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. -. SPACE TUG ECONOMIC ANALYSIS STUDY NAS 8-27709
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FINAL REPORT DR MA-04
VOLUME I I I : COST ESTIMATES
Prepared for National Aeronautics & Space Administration George C. Marshall Space Flight Center
Lockheed Missiles & Space Company, Inc. Sunnyvale, California and Mathemotica Inc. Princeton, New Jersey SPACE TUG ECONOM I C ANALY S I S STUDY
FINAL REPORT D R MA-04
May 1972
VOLUME Ill: COST ESTIMATES
Prepared For
National Aeronautics and Space Administration Mernhall Space Flight Center
Prepared By Lockheed Missiles & Space Company, Inc., Sunnyvale, California a nd Mathematica, Inc . Princeton, New Jersey
Lockheed Missiles $ S ce Company, Inc ., Sunnyvale, t?alifornia LMSC-Dl53408 Vol 111
FOREWORD
This report summarizes work accomplished under the Space Tug Economic Analysis Study on Contract NAS8-27709. This study was performed for the NASA Marshall Space Flight Center by Lockheed Missiles & Space Company, Jnc. of Sunnyvale, California, and Mathematica, Inc. of Princeton, New Jersey. The period of tech- nical performance was nine months, starting July 26, 1971.
The NASA Contracting Officer's Representatives for this program were Lieutenant Commander William C. Stilwell (USN) and Mr. Richard L. Klan. The study team was led by Mr. Charles V. Hopkins of Lockheed and Dr. Edward Greenblat of Mathematica. Task leaders on the Lockheed team were as follows: John P. Skratt - Data Integration and Interpretation William T. Eaton - Payload Data and Payload Effects Analysis Richard T. Parmley - Tug Definition
Other key team members included: Anthony G. Tuffo - Data Mechanization and Evaluation Zoe A. Taulbee - Computer Programming Jolanta B. Forsyth - Payload Costs and Benefits; Tug Cost Model Kenneth J. Lush - Program Costing Logic
This report is divided into three volumes as follows: r Volume I - Executive Summary Volume 11 - Tug Concepts Analysis r Volume 111 - Cost Estimates
Volume 111 contains two important elements of the study data base, namely the Tug costs and the entire payload data base. In addition to costs, the payload data includee 8 weight, sizes, orbital parameters, and schedulee.
1 LOCKHEED MISSILES & SPACE COMPANY CONTENTS
Chapter FOREWORD iii 1 INTRODUCTION 1- 1 2 GUIDELINES AND ASSUMPTIONS 2-1 Costing Assumptions 2- 1 Work Breakdown Structure 2- 1 3 ORBIT INJECTION STAGES 3- 1 Approach 3- 1 OIS Cost Data 3-2 Agena 3-2 Large Tank Agena (LTA) 3-4 Centaur 3- 5 Growth Tank Centaur 3- 8 Funding Requirements 3- 9 4 REUSABLE SPACE TUGS 4- 1 Approach 4- 1 RDT&E Costs 4-3 Single-Stage L02/L~2Tug RDT&E Costs 4-4 Single-Stage LF2/LH2 Tug RDTLF Costs 4- 11 Single-Stage FLOX/CH~Tug RDTBE Costs 4- 17 &age-and-One-Half LO~/LH~Tug RDTBE Costa 4-23 Investment Costs 4-26 L02/LH2 Single- Stage Tug Investment Costa 4-27 LF2/LH2 Single-Stage Tug Inwstment Costa 4-34 l?LOX/CH4 Single-Stage Tug Investment Costa 4-40 L02/LH2 Stage-and-One-Half Tug Investment Costs 4-46
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Chapter
Operations Costs L02/LH2 Single-Stage Tug Operations Costs LF2/LH2 Single-Stage Tug Operations Costs FLOX/CH~Single-Stage Tug Operations Costs LO~/LH~Stage- and-One-Half Tug Operations Costs Funding Requirements PAYLOAD COSTS AND CHARACTERISTICS Approach Payload Data
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ILLUSTRATIONS
Figure
Work Breakdown Structure 2-2 Typical Unit Cost vs Rate Curve for Agena OIS 3- 3 Typical Centaur OIS Recurring Cost vs I,:.* Curve 3-7 Large Tank Agena (OIS) Funding Requirements 3- 10 Parametric RLYP&E Costs for LO~/LH~Single-Stage, Growd-Based Tugs Parametric Avionics, Power and Structure RDT&E Costs, L02/~~2Single-Stage, Ground- Based Tugs 4- 8 Parametric Propulsion RDT&E Costs, L02/LH2 Single-Stage, Ground-Based Tugs 4- 9 Parametric Floating-Item RDT&E Costs, L02/LH2 Single-Stage, Ground-Based Tugs 4- 10 Parametric RIYP&E Costs for LF~/LH~Single-Stage, Ground- Based Tugs 4- 13 Parametric Avionics, Power and Structures RDT&E Costs, LF2/LH2 Single-Stage, Ground-Based Tugs 4- 14 Parametric Propulsion RDTOE Costs, LF~/LH~Single-Stage Ground-Based Tugs 4-15 Parametric Floating-Item RDT&E Costs, LF2/LH2 Single-Stage, Ground-Based Tugs 4- 16 Parametric RDT&E Costs for FLOX/CH~Single-Stage, Ground- Based Tugs 4- 19
Parametric Avionics, Power and Structures RM'&E Costs, ' FLOX/CH4 Single-Stage, Ground-Based Tugs 4-20 Parametric Propulsion RDT&E Costs, FLOWCH~Single-Stage, Ground-Based Tugs 4-21 Parametric Floating-Item RDTOE Costs, FLOX/CH~Slngle-Stage, Ground-Based Tugs 4-22 Parametric RDT&E Costs for L02/~H2Drop Tanks 4-25 Parametric First-Unit Costa for Reusable Versions of L02/LH2 Single-Stage Tugs 4-30 Parametric First-Unit Costs for Expendable Versions of LO^ /LH~Single-Stage Tugs 4-31
v
LOCKHEED MISSILES & SPACE COMPANY Figure
4- lfi Parametric Investment Costs for Reusable Versions of L02/L~2 Single-Stage Tugs Parametric Investment Costs for Expendable Versions of L02/LH2 Single-Stage Tugs Parametric First-Unit Costs for Reusable Versions of Lf2/~~2 Single-Stage Tugs Parametric First-Unit Costs for Expendable Versions nf LF2/~H2Single-Stage Tugs Parametric Investment Costs for Reusable Versions of LF2/LH2 Single-Stage Tugs Parametric Lnvestment Costs for Expendable Versions of LF~/LH~Single-Stage Tugs Parametric First-Unit Costs for Reusable Versions of FLOX/CH4 Single-Stage Tugs Parametric First-Unit Costs for Expendable Vcrsions of FLOX/cH4 Single-Stage Tugs Parametric Investment Costs for Reusable Versions of FLOX/CH4 Single-Stage Tugs Parametric Investment Costs for Expendable Versions of FLOX/CH4 Single-Stage Tugs parametric First-Unit Cost for LO~/LH~Drop Tanks Parametric Investment Costa for LO~/LH~Drop Tanks Parametric Follow-on Spares Costs for Reusable L02/LH2 Tugs Parametric Follow-on Spares Costs for Expendable L02/LH2 Tugs Parametric Operations Costs for Reusable LO~/LH~Tugs Parametric Operations Costs for Expendable L02/LH2 Tugs Parametric Follow-on Spares Costs for Reuaable LF~/LH~ Tugs Parametric Follow-on Spares Costa for Expendable LF~/LH~ Tugs Parametric Operations Costs for Reusable LF~/LH~Tugs Parametric Operations Costa for Expendable LF~/LH~Tugs Parametric Follow-on Spares Costs for Reusable FLOX/CH4 Tugs
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/ LOCKHEED MISSILES & SPACE COMPANY Figure Page 4-37 Parametric Follow-on Spares Costa for Expendable FLOX/CH, Tugs 4- 67 4-38 Parametric Operations Costs for Reusable FLOX/CH4 Tugs 4-68 4-39 Parnmetric Operations Costa for Expendable FLOX/CH4 Tugs 4-69 4- 40 Reusable Tug (50.2K) LO~/LH~Funding Requirements 4-73
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{ LOCKHEED MISSILES & SPACE COMPANY TABLES
Table
Average Recurring Production Cost for the Agena OIS 2-2 RDTOE Cost for LO~/LH?Single-Stage, Ground-Based Tug (Wp = 36.3K) 4- 5 RDTOE Cost for LO2 '5H2 Single-Stage, Ground-Baaed Tug (Wp = 50.2K) 4-6 RDT&E Cost for LF~/LH~Single-Stage, Ground-Based Tq: (Wp = 47.8K) 4- 12 RDTOE Cost for FLOX'CH4 Single-Stage, Ground-Based Tug (W, = 52. OK) 4- 18 RDTOE Cost for LO~/LH~Stage-and-One-Half, Ground-Based Tug (Wp = 30K) 4-24 First-Unit Cost for LO2/L4HZSingle-Stage, Ground-Based Tug (Wp = 36.3K) 4-28 First-Unit Cost for LO~/LH~Single-Stage , Ground-Based Tug (Wp = 50.2K) 4-28 Investment Cost for L02/LH2 Single-Stage, Ground-Based Tug (Wp = 36.3K) 4-2 9 Investment Cost for LO2/LH2 Single-Stage, Ground-Based Tug (Wp = 50.2K) 4-29 First-Unit Cost for LF2,'~~2Single-Stage, Ground-Based Tug (Wp = 47.8K) 4-35 Investment Cost for LF2/LH2 Single-Stage, Ground-Baaed Tug (Wp = 47.8K) 4-35 ~irst-unitCost for FLOX/CH~Single-Stage, Ground-Based Tug (Wp = 52. OK) 4-41 - Investment Cost for FLOWCH~Single-Stage, Ground-Baaed Tug (Wp= 52. OK) 4-41 First-Unit Cost for LO /LH Stage-and-One-Half, Ground- Based Tug (Core Wp z230~f 4-47 Investment Cost for LO hH2 Stage-and-One-Half, Ground- Based Tug (Core Wp =%OK) 4-47 Operations Cost Breakdown for L02/~~2Single-Stage, Ground-Based Tug (Wp = 36.3K) 4- 52
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Table
Operations Cost Breakdown for L02/LH2 Single-Stage, Ground-Based Tug (Wp = 50.2K) Operations Cost ~reakdownfor LF~/LH~Single-Stage, Ground-Based Tug (Wp = 47.8K) Operations Cost Breakdown for FLOWCH~Single-Stage, Ground-Basea Tug (Wp = 52. OK) Operations Cost Breakdown for L02/LH2 Stage-and-One-Half, Ground-Based Tug (Core Wp = 30K) Payload Coats nnd Characteristics for Mission No. 2 Payload Costs and Characteris:ics for Mission No. 3 Payload Costs and Characteristics for Mission No. 4 Fayload Costs and Characteristics for Mission No. 5 Payload Costs arid Characteristics for Mission No. 7 Payload Costs and Characteristics for Mission No. 8 Payload Costs and Characteristics for Mission No. 9 Payload Costs and Characteristics for Mission No. 10 Payload Costs and Characteristics for Mission No. 11 Pnvload Costs and Characteristics for Mission No. 12 Payload Costs and Characteristics for Mission No. 21 Payload Costs and Characteristics for Mission No. 22 Payload Costs and Characteristics for Mission No. 2?. Payload Costs and Characteristicn for: Mission No. 24 Payload Costs and Characteristics for Mission No. 25 Payload Costs and Characteristics for Mission No. 26 Payload Costs and Characteristicrj for Mission No. 27 Payload Costs and Characteristics for Mission No. 28 Payload Cosh3 and Characteristics for Mission No. 29 Payload Costs and Characteristics for Mission No. 30 Payload Costs and Characteristics for Mission No. 31 Payload Costs and Charactc:ristics for Mission No. 32 Pnyload Costs and Characteristics for Mission No. 33 Payload Costs and Chara.cteristics for Mission No. 34 Payload Costs and Characteristics for Mission No. 35
/LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol III
Table
Payload Costs and Characteristics for Mission No. 36 Payload Costs and Characteristics for Mission No. 37 Payload Costs and Characteristics for Mission No. 50 Payload Costs and Characteristics for Mission No. 51 Payload Costs and Characteristics for Mission No. 52 Payload Costs and Characteristics for Mission No. 53 Payload Costs and Characteristics for Mission No. 54 Subfield 1 Payload Costs and Characteristics for Mission No. 54 Subfield 2 Payload Costs and Characteristics for Mission No. 55 Payload Costs and Characteristics for Mission No. 57 Payload Costs and Characteristics for Mission No. 58 Payload Costs and Characteristics for Mission No. 59 Payload Costs and Characteristics for Mission No. 60 Payload Cosb and Characteristics for Mission No. 70 Payload Costs and Characteristics for Mission No. 71 P~yloadCosts and Characteristics for Mission No. 72 Payload Costs and Characteristics for Mission No. 73 Payload Costs and Characteristics for Mission No. 74 Payload Coats and Characteristics for Mission No. 75 Payload Costs and Characteristics for Mission No. 76 Payload Costs and Characteristics for Mission No. 77 Payload Costs and Characteristics for Mission No. 78
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{ LOCKHEED MISSILES dr SPACE COMPANY
Chapter 1 INTRODUCTI ON
Volume 111, Cost Estimates, contains all of the Tug and unmanned-payload costs that formed the basis for the comparisons and evaluations reported in Volume II. Included in the cost data are point estimates, parametric cost data, and funding curves. Vol- ume lII also contains summaries of the technical approach, guidelines, and assumptions used to derive these costs.
The objective of the cost analysis tasks in the Space Tug Economic Analysis study was to provide a data base from which comparisons of total Tug program cost (Tug cosL plus Shuttle user fees and payload costs) could be made. Because of this the cost data generated in the study had to be valid in two senses:
1. Proper overall magnitude for each configuration 2. Proper relative magnitude among the configurations As a result the emphasis in cost analysis ww on attaining relative accuracy, rather than precision, in the results.
Volume 111 is organized in the following way. Chapter 2 presents the important guide- lines and assumptions that were used to constrain the cost analysis, and the work break- down structure (WBS) that was used to format Tug c:oets. Chapters 3 through 5 then present the specific approach and key results of the cost analysis, in the following sequence : o Chapter 3 - Orbit Injection Stages a Chapter 4 .- Reusable Space Tugs Chapter 5 - Payloads
Chapter 3 presents the point costs estimated for the expendable orbit injection stagee. These stages are either existing vehicles or derivatives of existing vehicles, and be- cause their sizus are c!utahliabed, no pnrametric coat data wuro gonornttd for anv of thc OLS confiyurallonv. 1- 1
{ LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol 111
Chapter 4 contains cost data for reusable Space Tugs and also for expendable versions of these Tugs. The cost data include both point estimates and parametric data. The point costs, presented in the work breakdown structure format, ?.re for the Tug sizes and concepts that were selected for further study at the end of Phase I; RDT&E, first- unit, investment, and operations costs are presented for each Tug concept. The para- metric data are in the form of direct computer plots of cost 1.5 propellant loading, or cost vs activity level.
Chapter 5 contains payload data. This chapter comprises the comp! 3te payload data base for the study and includes payload costs, weights, dimensions, flight schedules, and orbital parameters for the unmanned spacecraft considered in this analysis. DoD payloads are described in a classified appendix to Chapter 5. This appendix is distributed on a limited basis.
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Chapter 2 GUI DELI NES AND ASSUMPTIONS
COSTING ASSMPTIONS
Important assumptions made in performing the cost analysis were as follows:
0 Constant year dollars were used. To be consistent with other studies of the Space Transportation System, the year selected was 1970. a The reference value for the Shuttle user fee was set at $5 million per flight. This value was used independently of the number of Shuttle flights required. a Prime contractor fee was omitted, but subcontractor and supplier fees were accounted for in the magnitude of costs. Tugs were assumed to be produced at a minimum efficient rate (roughly 5 per year) to minimize the costs of sustaining a production base. a In calculating Tug fleet requirements, it was assumed that reusable Tugs ap- proaching the end of their nominal (design) lifetime would be used on missions requiring an expendable stage. The recurring costs for Tugs and OIS vehicles do not include mission-peculiar services or software. All RDT&E costs include expenditures for a flight test program and also costs for developing and building Shuttle interface hardware. No costs for Government manpower (e. g., program management, tracking network, mission control center) or Government-furnished equipment/services are included.
WORK BREAKDOWN STRUCTURE
In reporting the Tug costs, a hardware-end-item-oriented work breakdown structure (WBS)is used. This WBS (Figure 2-1) is organized in general accordance with Attach- ment 2 to NASA Data Requirements Description MF-030, as contained in the statement of work for this contract. The subsystem level (level-5 in MF-030) is the keystone; the study WBS carries principal Tug subsystems and important services (designated as floating items in MF-030) at this level. nSPACE TUG SYSTEM
SPACE TUG SPACE TUG
I I I I I LAUNCH FLIGHT TRANSPORTATION STRUCTURES POWER SUPPLY AVIONICS 6 DISTRIBUTION PKOPULSION OPERATIONS 41 SERVICES 6 SERVICES FLIGHTS)
-CORE STAGE -GUIDANCE 6 -ELECTRICAL -MAIN COMMUNICATIONS VEHICLE STRUCTURES NAVIGATION POWER ROCKET OPERATIONS b CONTROL MAINTENANCE ENGINES 6 THERMAL -COMMUNICATIONS - HYDRAULIC PROPELLANTS -REPUCEMENT - FOLLOW-ON PROTECTION 'ORIENTATION SPARES h3 'INSTRUMENTATION CONTROL FACILITIES & TRAINING I PROPELLANT EuUlPMENT -RECOVERY h3 FEED, FILL, MAINTENANCE OPERATIONS DRAIN, 6 PRESSURIZATION ENGINEERING SUPPORT LDROP TANKS PROGRAM MANAGEMENT 6 INTEGRATION I I I I RANGWBASE GROUND INT EGRATION, TEST TEST SUPPORT SUPPORT TOOLING ASSEMBLY 6 OPERATIONS HARDWARE EQUIPMENT CHECKOUT - A
ENGINEERING PROGRAM
Figure 2- 1. Work Breakdown Structure LMSC-Dl53408 Vol I11
In accordance with Attachment 2 cited above, the Space Tug work breakdown structure i: tailored to fit the parametric cost model that was used to generate reusable Tug esti- mates. Consequently, this WBS has taken on some of the characteristics of the cost model, as follows:
a The subsystem groupings are fairly broad, reflecting the generalized nature of the data base a The hardware breakdown is also intended to serve the Space Shuttle; conse- quently systems such as hydraulics, that are major elements of Shuttle hard- ware, are identifiad as separate line entries even though hydraulic systems are a minor cost element in space vehicles
To help reconcile the Tug costs quoted in this volume with the historical cost studies that are now nearing completion under NASA sponsorship and that use the more detailed WBS format of MF-030, the following important definitions of Space Tug WBS entries are provided:
Structures. In addition to costs for the major load-bearing structural members, this entry includes costs for thermal/meteoroid protection and propellant feed/management systems. It also includes a proportion af the analytical definition and support tasks perform: - at the total-vehicle level. These latter tasks, including weights, structural dynamics, loads, and thermodynamics analyses, are sometimes carried under Systems Engineering and Integration. Specific items of hardware carried under Structures are as follows:
a All integral and nonintegral propellant tanks, including bulkheads a Al' 'od-carrying elements including thrust structure, intertank sections, and interstages .,All pressurization system elements (tanks, plumbing) a All propellant feed, fill, and arain elements a Tank insulation and meteoroid shielding a Propellant utilization systems a Przjpellant orientation and management systems (screens, baffles, zero-g gent devices)
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Avionics. This entry refers to the major electronic systems required to guide, stabilize, monitor, and communicate with the Space Tug. Specific items included under Avioni6s are as f Jlows: a Guidance and Navigation. lncludes all ~nertialreference elements; navigational sensors; stabilization and control electronics; rendezvous and docking electron- ics; and central computers (regardless of whether the computers also serve other subsystems) a Communications. Comprises all rf equipment requlred to transmit information between Tug and Shuttle, or between the Tug and ground stations. Equates to Telemetry/~racking/Command subsystem in unmanned spacecraft terminology. a Instrumlmtation. Includes all sensors, data conditioning and data evaluation hardware, and associated interconnections. Also includes displays and status panels.
Power Supply and Distribution. This entry covers all hardware that produces either electrical or hydraulic/pneumatic power. Specific elements subordinate to Power fhp- ply and Distribution are as follows: a Electrical Power. Includes power supply (e. g., batteries, fuel cells), power conversion, and power distribution (electrical harnessing, junction boxes). a Hydraulic Power. Includes power packages, accumulators, lines, and actuators (not used with reusable Tug because these vehicles have electromechanical gim- bal actuators)
Propulsion. This WBS entry covers all Tug propulsive systems: primary, secondary, and orientation control. It includes engines for all systems, and feed/fill/drain/ pressurization functions for the secondary and orientation control systems. Systems subordinate to Propulsion are as follows: Main Rocket Engine. Iticludes the engine and its electromechanical thrust vector control mechanism. Excludes main stage tankage, pressurization, plumbing, and propellant management devices a Orientation Control. Equates to Reaction Control or Attitude Control systems in other nomenclature. Comprises engines, tanks, and all feed functions.
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Integration, Assembly and Checkout. This entry covers all stages between the completion of subsystems hardware and the delivery of the completed Tug. It includes the following steps:
a Final Assembly. Installation of subsystems, assembly of major segments, alignment, and checkout Acceptance Test. Functional testing in specified environments, and all support- ing test plans, quality assurance, and documentation activities
Tooling. This entry includes all costs associated with tooling and special test equip- ment (STE). It specifically comprises the cost of planning, design, fabrication, assem- bly, installation, mcdif ication, maintenance, and rework of all tooling and STE, as follows:
Tooling. Includes assembly tools, dies, jigs, fixtures, master forms, gauges, and in-plant handling equipment Special Test Equipment. Includes simulators, test sets, ar 3 other hardware designed to accomplish the in-process testing of avionics equipment
Ground Support Equipment. This entry includes the cost of development, engineering, testing, and production of all ground-based equipment required to support the Space Tug during test (development and acceptance), launch, and refurbishment. It comprises checkout equipment, ground handling adservicing equipment, and launch monitor and control equipment.
Test Hardware. This WBS entry covers all major test articles used during the RDT&E phase of the Space Tug program, including ground- snd flight-test articles as follows:
Ground Test Hardware. Includes the cost of manufacturing mockups and the complete vehicle elements needed for structural/dynamic testing, propulsion system integration testing, and all-systems testing. Hardware for subsystems development and qualification test is excluded from this element but is included with the appropriate subsystem design and development costs. Flivht Test Hardware, Includes the fabrication, assembly and acceptance-test costs of all flight test articles.
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Test Operations. This cntry comprises the direct costs of conducting all system-level ground and flight tests. It includes manpower for test planning, test operations, and data reduction/evaluation; it also includes all consumables used during these tests, particularly propellants and gases. Specific test operations cost elements are aa follows: Ground Test. Includes only system-level tests such as structures, dynamks, cold flow, and hot firings. Excludes subsystem level tests (these are carried under the appropriate subsystem entries in the WBS). a Flight Test. Includes the costs for Tug launch, flight, and refurbishment op- erations in the RDT&E phase; flight-test data reduction and evaluation; and Space Shuttle user fezs for the test flights.
Training, This entry covers the costs of initial personnel-training irctivities, design and fabrication of simulators and teaching aids, and development of curricula. The skills taught in the training program include Shuttle crew operations for Tug checkout, deployment, and retrieval; mission-control crew functions; and launch base operations with the Tug.
Facilities and Equipment, This entry covers the costs incurred to design, build, and activate new facilities for the Space Tug. Because existing facilities are sufficient for manufacturing and testing of the Tug, and because Shuttle launch facilities will serve both vehicles, the only fncili,~esrequired for the Tug are refurbishment and mainte- nance shops.
Systems Engineering and Integration. T5is entry covers two separate elements from the Tug cost model, namely Systems Engineering and Vehicle Integration. Systems Engineering is defined in the model to include: eatabliahing engineering design charac- teristics; determinicg criteria for design review; establishing procedures for testing components, subsystems, or vehicle elements; integration of ground and flight test re- sults into the vehicle design; developing procedures for vehicle maintenance; quality planning and administrative engineering. Vehicle Integration is defined as the cost of engineering and development activities relating to the definition of vehicle and payload interfaces, and the proper integration of the Tug with other vehicle system elements. Some of the costs identified under Systems Engineering and Integration in historical studies are prorated to the subsystems (particularly Structures) in the Tug cost model.
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Program Management. This entry covers the costs for prime-contractor direct costs associated with managing the Tug program. It includes the cost of maintaining a project office to perform such functions as overall technical direction and coordination; pro- gram control (schedules and costs); and documentat ion (reports, specifications, manu- als). This WBS entry specifically excludes salaries of managers and executives work- ing for the contractor; these persons are indirect employees.
Launch Operations and Services.- This WBS entry covers all events between the time that a new Tug arrives at the launch site (or a refurbished Tug is delivered from the maintenance shops) l;o the time the Shuttle is launched. Specific cost elements subordi- nate to this entry are as follows:
8 Launch Operations. Includes the costs for manpower to perform receiving inspection, TII~checkout, payload mating and checkout, prelaunch handling (in support of Shuttle crew), Tug propellant loading, and participation in the countdown Propellants. Comprises costs for main-stage and orientation-control propel- lants, and all gases, flushing compounds, and miscellaneous fluids. Facilities and Equipment Maintenance. Refers to the recurring costs for main- tenance and operation of all Tug facilities and GSE at the launch site 8 Engineering Support. Includes sustaining engineering, liaison and engineering services activities performed at the contractor's plant and at the launch site during the Operations phase of the Tug program 8 Pro~ramMana~ement and Integration. Comprises costs for administration and management services in support of the Tug launch-base activities, e. g., cost and schedule control and reporting, management, and clerical salartea Range/Base Srlpport. Refers to the costs of services (usually provided by a support contractor) that support the direct launch and maintenance operations. Includes range safety and control; shop and repair services; standards md in- strument calibration; and base services such as food, mail, reproduction, security, fire protection, utilities, communications, transportatton, health and custodial services, and logistics support.
Flight Operations and Services. This WBS entry covers all Tug activities from launch of the Shuttle through recovery of the Tug at the completion, of its mission. Specific cost elements subordinate to this study are as follows:
a Communications and Control. Also known as Mission Control. Includm costs associated with ground command, control, and tracking from Tug launch through tnission completion and returr. Includes such functions as flight con- trol, telemetry, communtcations, data processing and data analysis.
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Replacement Training. Includes the cost of training qualified Shuttle and mission-control crew personnel, to replace those lost by rotation or attrition, in order to maintain manning at levels necessary to meet flight and ground operation schedules. Recovery Operations,- Includes the cost of assisting in recovery operations, propellant purging, vehicle deactivation and servicing. Assumes that the Tug returns within the Shuttle bay.
Refurbishment. This WBS entry covers all activities between the time when a deacti- vated Tug is returned froin the flight cycle ar,, he time that this Tug is delivered to the launch facility ready for a new prelaunch cycle. Cost elements specifically included under this entry are as follows: Vehicle Maintenance, Includes the cost to restore a reusable Tug after mission completion to a readiness condition for subsequent missions. All coats per- taining to inspec tion, maintenance, replacement of necessary parts, repair (as necessary) of components, and testing are included. This activity ie com- pleted when the vehicle is ready for launch operations. Includes both normal turnaround between flights and regularly scheduled overhauls . Follow-on Spares. Refers to the coats of spare parts and components produced to repleni~hinitial spare stocks in support of Tug maintenance and overhaul, both scheduled and unscheduled.
Transportation. This WBS entry accumulates costs for Space Shuttle user fees incurred in delivering the Tug and its payload to low earth orbit. A baseline user fee of $5 million per flight was used in this study.
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Chapter 3 ORB IT INJECTION STAGES
This chapter reports cost estimates derived for the orbit injection stage (01s) claae of Space Tags. The OISs are existing stages, or growth versions of existing stages, modified for Shuttle compatibility and flown only in the expendable m )de. Important aspects of the OIS cost analysis are as follows: Point costs were derived rather than parametric data because the OIS sizes ware generally well established The emphasis in costiq was on deriving estimates that were comparable between concepts, especially for the unit production and operations costs that drive OIS total-program expenditure levels. a The recurring production costs cited for OIS concepts are average unit values at a givcn production rate. Theoretical first-unit costs were not presented becrbuse the OIS concepts represent mature space-vehicle designs whose costs are influenced by production rate rather than learning effects.
APPROACH
The estimates of 01s costs were derived using a two-step procedure. First, a set of preliminary estimates was made so cost comparisons could be made using the STAR/ ANNEX computer program. The unit costs were estimated on the basls of current pricing data for the existing Agena and Centaur stages. RDT&E costs for the con- version of those stages to OIS cotlfigurations were estimated by extrapolation from compar~bledevelopment programs.
Then, as tho NASA-funded studies of Agena and Centaur OE3 vehicles (NAS9-11949 and NAS3-14389, respectively) were completed, the reeulte of the more detailed eetimates formulated on these contracts were compared with the preliminary valuee. Differences between the two sets of estin- tee were evaluated and reconciled.
The results of this analysis are presented in th? following eections.
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015 COST DATA
Agena
'i'he ~)reliminrtrycost estimates used to represent the existing Aget:.~ (modified for scrvicc as an orbit injection stage) were as follows: 7- I1 Recurr iilg Production $ 2.29 Milli Recurring Operat ions $ 0.68 Mill. . I1
The recurring costs were calculated assuming the production and launch rates needed to sustain a best-mix family of Agena and Centaur (i. e., 378 Agenas md 116 Centaurs) over the 12 year mission model. A tabular breakout of Agena OIS recurring production costs formulated in this analysis is presented in Table 3-1.
Table 3-1. AVERArJZ HECURRXNG PRODUCTION COST FOR THE AGENA OIS
1tern Structure (0.261) Structures and Thermal Protection 0.1 91 Propei lant Fzed and Management I 0.076 Avionics Guidance and Navigation Communications Instrumentation 1 I Power Supply ard Distr.ibution I (0.1 04) I Electrical Hydraulic I Propu Isi on I (0.523) I Main Rocket Engine Orienlai ion Control I Integration, Assembly, Checkout, and Test I 0.225 I I Program Management I 0.061 I I Systems Engineering I 0.245 I Spans 0.058 Total 2.292 LMSC-Dl63408 Vol 1x1
In lhe Shuttle/A~cncle tudy pcrfornled by Ilockheed for NASA/ MSC (NAS9-11949) these coats wcre complct~~lyrr.!c;llculntcd using :I rigorous bottom-up estlmnting mcthdolcr;~, In general, the rccalculnted costs werc found to be in ;~grcemcntwith the preliminary values once rate differences wcre nccounttd for. Spm:ific compurtsona of thc cost data arc as follows: Recurring Production. The detailed analysis of Agena OIS unit production colvts gave an estimate of $3.41 million per vehicle at a manufacturing rate of aix per year; projected cost reductions with higher rates are shown in Figure 3-1. When extrapolated ta the Agena/Centaur best-mix launch ratc! of over 30 Agenas per year, the unit costs drop to around $2.2 million e~,:h; this is in excellent agreement with the preliminary estimaie. Recurring Operations. The detailed cost analysis resulted ir. an estimate of $780,000 per flight for recurring operations (launch ,.~d flight operatious/ services) at a rate of 6 l:.wnches per year. This compares t.9 ehe preliminary estimate of $682,000 at over 30 Agena OIS launches per year. When meas- ured against other Agena launch rate/cost projections, the original estimate of $682,000 at more than 30 launches per year is conside;:ec quite conservative. RDT&E. In the detailed Agena OIS cost analysis it was estimated that devel- opment of the Agcna for service as an orbit injection stage (including Plbri- cation of six sets of Shuttle interface hardware and one flight test artic..ej would cost $40.469 million. This compares to an original estimate of $43.9 million, a variation of less than 10 percent.
C X (TYPICAL AGENA OIS VALUES)
Figure. 9-1 mica1 Unit Cost vs Rate Curve for Agma OIS
/ LOCKHEED MISSILES & SPACE COMPANY LMSC -Dl53408 Vol I11
In summary the preliminary values used for the Agena OIS in cost comparisons were equivalent lo the refined estimates, or were slightly more conservative,
Large Tank Agena (LTA)
The preliminary estimates used to represent the Large Tank Agena OIS in cost com- parisons were as follows:
The recurring costs were based on production and launch rates needed to sustain the 12 year mission mdcl using exclusively the Large Tank Agena OIS, that is, rates in excess of 40 per year. Tile R3T&E costs were based on a development program in which the OIS development would proceed directly to the large-tank version of Agena rather than evolving from a 5-foot diameter Agena OIS. ( : In t;.; reflned cost analysis performed under contract NAS9-11949 the LTA orbit in- jection stages were estimated at the same level of detail as the Agena 01s. Comparing the result~lof this refined analysis with the preliminary estimates just discussed, the following specific observations can be made:
Recurring Production. In the detailed cost analysis, unit production costs for the LTA orbit injection stage were estimated at $3.86 million for a manufacturing rate of six vehicles per year, whereas the preliminary esti- mate was $2.59 million based on a production rate of 40 vehicles per year. Although no unit-coat-versus-rate chart was formulated for the LTA orbit injection stage, the $2.59 million cost at 40 per year appears consistent with the $3.86 million at six per year if the trend of the baseline Agena rate curve applies. Recurring Operations. The derived operations cost of the LTA OIS was $844,000 per launch at six fiights per year. This compares with the $682,000 preliminary estimate based on 40 launches per year. In rec- onciling these two values it appears that $682,000 is a reasonable-to- slightly-conservative extrapolation of the operations costs at over 40 launches per year. RDT&E. The RDT&E cost for a Large Tank Agena OIS was estimated at $47.662 million in the detailed cost analysis and at $51.9 million in the pre- liminary, a difference of less than 10 percent.
/ I nr -ucFn .qlCrll FS I-: SPACE COMPANY . ..- 'a. .- '9-
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In summary, the LTA orbit injection stage costs asused in the preliminary comparisons agree reasonably well with the detailed estimates derived in the Agena O!S study.
Centaur
The preliminary Centaur cost estimates used by Lockheed to compare OIS concepts were as follows:
The recurring costs were calculated assu~llingthe production and launch rates needed to sustain a best-mix family of Agena and Centaur (116 Centaurs over 12 years). A tabular breakout of Centaur OIS recurring-production costs, as used in the Tug con- cept cornparlsons, is presented in Table 3-2.
Table 3-2. PAVERAGE RECURRING PRODUCTION COST FOR CENTAUR OIS
Item Cost ($ Mil lions) ~tructure (1 -462 ) Structures and Thermal Protection 0.662 Propellant Feed and Management 0.800 *r,vionics (1 -341 ) Guidance and Navigation 1 -056 Communications 0.285 Instrumentat ion 1 Power Supply and Distribution (0.1 97) Electrical 0.095 Hydrau 1i c 0.1 02 Propulsion (1 -41 1 ) Main Rocket Engines 0 .a80 Orientation Control 0.531 Integration, Assembly, Checkout and Test 0.335 Program Management x Systems Engineering * Tota I 4.746
- p~ *Distributed among Subsystems 3- 5
LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol I11
In the study "Compatibility of a Cryogenic Upper Stage with Space Shuttle, " performed by General Dynamics/Convatr Aerospace for NASA Lewis Research Center (contract NAS3-14489), a systematic analysis of Centaur OIS costs was conducted. The results of this analysis show that there is general agreement between these costs and Uckit@r?d preliminary estimates in all areas except RDT&E funding requirements. Specific com- parisons are as follows:
Recurring Production. The recclrring production costs estimated by Convair Aerospace totaled $5.24 million each at a production rate of fot~rvehicles per year. A curve of the expected Centaur OIS cost versus production rate was also formulated by Convair; this curve is presented as the upper plot in Figure 3-2. When extrapolated to the Centaur launch rate for an Aged Centaur best-mix (approximately nine per year) the imit cost of a Centaur OIS declines to about $4.7 million, which is in excellent agreement with the preliminary estimate. Recurring Operations. The detailed Convair Aerospace cost analysis esti- mated Centaur OIS recurring operations costs at $1.69 million for a launch rate of four per year, with cost reduction for higher rates as shown in the lower curve of Figure 3-2. When extrapolated to nine launches r?r year this estimate drops to approximately $1.2 million, which agrees exactly with the preliminary estimate. The Convair costs, however, exclude propellauts and gases. RDT&E. Convair Aerospace estimated the cost to modify the Centaur D-1T to an orbit injection stage configuration at $30.6 million. This estimate is based on the assumptions that there would be no flight test of the Centaur OIS, and that two operational sets of Shuttle interface equipment would be procured. This estimate differs by a factor of two with the preliminary costs estimated by Lockheed. Obvious sourcec of difference between the two values are (1) the inclusion of a flight test program in the Lockheed estimate and (2) the difference in amount of operational Shuttle interface equipment procured (six sets assumed by Lockheed and two by Convair Aerospace). The other variances apparently arise from differing inter- pretations of relative con~plexityin Centaur modification to the OIS configuration.
In summary, the preliminary estimates for Centaur OIS used in cost comparisons were in agreement with Convair Aerospace estimz.tes, except in the area of RDT&E cost. However, inasmuch as development coats were not a factor in the economic ranking of OIS concepts, the importance of the RDT&E cost discrepancies was minimal.
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Growth Tank Centaur
The preliminary cost estimates formulated by Lockheed for the Growth Tank (G'I') Centaur were as follows:
Reclirr tng Production $ 5.25 Million Recurring Operations $ 1.20 Million RDT&E $65.50 hlil!iou
The recurring costs were calculated assuming production and launch rates of nine vehicles per year.
Under contract NAS3-14389, Convair Aerospace estimated, on a preliminary basis the costs of a Growth Tank Centaur orbit injection stage. The results of this analysis may be comnared to the preliminary costs as follows:
8 Recurring Production. Growth Tank Centaur OIS recurring production costs were estimated to be $5.5 million at a rate of four per yebr. This contrasts with Lockheed1s estimate of $5.2 5 million at a production rate of nine vehicles per year. No cost-versus-rate curve was generated by Convair Aerospace for the GT Centaur 01s; however, based on Centaur trends it is estimated that the preliminary values are about $200,000 higher at nine per year than an extrapolation of the Convair estimate. 8 Recurring Operations. Convair Aerospace did not identify any increase in recurring-operations costs in going- - from the D-1T to the GT wersion of a Centaur 01s.- However, the Convair estimates specifically exclude propellants and gases, one of the launch cost items that would definitely increase for the larger GT Centaur. After adjusting the Convair estimates of $1.69 million per launch (at four per year) for rate variations there results a cost identical lo the preliminary value of $1.2 million. Both values are low by the cost of propellants and gases. 8 RDT&E. The RDT&E cost estimated by Convair Aerospace for developing an 018 to the GT Centaur configuration (without the intervening step of a D-1T Centaur version) is $36.2 million. This compares to the Lockheed preliminary estimate of $65.5 million. The same factors that were dis- cussed with relation to the differences between Convair and Lockheed estimates for the D-1 T Centaur OIS apply here.
In summary, the comparative costs used by Lockheed in the Space Tug Economic Analysis for the GT Centaur OIS were sIightly higher in recurring-production cost than Convair's value. Both values were identical in recurring operations, but are
I I QCKHEFD MISSILES & SPACE COMPANY LMSC -Dl53408 Vol 111
probably low because of propellant/gas requirements. The RDT&E costs estimated by Convair were just over half the value estimated by Lockheed; the differences re- flect varying assumptions and differing estimates of the development complexity.
FUNDING REQUlREMENTS
Tug funding requirements by year were calculated for all OIS configurations as part of the STAR/ANNEX program. Standard statistical spread functions were used to distribute costs over the applicable time spans. No smoothing of expenditure curves was performed.
To typify the funding pattern lor the entire class of orbit injection stages, the annual expenditure requirements of a promising OIS configuration (the Large Tank Agena) have been plotted by fiscal year. This graph is presented as Figure 3-3. The funding requirements shown here represent expenditures for RDT&E, recurring production (i... estment in the expendable Tug fleet), and recurring operations for the &2 year 42 duration of the mission model. These costs specifically exclude Space Shuttle user fee, and all payload costs. The characteristic funding curve for an orbit injection stage features low early-year funding ($20 million peak for LTA in FY 1976-77); this is of importance because peak Shuttle funding requirements occur in this same general time period. However, Large Tank Agena OIS funding requirements increase to a level of about $150 million during the operational period. The total funding for the Large Tank Agena OIS amounts to $1.64 billion.
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1 I nevHrFQ MISSILES & SPACE COMPANY LMSC-Dl53408 Vol lII
RECURRl NG PRODUCTION (INVESTMENT)
74 76 78 80 82 84 86 88 90 FISCAL YEAR
Figure 3-3. Large Tank Agena (OIS)Funding Requirements
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Chapter 4 REUSABLE SPACE TUGS
Chapter 4 reports the cost estimates derived for the general class of reusable Space Tugs (both reusable and expendable versions of the Tugs). This chapter is organized in the following manner. First, cine approach used in costing ieusable Tugs is summarized briefly. Then the cost data for specific Tug concepts are presented in detail. The sequence of data follows a time-phased order, as follows:
1. RDT&E costs 2. Investment phase costs (including theoretical first-unit values) 3. Operations costs
Within each phase, the costs are compared by concept in the following sequence:
Point costs are given (in the WBS format) for the reference Tug sizes selected at the end of Phase I and then parametric cost curves are given to extend the data across the spectrum of Tug sizes. In the first-unit cost data, parametric estimates are presented for both expendable and reusable versions of the Tug concepts.
The final section of Chapter 4 discusses funding requirements for these reusable Tugs.
APPROACH
The costing of reusable Space Tug concepts was accomplished by the use of a parametric cost model that was automated within 'Ile logic of the STAR/ANNEX computer program. This cost model was based on an earlier model derived by Aeroepace Corporation
~STSCost Methodology, Volume 11, "Orbit-to-Orbit Shuttle Cost Methodology, l1 Aerospace Corp. , TOR-0059(6759-04)- Auguat 31, 1970, as revised. LMSC -Dl53408 Vol I11
for chemical orbit-to-orbit shuttle systems, This basic model was augmented as other data from NASA or Lockheed sources became available. Certain of the cost estimating relationships in the model were replaced and certain of the complexity factors were modified.
The resulting model reflects the most detailed estimates attainable with thc given historical base. In this model costs for major categories of subsystems and services are estimated using cost estimating relationships (CERs). These CERs relate cost to technical parameters (primarily weight); they are based on broad historical data for launch vehicles, manned and unmanned spacecraft, and liquid-propellant ballistic missiles. Because the data base is so broad and the data are in inconsistent formats, the categories of costs for CERs are also very broad. For example the CER for Structures includes in addition to load-carrjing structural members, insulation (thermal protection), propellant feed/fill/drain, and pressurization systems; it also includes some share of overall-system design and sustaining-engineering costs,
Any costs not estimated directly by CERs are derived by other mathematical relation- ships that take into account both the hardware costs (as derived from the CERs) and external factors such as activity level.
Complexity factors are applied to the resulting costs, to account for differences of propellant type, design concept, or lifetime. In addition, learning curve factors are applied to the theoretical first-unit costs to ad just for production improvement effects; these learning factors are also assumed to compensate for size-of-buy efficiencies.
The output of this model is a breakdown of reusable Tug dollar estimates to major cost-producing elements for the RDT&E, investment, and operations phases. NASA is now in the process of building a cost data bank with far greater detail than the sources used for this Tug cost model; moreover, these studies are being conducted with a common reference format so the results will be more directly comparable. When the data bank is complete, a Tug cost model of far finer detail will become feasible.
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RDT&E COSTS
The costs for the rescarch, development, test, and evaluation (RDT&E) phase of the reusable Space Tug program are presented here. The RDT&E phase costs include all nonrecurring expenditures that would be made for the Space Tug program from the start of Phase C (Design) through the date of initial operational capability (IOC) for the full Tug system. Specific activities included in this phase are design and develop- ment of the Tug syst~m;fabrication oi ground- and flight-test hardware; test operations (ground and flight); design and fabrication of tooling and ground support equipment sufficient for the RDT&E phase; and training.
Important assumptions governing these RDT&2 costa are aB follows:
A total of five equivalent vehic!ss was coated under the WBS entry for Test Hardware; of these, three were ground-test articles and two were flight- test articles. Test Operations costs include 20 equivalent full-duration firings. Costs for Concept Feasibility and Definition phases of the program (Phases A and B, respectively, under Phased Project Planning criteria) were omitted. Technology progrsm costs (normally funded under Supporting Research and Technology expenditbres) were likewise omitted.
For definition of the individual WBS entries, refer to Chapter 2.
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/ LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol 111
Single-Stage L@/LH~ Tug RDT&E Costs
The RDT&E co; is for single-stage, reusable, ground-based Space Tug configurations that use L@/LH2 propellants are presented in this section. Point estimates for the RDT&E costs of two reference eizes (36,300 lb and 50,200 lb propellant loading) of this class of Tugs arc presented in Tables 4-1 and 4-2, respectively.
Parametric RDT&E cost data for single-stage Lm/Lli2 reusable Tugs are presented in Figures 4-1 through 4-4. Mgure 4-1 is a summary of RDT&E cost as a function of propellant loading. The variation in cost is caused solely by the overall size effects (e. g., larger tooling, costlier test articles, increased test-phase propellants). The primary breakdown of costs in Figure 4-1 follows a nomenclairlre peculiar to the cost model. Each of the cost entries on this chart is further broken down as follows: Airframe. Consists of the structures, avionics, and power subsystems. The parametric breakdown of these costs ie given in Figure 4-2. Propulsion. Consists of main-engine and orientation-control systems. The Xreakdom of these costs is presented in Figure 4-3. Miscellan Equates to floating-item (services) type costs. The breakdown dese costs is presented in Figure 4-4.
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{ LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol I11
Table 4-1. RDT&E C08T FOR ~/LH~SINGLE-STAGE, GROUND-BASED 1'UG (Wp= 36.3K)
I ltern Cost ($ mi llions) Structure 87.1 91 Avionics (28 ..99)) Guidance and Navigation 16.834 Communications 9.931 Instrumentation 2.1 73 Power Supply and Distribution (21,010) Electrical Power 21,010 Ropu lsi on (1 3? ,775) Main Rocket Engine 1 95,876 Orientation Control I 27.899 Initial Tooling 23.495, Ground Support Equipment 11.678 Test Hardware 80.047 Test Operations 35.082 Training 4,801 Systems Engineering and Integration 22.406 Program tviamgernent 25.177 Facilities 36.284 Total 509.948 -
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/ LOCKHEED MIC. ILLS & SPACE COMPANY IJMSC-Dl53408 Vol IT1
'I'al,lc~.I-%. 111YI'&1' (:OS'I' YOlt L(~/I,II~SINGLE-STAGE, GROUNLI-BASED TUG (W1> 50.2K)
+ Item Cost ($ miI l ions) --- Structure 'r5.832 Avionics (28.998) Guidance and Navigation 16.834 Communications 9.991 Instrumentation 2.173 Power Supply and Distribution (21.01 0) Electrical Power 21 -010 Propulsion (1 34.106) Main Rocket Engine 105 -876 Orientation Control 28,230 Initial Tooling 26.334 Ground Support Equipment 12,677 Test Hardware 81.941 Test Operations 35.559 Training 4.839 Systcms Engineering and Integration 23.355 Program Management 26.444 Facilities 37.083
Total 528.1 78
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LOCKHEED MISSILES & SPACE COMPANY .. --.- I #& REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. -,I/ : . .
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Figure 4-1. Parametric RDTBE Coete for LQ/LH2 Single-Stage, Grd-Bared Tqp
j4-7 : : REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR .,, .
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Figure 4-2. Parametric Avionics, Power and Structure RDTQE Costs, IX)g/LE2 Single-Stage, Ground Based Tugs
LOCKHEED MISSILES & SPACE COMPANY " -- t*- .* - I
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LWC-DlS3408 Vol I11
PROFELLANT KIM1 *LBS0 - . . _____------I- ___ - --
Figure 4-3. Parametric Propulsion RDT&E Coets, %/LQ Silrgle-Stage, Grd t C Baaed Tugs ,409 I-.'"F.- / LOCKHEED MISSILES & SPACE COMPANY I, L ;i REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. "-7 . .
Ngure 4-4. Parametric Floating-Item RDT&E Coets, LQ/LH2 Single-Stage, Ground-Baaed Tugs
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LMSC -Dl53408 Vol I11 42 t 8' 8'
Singk-Stagc LF,,/LII Tug IiLYT& IS Costs -2
This scclion prcsc~ltsRIYI'& E costs Tor singlc-st:&c, ground-l):i.rc?ct, rc8us:1l)lc Slricsc~ 'rugs lllnl usc LP, /LII, ~)ropcllants. A 1n)inl csCim:tCc for lhc IllYl't 11: cost of I.ho on(! L '2 rcbfcrcncc I,Y~/I.~I~'L'ug concc!(d, sizcd at 47, U00 lb propcllnnt Itxding, is l)rc!sc~nt~d ill *ktl~il*4-3.
1br;lrnctric cost d;lliu fur the RVl'OE costs of single-stage LF~/LI~~rcusablc Spacc Tugs arc prcscntcd in Figurcs 4-5 through 4-8. The geileral format of these graphs is similar to the LO~/LI~~series presented in the previous section; that is. the total RDT&E cost curves are given first, followed by detailed parametric breakdowns of the RDT&E cost elements.
0
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( LOCKHEED MISSILES & SPACE COMPANY LMSC -Dl53408 Vol 111
Table 4-3. RDT& E COST FOR LF~/LII~SINGLE-STAGE, GROUND-BASKD 'IVG (Wp-- 47.8K) t l tem Cost ($ millions) Structure 91 -649 Avionics (28.998) Guidance and Navigation 16.834 Communications 9.991 Instrumentation 2.1 73 Power Supply and Distribution (21 .01 0) Electrical Power 21 .010 Propulsion (1 89.563) Main Rocket Engine 161 .334 Orientation Control 28.229 Initial Tooling 23,087 Ground Support Equipment 11.548 Test Hardware 82.835 Test Ope rat ions 35 -342 Tmining 4.857 Systems Engineering and Integration 25.1 64 Program Management 25.959 Foci lities 36.1 81
Total 576.1 93
4- 12 I & :$.,,. _. REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR.
PROPELLAKT I-E IGHT 'LBS*
- - A .- .. - -~ .. .- -- --
Figure 4-5. Parametric RDTQE Costs for LF2/LH2 Single-Stage, Grourd-Baaed Tugm
1 1 ,OCKHEEb MISSILES & SPACE COMPANY pi L 4 REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. 'ad . .
NAV 1 ljA
Figure 4-6. Parametric Avionics, Power and Structures RIYI'QE Costs, LF2/L&4 Single-Stage, Ground-Based Tuge
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IrtuPtLL ANT IEIUIT *L6* .- ---
Figure 4-7. Parametric Prapulaion RDT&E Cwto, LF~/LH~Bipgle~, Grouncl-Baaed Tugs , .. ..,.. : REPRODUCIBILITY OF THE ORIGINAL PnGt IS POOR.L
R b.1 A:E+ E !:ilGT' MISCELLAMI WUSEABLE MX€ Hr DRUI-fPl FI I.&:@ IN CRC~CLLAN~
;-hni'l@1 ti. 1mc~ tRlMRCR OF ENGINES ENlAL I. 144 .PEt ir li IWICF
Figure 4-8, Parametric Floating-Item RDTQE Cooto, LF2/w Singb-8Wg0, Ground-Brured Tug6
/ LOCKHEED MISSILES & SPACE COMPANY LMX! -L)153408 Vol 111
I Single-Stngc FLOX/C 114 Tug RDT&.E Costs 'I'l~iuscction presents HD'I'&l*: costs for eingle-atage, ground-based reusable Space 'I'UKN that usc FLOX/Cllq propellants. A point estimate of RDTt E cost for the one rofcrcncc VC0X/CH4 'rug concept, siccd at 52,000 lb propellant loading, is presented
lhramctric HDT&Lz cost dnh for single-stage reusable FLOX/CH~Tugs are presented in Figures 4-9 through 4-12. These graphs follow the format and sequence used with the L02/LEi2 and L,Fz/ LH2 Tug parametric data (i. e. , total RDT&E costs first, followed by details of the major cost elements).
LOCKHEED MISSILES & SPACe COMPANY 1 " . 3. 'Y .
LMSC-Dl53408 Vol In
Tdle 4-4. R lYl'&E COST FOR ~~U)X/CII~SINGLE-STAGE. GI1 WNlhBASEU TUG (W,; 52. OK) - Item Cost ($ Millions)
Structure 64.204 Avionics (28 998 Guidance and Navigation 16.834 Communications 9 -991 Instrumentation 2.173 Power Supply and Distribution (21.010) Electrical Power 21 .010 Propulsion (1 33.965) Main Rocket Engine 1 05 -876 Orientation Control 28.089 Initial Tooling 21.265 Ground Support Equipment 10.W Test Hardware 72 -918 Test Operat ions 33.983 Training 4.- Systems Engineering and Integration 20.033 Rogram Management 22.233 Facilities 35.61 7
Total 469.728 J -
F ' , j,
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LOCKHEED MISSILES a smce COMPANY r""*P.' i. ' L. .' -, !.&.**& -. . - -'! REPR0,DUClBlLlTY OF THE ORlCMAL PAGE IS POOR^ 4..
LMW-Dl53408 Vol Iff
Figure 4-9. Yarnmetric nDT&E Cost6 for FLOX/CH~Single4tage. Ground-Based l'uge 4- 19
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LMSC -Dl 5340 8 Vol 111
t NIPXlLI< 1'lt 1 Nk.IH', I I1IlC.l I NAV I bA Figure 4-10. Parametric Avionics, Power and Structures RDT&E Coete, FLOX/CH4 Single-Stage , Ground-Based Tugs LOCKHEED MISSILES & SPACE COMPANY ." .' -- .. :*a A BlUCIBILITY OF THE ORIGINAL PAGE IS POOR, LMSC -Dl53408 VO~m MAIN EICIINL Figure 4-1 1. Parametric Propulsion RDT&E Costs, FLOX/CH~Single-Stage, d Ground-Based Tugs 4-2 I. / LOCKHEED MISSILES & SPACE COMPANY L .."f REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. LMSC -Dl55408 Vol 111 Figure 4-12. Parametric Floating-Item RDTBE Costs, FLOX/CH~Single-Stage, (, Ground-Baeed Tugs 4-22 / LOCKHEED MISSILES b; SPACE COMPANY LMC-Dl53408 Vol I11 Stage-And-One-Iisl LO^/^.. 'l'ug ItIYI'L O Costa This s~rtiunprescnts ltW&E cost. lor ground-bas& Sp:rc 'l'ugx using 1.0+/11 lg propcllmts. An HIYl'& 1.: cost point-estimate for a reforcnce stage-:md-onc-half LO /lJll2 'l'ug FUIY.L'I)~ is prcsent~xlin Table 4-5; this concept features n reusable 2 corc shgc of 30,000 \b propellant loading and a set of expendable propellant tanks with totiil propellant capacity of 27,000 lb. Parametric RDT&E cosl data for Lhe drop tanks, only, are presented in Figure 4-13. Applicable parametric RDT&E costs for the core stage are contained in Figure 4-1, previously referenced. LOCKHEED MISSILES & SPACE COMPANY 8 'l'ihl~14-5. IIIYI'ON COST MITI LO~/LH~STAGK-ANII-ONE-HALF, Item Cost ($ Mi llions) Structure (121 .903) Core Stage 83.756 Drop Tanks 38.147 Avionics (28.998) Guidance and Navigation 16.834 Communications 9.991 lhstrumentation 2.173 Power Supply and Distribution (21 -010) Electrical Power 21 .010 Fropu lsion (1 33.741 ) Moin Rocket Engine 105.876 Orientation Control 27.865 Initial Tooling 22.388 Ground Support Equipment 11 -236 Test Hardwore 80.470 Test Operations 36.798 Training 4.809 Systems Engineering and Integration 25.661 Program Management 28.262 Facilities 35.931 Tota l 551.207 - 1 LOCKHEEO MISSILES & SPACE COMPANY + 'I ., A REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. Wi LMSC -Dl53408 Vol I11 WB TAW R.D 1. AME. COST LOX HMROQN PRCPELLANT ZOO00 LBS. Tw7E.T 960 SEC. SPEClFlC IrfuSC Figure 4-13. Parametric RDT&E Coeta for L%/LH~ Drop Tanks 4-2 5 I LOCKHEED MISSILES (L SPACE COMPANY LMSC -Dl53408 Vol I11 'l'h(8 c-osts :~sscw*i:~lcdwith lhc! lnvcstmcnt p11:luc of lhc Space 'rug progr;tm :trc rc*porlcd 1 in illis sc*c.Iion. 'I'llis Invc!stmcnl phasc, which ovc!rlnps lhc ItIY1'&11: pI~:is(*,~I~CIU~CS Ill(. i~equisilionol' vt*hiclcs, l':tcilities, and cquiymcnl nccdcd lo supporl :in owr:ttionirl Siutcc* 'I'ug ssyslc!til. C:o.c.lu spc?cifically included in this phasc comprise rwurring- ~)rcwlucliot~c.xl)cndilurcs Sor lhc acquisition of the reusable 'I'ug fleet and spares; the cxpcndul,lc 'l'ugs, clrop tanks, and their spares; and the facilities, tooling, and GSE abovc and beyond lZI)T&E phase requirements. These costs also include management and support scrvices incurred during the Investment phase. The Investment phase cost data present the breakdown of total Investment costs (as point values nnd parametric data) as well as theoretical first-unit costs. The term theoretical first unit denotes that such values are of use primarily in costing multiple-unit vehiclc buys and have little value aa anticipated unit cost estimates. Learning curve factors used in calculating Investment phase costs werc as follows: 0 Tug core vehicles - 95 percent Expendable drop tanks - 88 percent For definition of the individual WBS entries used in the first-unit cost data, refer to Chapter 2. LMSC -Dl53408 Vol 111 --L%/LH~ Singlc-Stngc 'rug Lnvcstmcnt Costs I'oint cost data for Invc~stmentphasc c,xpnditurcs in IAk/Lllg rcuw:lblc ground-bnscd 'rugs arc presented in Tablcs 4-6 through 4-9. 'I'hcsc coats :trin lor ninglc-sl;~gc*'l'i~gn sizcd nt 3(i, 300 Ib ilnd 50,200 lb propell:ult larding. 'I'nblcs -1-6 4-7 prctsit~ltthtw- rctic:ll firsl-unit costs for the two Tug aizcs, while T:lbloo 4-S and 4-9 prcsctrt t he* tot;ll Invc\slmc*ntpIi;tsc costs for the two point dcsigm. I%ir:~mctric*Invc*stnrcnt cost data for lhc spc~trumof potential ~/LH~single-shgc 'I'ugs arc prc!scntc. LOCKHEED MISSILES % SPACE COMPANY ,\-* - n+Z+T4%- ----.." , 7 L.- . Y- 3 &' ."i::.i.2.,..w ,* ,&&,. :, LMSC-Dl53408 Vol 111 'I'ablc 4-6. FIIST-UNIT COST FOR ~/LH~SINGLESTAGE, GROUND-BASED TUG (W, - 36.3K) l tern Cost ($ millions) Structure (Including Insulation and Propellant Feed) (3.1 68) Core Stage 3.1 68 Drop Tank 0.000 Avionics (8.41 9) Guidance and Navigation 5.524 Communications 1 .995 Instrumentation 0.900 Power Supply and Distribution (2.371 ) Electrical Power 2.371 Propulsion (1.338) Main Rocket Engine 0.406 Orientation Control 0.932 Integration, Assembly, Checkout and Test 0.714 Tota I 16.01 0 Table 4-7. FIRST-UNIT CWT FOR LO~/LH~SINGLE-STAGE, GROUND-BASED TUG (W, = 50.2K) ltem Cost ($ millions) Structure (Including Insulation and Propellant Feed) (3.470) Core Staw Drop Tanks Av~onics Guidance and Navigation Communications lnstrumentation Power Supply and Distribution Electrical Power Propulsion Muin Rocket Engine Orientation Control Integration, Assembly, Checkout and Test L--.- Total 1 16.389 1 LOCKHEED MISSILES & SPACE COMPANY Table 4-8. INVESTMENT COST FOR q/LH2 SINGLESTAGE, GROUND-BASED TUG (Wp- 30.3K) '?- Itern Cost ($ miI I ions) J Reusable Fleet Cost (14 Tugs Plus Initial Spares and Support) 235.044 Expendable Hardware Cost (468 303) Expendable Tugs (64 Units Plus Spares/Support) 468.903 Drop Tanks (0 Sets) 0.000 Facilities and Equipment 22.458 Total 726.405 1 I tem Cost ($ millions) Reusable Fleet Cost (17 Tugs Plus lnitial Spares and Support) 31 2.275 Expendable Hardware Cost Expendable Tugs (14 Units Plus Spares/Support) Drop Tanks (0 Sets) Facilities and Equipment LOCKHEED MISSILES & SPACE COMPANY -. .. 1 " REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. w,. .-.,-. * . LM8C -Dl59408 Vol UI F ik: e 4-14. Parametric Nrat-Unit Costa for Rewable Veraionu of LOBhgZ Single-Stage Tugs LOCKHEED MISSILES & SPACE COMPANY ,. ,. I i REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. *,,, LMSC -Dl68408 VO~m { LOCKHEED MISSILES & SPACE COMPANY Figure 4-16. Parametric Investment Costa for Reusable Verelm of LO.,/LHg Single-Stage 'i'-lgs / LOCKHEED MISSILES & SPACE COMPANY LMSC -Dl53408 VOI m LES Figure 4-17. Parametric Investment Costs for Expendable Veraions of L%/- Si~gle-StageTug8 433 LOCKHEED MISSILES & SPACE COMPANY LMSC-Dl53408 Vol 111 --~F2/L11~ Singlc-Sktgc 'I'ug Invustmcnt Costs Point investment-cost data for ~~LF~/LH~reusable ground-basedlug sized at 47,800 Lb propellant Loading arc presented in Tables 4-10 and 4-11. Table 4-10 colltains the thcorclic:tl first-unit costs for this Tug while Table 4-11 presents the total Investment phnsc cxpnditurc rcquircments. L I R1r;trnctric data on thc Invcstrnent phase costs of single-stage LF~/LH~Tugs are I l presenttd in Figures 4-1 8 through 4-21. Curves of first-unit costs for reusable and ! expendable versions of thc LF~/LH~Tug are given in Figures 4-18 and 4-19, respec- tively; total Invcstmcnt costs for thcse same two versions are graphed in Figures 4-20 :lnd 4-21. LOCKHEED MISSILES & SPACE COMPANY LMSC -01 53408 Vol 111 7':1I,lc 4-10. FI1WI8-UNIT COS1 FOR LI?~/L~I~SINGLE-STAGE, GROUND-BASED TUG (W,-: 47.8);) ltem Cost ($ millions) Structure (Including Insulation and Propellant Feed) (3 -498) Core Stage 3 -498 Drop Tank 0.000 Avionics (8.41 9) Guidance and Navigc~tion 5 -524 Communications 1 -995 Instrumentation 0.900 Power Supply and Distribution (2.371 ) Electrical Power 2.371 Propulsion (1 -432) Main Rocket Engine 0.487 Orientation Control 0.945 Integration, Assemb ly ,Checkout and Test 0.847 Tota l 16.567 .. - - Table 4-1 1. INVESTME NI' COST FOli LF2/L~2SINGLE-STAGE, GROUND-BASED TUG (Wp= 47. SK) ltern Cost ($ millions) Reusable Fleet Cost (1 7 Tugs Plus Initial Spores and Support) 327.977 Expendable Hardware Cost (1 7.81 2) Expendable Tugs (2 Units Plus Spores/Suppori) 17.81 2 Drop Tanks (0 Sets) 0.000 Facilities and Equipment 22.272 I Total I 368.061 I LOCKHEED MISSILES & SPACE COMPANY -., . "'7'rn" .AT--*,? " llsra fl q* -q HYclliiCCN FLI4RlNE PfiLt5LCIN1 474.4 SEC ~PECIFliIP;PCCX Figure 4-18. Parametrir "'ret-Unit Goth for Reusable Verelons or LF~/L%sitgie-stage nyl~ LOCKHEED MISSILES 8. SPACE COMPANY I-.--..--. . . ,-a, i THE ORIGINAL PAGE IS POOR. EXPENDABLE WXE HYCV~YCNFLLURIM PRWCLLANI IWEER 1jF EwINS EIXlAL I. 979.4 Xi. CfiCIFIC IWlCSE Figure 4-19. Parametric Firsbunit Coat8 for Expendable Version6 uf LF~/L%single-stage 'rugs I LOCKHEED MISSILES (L SPACE COMPANY L UmIk@l:7GINALPAG~ IS POOR 30 VEHICLES .'I1 Vf ti1iLf.C; Id VEHICLES I VEHICLE F lgur e 4-20. Parametric Inve8tment Coeb for Reueable Vere ion6 of LF2/LyL Single-Stage Tug6 I LOCKHEED MISSILES & SPACE COMPANY VEHICLES b'RcPELL ANT rX l'.Hr 'LPS* ------. - .---.- -. Figure 4-21. Parametric Investment Costa for Expendnble Version. of LFa/LE2 Single-Stage Tugs / LOCKHEED MISSILES & SPACE COMPANY - .m-+, ,. ,. ' ~~~~:~~!~l~l~l~~I~~~ ., . . ORIGINAL PAGE IS POOR. : LMSC -Dl53408 Vol 111 FLOX/C H4 Single-Stagc 'I'ug Invcstmcnt COBts _^.- -_- . --- Point Investment-cost data for a FLox/CI~~rcuenblc ground-based tug sixcvl a1 92.000 11, propcllmt loading are prcsontcd in Tables 4-12 .and 4-13. Tdlc 4-10 conhins lhc. thcorctical fi rst-unil costs for this Tug while Tablc 4-1 :1 presents the total Inveatmcnt phase cxpcndi turc rcqui rcmcnts. Parametric data' on the Investment phase costs for single-stage FLOX/CH~ Tugs are presented in Figures 4-22 through 4-25. Curves of first-unit costs for reusable and expendable versions of the FWX/CH~Tug are given in Figures 4-22 and 4-23. re- spcctivcly; the total Investment costs for these same two versions are graphcd in Fibwrcs 4-21 and 4-25. 4-40 LOCKHEED MIE31LES (L SPACE COMPANY LMSC -Dl 53408 VO~rn T:\blc 4-12. FIRST-UNIT COST FOR FLOX/CH~SmGLE-STAGE, GROUND-BASED TUG Cost (5 millions) Structure (Including Insulation and Propellant Feed) Core Stage Drop Tank Avionics I Guidance and Navigation I Cornmunica tions I Instrumentation Power Supply and Distribution Electrical Pows Propulsion I Main Rocket Engine Orientation Control Integration, Assembly, Checkout and Test Total Table 4-13. INVESTMENT COST FOR F'LOX/CH4 SINGLE-STAGE, GROUND-BASED TUG (W, = 52. OK) Item Cost ($ million) Reusable Fleet Cost (1 7 Tugs Plus Initial Spares and Support) 281.596 Expendob le Hardware Cost (58.085) Expendable Tugs (9 Units Plus Spores/Support) 58 .085 Drop Tanks (0 Sets) 0.000 Facilities and Equipment 21.257 Toto l 360,938 i LOCKHEED MISSILES & SPACE COMPANY IM17 COSTS REUSEIBLE HUX FLOX %THANE PROPELLANT 20000 LB5 IHtUST NWSR Of ENGINES EWAL I . r14.0 XC.SPECIFIC IPPUSE PROPELLANT 1IE !GI41 'L85. FWe 4-22. Parametrlo FlrsbUntt Corn for Rrulblo vOr8bIU of FLOX'CH* Single-we 4-42' LOCKHEED MISSILES & SPACE COMPANY WIT COSTS EXPENi4R.E rYXX FLOX KTHAM PRYELLANT ZOO00 LfrS. TWal WSROf ENGIFES EQUAL I 919.0 KC. SPEClClC IrPUY ** FIRST UNIT SYS INTClVEW ELECTRICAL W AVIONICS Figure 4-23. Parametric Flmt-Untt Co8to for Expodable Verelau of FLOX/CH4 81ngle-Stage Tug6 / LOCKHEED MISSILES & SPACE COMPANY .- --&. - , ,*- -.,.. . &. f. REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. t REUSEARE KflC FLOX W.THAN PROFfLLINt MMSh OF EMGlNES ECUAL I r1h.o SEC. SPECIFIC IWY VEHICLES VEHICLES Figure 4-24. Parametric Investment Cat8 for Reurrble Ver8io~of FLOX/CH4 Single-Stage Tug6 / LOCKHEED MISSILES & SPACE COMPANY -., , . - A I1#T THE ORIGINAL PAGE IS POOR. t.- EXPEWABLE rUOC MPI)EH OF ENGINES EOUAL I Figure 4-25. Parametric Iaveetmsnt Codbr Eqmdnble Verrioar of FLOX/CH( SiWe-8ty. Tu(* / LOCKHEED MISSILES & SPACE COMPANY - LO^/ - LH,, Stage-and-One-Half Tug Inve8tmcnt Co8.t. The point coat data m lwestment phase expemdlture requlremeat. for an LO~/L% swc-and-one-half Tug eized at 30,000 lb core-stage and 27,000 Ib drop-tank prope! - lant weight8 arc presented in Tables 4-14 and 4-15. Table 4-14 containe the theoreti- cal flret-unit costa for thls Tug while Table 4-15 presents the total Investment phnse expenditure requirements. Pammotric date on the Investment phrse corts of the expendable W2/L3 drop-tank set are plotted in Figurcs 4-2C and 4-27. Figure 426 grt+,.:m the first-unit coats over a range of ~lzeefrom 8000 lb to 26,000 lb propellant; Flgure 4-27 presents the curvee of total Investment coat over the eame elze range. LOCKHEEO MISSILES & SPACe COMPANY LMSC-Dl53408 Vol 1h1 'l'd~le4-14. FIItS'r-UNIT COST FOll L02/LH2 SFAGE-AND-ONK HALF, GROUND-BASED TUG (COIIE W, = 30K) Cost ($ Millions) Structure (Including Insulation and Propellant Feed) Core Stage Drop Tank Avionics Guidance and Navigation Communications Instrumentation Power Supply and Distribution Eiectrica l Power Ropulsion Main Rc . " Engine Orientation Control Integration, Assembly, Checkcut and Test Total Table 4-15, INVESTMENT COST FOR L02/LH2 STAGE-ANDONE-HALF, GRTIUNIbBASED TUG (CORE W, = 30K) Itern Cost ($ Mi l lions) Reusable Fleet Cost (1 6 Tugs Plus Initial Spares and Support) Expendable Hardware Ccrt Expendable Tugs (1 Unit Plus Spares/tupport) Drop Tanks (236 Sets Plus Slxlres/Support) 23.962 Facilities and Equipment 21.821 C Toto l 357.61 4 LOCKHEED MISSILES & SPACE COMPANY I ,. , ,. , -. ,A L. REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. ; LMSC-Dl53408 Vol 111 Figure 4-26. Parametric First-Unit COB~for -/LA2 Drop Tanb 4-48 LOCKHEED MISSILES & SPACE COMPANY -- - .--- - -.. .-t 4 1C' REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. W(P lllY lNKSllENT Cost LOxmWWO(PRlRLLANT 20000 LBS. TH*15. W SEC. SPECIFIC I-% 9ETS SETS YTS SET PROPELLANT EIGHT *LBS* Figure 4-27. Parametric Investment Coats for LO~/LH~Drop Tank6 4-49 LOCKHEED MISSILES & SPACE COMPANY Ol'lf IU'I'IONS COSTS Thc costs associated with maintaining a reusable Space Tug program through its twclve year operational phase (1979 - 1990) are reported in this section. The Operations phase includes all activities associated with preparing the Tug for launch (handling, checkout, fueling, countdown); all actidtias associated with flight of a reusable Tug (mission control, recovery); and all activities associated with reusable Tug refurbishment (inspection, repair and replacement of hardware as necessary, pcriodic major ovcrhaul, and spares provisioning). The Operations phaac also includes ksc management, direct range services, and facilities/cquipmcnt operation and maintenance. Important assumptions made in estimating Operations phase costs Were as follows: The costs of Government manpower and equipment for mission control, tracking and data acquisition were omitted a Tug operations were assumed to take place at two sites, namely ETR and WTR For definition of the individual WBS entries used in the Operatious costs, see Chapter 2. LOCKHEEO MISSILES & SPACE COMPA, 1- LMSC-Dl53408 Vol TIT LO /LH, svrations Coste -9 - .- - Point-co~tdata for Operations phmc expenditures with I~02/LH2reusnblc ground-based 'I'ugs arc pri~scntcdin Tablcs 4-16 and 4-17. Those costs are for single-stage Tugs sizccl at :l(i,300 Ib and 50,200 Ib propellant loading, respectively. Parametric data on LO~/LH~single-stage Tug operations costs are presented in Figures 4-28 through 4-31. These graphs cover selected activity-level-dependent elcmnts of Tug operations only. Figures 4-28 and 4-29 comprise plots of follow-on spares costs as a function of propellant loading for reusable and expendable versions of the LO~/LH~Tug, respectively; these are calculated on a total cost basis. Figures 4-30 and 4-31 are curves of other key Operations costs as a functiqn of activity level; these are plotted on a cost-per-flight basis and are for rcusable and expendable versions of the LF~/LH~Tug, respectively. LOCKHEED MISSILES & SPACE COMPANY -..-...- - -____. -____ I -- ' Table 4-lti. OPERATIONS COST BREAKDOWN Mm LO~/LH~SINGLU-STAGE, GROUND-BASED TUG (W, = 36.3K) Item Cost ($ Millions) Launch Operations and Services (493 bunches) (186.599) Launch Operations 110.487 RopeI Ian ts 1 369 Facilities and Equipment Maintenance 7.007 Engineering Support 27.000 Program hnagement and Integration 27.000 Range/&lse Support 13.536 Flight Operations (415 Reusable Tug Flights) I (22 -352) Communications and Control Replacement Training Recovery Operations Refurbishment (401 Refurbishment Cycles) Vehicle Maintenance Fol low-on Spares Transportation Cost (51 1 Shuttle Flights) 2,555.000 Toto l 2,968.669 LOCKHEED MISSILES & SPACE COMPANY I.. Y: " 1. ,":&,< : ,, . >i*;*. LMSC-Dl53408 Vol In T:hlc 4-17. OPEltATIONS CO!W BREAKLYlWN FOR L02/Ln2 SINGLE-STAGE, GROUND-BASED TUG (Wp = 50.2K) 1 ltern -.Cost ($ Millions) Launch Operations and Services (51 9 Launches) (194.147) bunch Operations 1 16.731 Rope Ilants 2,274 Facilities and Equipment Maintenance 7.606 Engineering Support 27.000 Program Management and Integration 27.000 Range/~ase Support 13.536 Flight Operations (488 Reusable Tug Flights) (22.568) Communications and Control 6.768 Replacement Training 14.517 Recovery Operations 1.283 Refurbishmer rt (471 Refurbishment Cycles) (240.557) Vehicle Maintenance 45.1 82 Fol low-on Spares 195,375 Transportation Cost (562 Shuttle Flights) 2,810.000 Tota l 3,267.272 b LOCKHEED MISSILES & SPACE COMPANY -....,. -* REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR.-'a. FIXLI'IW 1'54 SPARES C :#ST ff R FL li.ttT HEUyF AF' E FlOClE 20000 LB'; THRL5: NLtIElf H OF LNGINE5 EQIIAL I . 'S 'ARE 'ARE:s Figure 4-28. Parametric Follow-on Spares Costs for Reusable Lo2/LH2 Tugs I 9CKHEED MISSILES 91 SPACE COMPANY - -. .. . ,--.-... , L REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. ; I l(Jl Al. 'PARES** 'HER WBSYSlEnS EWINt. 'PA URE SPARES Figure 4-29. Parametrio Follow-on Spare6 Coeta for Expendable LO~/LH~Tugs I ,OCKHEED MlSSlLYS & SPACE COMPANY '- REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. : HL lv.X ARLE M3UE NOIEKR LX EM,INCG €131lAL 1 . VEHICLE llAlNTENANCE IfY. EQIIP. PUlNlEWNCC MI AM CONIROL ERI' *eCRAl IN NCMXR Of FLIGHTS PER YEAR - -- . ------.- Figure 4-30. Parametric Opentiow Costa for Rauable L02/LH2 T'ugo REPRODUCIBILITY OF THE ORlGlNAl PAG~ .M;I@@ .. ,- 4 "U t f I C Figure 4-31. Parametric Operatione Cortr ior EXpandrble LO2/W2 f LOCKHEED MISSILES & SPACE COMPANY I -LF2/LII -2 Singlc-Stage Tug Ope rations Coste Point-cmst data for tho qxtratione phase expenditure roquircmcnts with a reusable ground-h~edLF~/LI~~ Tug sized at 47, ROO lb propetllant loading are presented in Tablc 4- 18. Thcse costu reflect the added complexity of operations required with LF2 oxidizcr (comparcd to LOZ), as well as the added cost of the propellant itself. Parametric data on Operations costs for reusable and expendable versions of the LF2/LI12 single-stage Tug are graphed in Figuras 4-32 through 4-35. Figures 4-32 and 4-33 plot total follow-on spares coste ae a function of Tug size. Figures 4-34 and 4-35 plot the cost pcr flight of key Operations activities ae a function of the annual launch rate, LOCKHEED MISSILES 6 SPACE COMPANY 1 LlMSC-Dl53408 Vol T*! T~blc4-18. OPERATIONS COST BREAKDOWN MI13 LP2/LH2 SINGLE-STAGE, GROUND-BASED TUG (W, .- 47.8K) Cost ($ Millions) ------launch~~ektionsand Services (51 9 bunches) launch Operations Rope I Iants Facilities and Equipment Maintenance Engineering Support Rogram Management and Integration Range/~ase Support Flight Operations (500 Reusable Tug Flights) Communications and Control Rep lacement Tm ining Recovery Operations Refurbishment (483 Refurbishment Cycles) Veliicle Maintenance Fo! low-on Spares Transportation Cost (535 Shuttle Flights) Tom I LOCKHEED MISSILES & SPACE COMPANY 1 'z REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR Mmi Figure 4-32. Parametric Follow-cm Spare6 Coeta for Reusable LF~/LH~Tugs I LOCKHEED MISSILES & SPACE COMPANY : .~ REPRODUCIBILITY OF THE ORIGINAL FAGL IS POOR. T Fl.,are 4-33. Parametric Follow-on 8pm-ee Costs for Expendable LF2/La Tuge I LOCKHEED MISSILES & SPACE COMPANY VE!il~.if HAINIFtJANI ItY, LiA*IP. MA NS haiONTROL CRY WERAT IONS H OPERATIWS r&?!ER cY FL?C+iTS PCR YEAR .- .- _. Figure 4-34, Parametric Operations Costa for ReUdle LF2/LH2 w . * :~~~:~~1~1Ur(Illl~~b~~~~~~OR IGlNA L PAGt I S POOR ~&?'L NUrBER CC FLIGHTS PER YEAR -...---.------ Figure 4-36. Parametric Operatiom Costa for Expsa-10 LF~/T.~H~l\lr* b I am-a-n ncrc~tre PAP^ COMPANY FI,OX/C 1 Si nglc-Stage Tug @orations Costs -- -.- -. -.. ..-- Point-cost data for the Operations phase vxpenditure requirements with a reusable ground-based FL0X/CI14 l'ug sized at 52,000 lb propellant loading are presented in Table 4-19. Thesc costs reflect the added complexity of operations required with FMX/CHq propellants (compared to L%/UiZ ) as well as the added cost of the propellant itself. Parametric &ta on Operations costs for the reusable and expendable versions of the FLOX/Cli4 single-stage Tug are graphed in Figures 4-36 through 4-39. Fiyres 4-36 and 4-37 plot total follow-on spares costs as a function of Tug size. Figures 4-38 and 4-39 plot the cost per flight of key Operations activities as a function of the annual flight rate. 4-64 LOCKHEED MISSILES & SPACE COMPANY .- LMSC-Dl53400 Vol 111 Td)Lt! 1-19. OPEllATIONS COST BREAKDOWN FOR FLOX/CH~ SINGLE-STAGE, GROUND-BASED TUG (W, = 52.OK) Cost ($ Mi llions) (506 Launches) (235.570) hunch Operations Prope Ilonts Foci lities and Equipment Maintenance Engineering Support R ogram Management and lntegmtion Range/~ase Support I Flight Operations (480 Reusable Tug Flights) Communications and Control Replacement Training Recovery Operations Refurbishment (463 Refurbishment Cycles) Vehicle Maintenance Fol low-on Spares Transportation Cost (522 Shuttle Flights) 2,610.000 Tota l 3,105.002 1 LOCKHEED MISSILES & 'ACE COMPANY -- v'T. REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. I,: 1 Fr*.LW U1 SPAHLS (051 PER FI-ICHI REUSEABLE tOOE FLOX I'€THANC WW)PELLANT ~0000LBS. TWJl MneER OF ENGINES EWAL I. r1v.o SEC. SPECIFIC IWSE llAL SPARES'. I S;BSYSTEr(S SPARES T ENGlb" SPARES TLRE spas PROPELLANT WEIWT *LBf* .. - . -. - Figure 4-7%. Parametric Follow-on me6 COB~for Reusable FLOX/CH4 Tqp I LOCKHEED MISSILES & SPACE COMPANY -. 4 REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. m fOLLW 134 SPARES ':9ST RR FL ICHT 2OUOO LBS. THWST 'U SPARES" Figure 4-37. Parametric Follow-on me8Code for Expendable FLOX/CH~Tug8 I LOCKHEED MISSILES & SPACE COMPANY ACTlVllV LEVEL DtKNXNT COSTS REVSCARE ROC€ FLOX MTWH PRWELLANT 9Ib.O SEC. SFECIFIC IWSE VEHICLE MAINTOUWE FACILITY, EQUIP. WIWXMMC I t Figure 4-38. Parametric Operation@Coat8 for Rewable MX)X/q 4-68 f LOCKHEED MISSILES & SPACE COMPANY (Rl. ACTIVllY LEVEL DEPENICNT COSTS EXPEHMaE KIOE FLOX MTMH RmLLANT OF FLIWTS PER VEAR Figure 4-39. Parumtrio Op@&iOIU Corm bor FWCHI Tugr -t4O2/I41I2 -. ------Stu~0-ttnd411~-lldt Tug Qxrations Coete 'I'ho point coats for qwratione phase oxpunditare requirements with a stage-and-one- half 14/L1l2 Wcc Tug conccpt are presented in Table 4-20. Thcse costs arc for u concrvt with a corc-stago propellant loading of 30,000 lb and a drop-tank prqml! *.;ri loatiing of 27,000 Ib. elro LOCKHEED MISSILES 6 SPACE COMPANY I II ' -1-- t 1tem Cost f$ Millions) launch Operations and Services (496 Launches) (1 86.790) Launch Operations 111.205 Rope IIan ts 1 .308 Facilities and f quipment Maintenance 6.741 Engineering Support 27.000 Program Monugement and Integration 27.000 Range/bse Support 13.536 FIight Operations (479 Flights with Core Stage Reuse) (22.475) Comrnunicat ions and Control 6.768 Replacement Training 14 -428 Recovery Operations 1.279 Refurbishment (463 Core Stage Refurbishment Cycles) (233.661 ) Vehicle Maintenance 44.776 Y, Fol low-on Spares 188.885 Transportation Cost (628 Shuttle Flights) 3,140.000 -i Tota l 3,582.926 .t3 ,? 4 :4 9 "-8 k" gd .. - .I. .a: .* . , -t. En i. - Iic: t* . . .I i : REPRODUCIBILITY OF THE ORIGINAL PAG~IS POOR *-- .. LMSC-Dl53408 Vol nI 'IqL!funclir,g rcxpircrncnts, by fi~cillyear, of n reusable to2/Ll12Space Tug (50.200 lb propcll;tt\t loading) are graphed in Figurc 4-40. This figure was presented to typify thc cqtenditurc yattcrt~of thc cntirc clasu of rcu~ableTugs. Thc funding curve! wno dcrivcd using dcvclopmcnt nntl proct~rcmcntsp;ll; data (c.g., 5 vcars for ItIYI'RrK) in combination with standard etati stical spread functione. No smoothing c)f lhi- cqn8ndi- turcs was pcrformcd. 'I'lrcac coats include only 'I'ug expendittires (Itl)'l'&lS, Invv~t- mc!nt, Op~~.;rtions);Shutllc uncr fc*cs ancl pt~ylwrlcoats wcrc ~p~cificrtrllyr~xclui~cd. 'I'his c#hunu-tcri~ti<.rcunablo-'l'ug funding curve fcuturr*~:l ~)c.~kin ft~ntlingduring thc c*:~rly~C(LI~ (FP 1975 - 1079) pcimrily caused by ltD'I'&IS cxpcncliturcs untl sccondorily by Invosttncnt phasc rcquirc.mcnts. l%e magnitude of thc peak year requirement ex- cceds $200 million, The RDT&E component of this funding can be alleviated slightly by a vigorous program of supporting research and technology in the FY 1973 - 75, and can be further decreased by accepting lower Tug performance (e, g., no retrieval capability; storable propeliantsl. However, no appreciable reduction in the early- year peak can be achieved wi aout phased introduction of the reusable Tug and uee of thc orbital injection stage for early operational missions. Once thc operatiot~alphase of the reusable Tug program arrives, funding levcle clcdinc to juat ovcr $50 millior. per ymr. This bfficicncy in operations limit6 totill 'I'ug c!qcl,cmiiturcu to $1.4 1 billion, in c:ontrnat to $1. (i4 billion for the rnont compctitivc orhit injccalion sbgc. 41-72 / I nC,KHEED MISSILES & SPACE COMPANY IaMS(!-I 1153408 Vol U1. 74 76 78 80 82 04 86 88 90 FISCAL YEAR I 1 nP1+HEFT)MISSILES & SPACE COMPANY L ' REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR .aP', I,MSC-D15:14OH Vol 111 Chapter 5 PAY LOAD COSTS AND CHARACTER1ST1 CS This final chapter in Volume III presents cost data - and other important character- istics - for the unmmctl spacecraft delivered by the Space Tug system. The organi- zntion of Lhis chaplcr is as follows. First the overall approach to payload costing is rcvicwd to cstal~lisha basis for the estimates that follow. Then the contents of the data shects that makc up lllc p~yloaddata bsc are dcscribcvl in detail to guidc thc rc;ulcr in interpreting lhis information. Finally the actual payload data shccts for ~uostof the unmiinn~dspxc~raft in the mission model are prcscntcd. This informa- Lion c-overs NASA and applications-agency progr:ims only; Ihl) paylo:i(l r:\incxi in :\ scpnr:~lccl:issificul :ippcndix (limilccl distr~hution). 'rhc shrtilrg point in thc paylad cost analysis was a mission modcl comprising 64 programs (-483 spacecraft placements) that was supplied to Lockheed by NASA. This modcl was limited to those missions for which a Tug is potentially required; hence it excluded low-earth-orbit spacecraft directly deliverable by the Shuttle alone. User agencies represented in the model were NASA (both the Office of Space Sciences and the Office of Applications), the Ilepartment of Defense, and various non-NASA appli- cations agencies. Data included with the model (augmented by Aerospace C~rporation results from the STS Economic Analysis study) also provid~dthe orbital parameters, sizes, weights (by subsystcm), powcr requirements, and flight schedulcs for all of the biisclinc piy1o:lds considcrcvl in the mission modcl. Thc cosb for Lhcsc hsclinc p~yloadswcrc lhun calcultlled using a lxlrtlmclric ccmt methodology applied against the spacecraft weights and characteristics. The cost es- timating relationships used to perform these computations were historically-derived curvrs of cost ns a function of technical characteristics (primarily weight) for the f princip~lsubsystcrns of unmanned spacecraft. The resulting baseline payload costs LOCKHEED MISSILES & SPACE COMPANY - REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. .I I: *-.n*rransr^ ..- . A . . . - .+ .--. .- ..------. ..- '.* .% .+ '" a -. - w LMSC- 1)153408 Vol 111 wcrc chcckccl against comparable cstimatos dcrivcd by Acraspacc Corporation in the S1'S Kconomic: Analysis study and found to be in agrccrnent. Ilaving eshblish~dthc bqselinc spacecraft costs, the final step in thc payload costing task w:w to dcvclop algcrithms to express the cost savings possible with Space Tug systcms. ILi-scd on the work performed by Lockheed under the original Payload Effects .4n:tlysis stucly (NASw-2 156) tllrce classes of payload cost savings were idcntificd for tllc 'rug, ~xtm~ly: e .Mnss/Volunlc: ...... - These arc the savings possible when payload weight and volumc capacity (in excess of baseline rcquirernents) are availahlc, and low-cost fab- rication techniques can be used because of the relaxed design tolerances. a Rkyimd Retrieval and Reuse: These are savings achieved when a spacceraft retrieafrofirbit is refurbished, experiments are replaced as needed, and the swcecrafL is returned to operational service (in lieu of purchasing a new unit). -Accessibility: Thcse savings, formerly called risk acceptance, arise from the fact that less testing (both RDT&E and acceptance) can be allowed for spacc- craft that arc 3ccessiblc for repair in case of failure on orbit. The savings attainable with each of these three effects were quantified in the form of cost and weight estimating relationships, and other algorithms. These were automated into the logic of the Lockheed STAR/ANNEX program in such a way that appropriate low-cost spacecraft estimates could be generated as required by the available payload capdility of a given Tug in a given mode. PAYLOAD DATA This section contains data on the costs and characteristics of the unmanned payloads. This information is arrayed on data sheets (one sheet per payload). Following is an explanation of the payload data sheets. The payload data sheets for all spacecraft except the DoD programs are presented in Tables 5-1 through 5-48. These are arrnngcd in numerical order in acc~vdancewith their assigned number in the reference mission mudel. Thcse shccts contain all of the mission and cost (I:\t:k neccss:lry to compute .md spread all of the c~stincrt?ments of one program from thc mission moclcl. The data are grouped into blocks, details of which are given below. 'I'hc major blocks C:, are as follows: 5-2 I 1-OCKHEED MISSILES & SPACE COMPANY e Mission identification o Mission definition a Acccphblc mission modes .. Schedule of all cost producing cvcnts [.isling of weights and costs Miscellancwus cost and wdght parameters Cost spretld parameters and misccllancous data The contents of each of these blocks is as follows: 1 Mission uen~~ficatiok.This gives the mission number in the so-called Fleming model of March 1971 and the mission title. The subfield is provided to allow for variance within a mission, such as sending the same payload to a variety of orhi ts. --Mission Definition. 'I'his lists the final orbit into which the payloacl is to he 0 placed, the AV required (above the velocity in a circular orbit at 100 nm), pay- load life, and the number of active payloads required. The payload dimensions and density are for the baseline payload, before application of payload effects and repackaging; these dimensions are taken from Aerospace Corporation data. .Acceptabte Mission Modes. This lists the possible payload modes (expendable or retrievable) and Tug modes (round trip placement and retrieval in one flight, placement only, retrieval only, expendable Tug) and states which modes may be used for the qubject mission. -.hchedule. The first two lines of the schedule arc for expcndahle payloads and arc t.a1.<:nfrom thc mission model. 'Ihe launch schc~lulealso applics to payload placement when the payload is retrieved and refitrl~ishcd(in the pl-cscnl study only refurbishment on the ground was considered). The retrieval schedulc was developed by LMSC during the study; it is designed to minimize new buys and also to permit combinations of placement and retrieval on one flight as far as possible. The resulting new-payload acquisition schedule for a retrievable pay- load Is then shown. The schedule of new-experiment RDT&E, for these cases in LOCKHEED MISSILES & SPACE COMPANY ..I"----.-.-r - . - ,,.'C...i_ ... + *- --- my , .'., " , <., J . LMSC-Dl53408 Vol III i whicbl~tl~i* c~spc~i.in~~nt is r:h:tngc?d rtvory few y cars, is Liken ftwm Ac*l.osp:lcc* ('or- E pomticw :~n:~lyscs.'L'hnt part of opc~utionncost nslsociativt with orl~it:ll eupp11-t. i indt?cndcnt of launcll rate, is applied in every j,e:3.:1r in which :tn :~sli\riskis sho\v~l. I k Weight and Cost Parameters. Weights and costs are listed here by subsystem. These data are derivccl as follows: Uqseline Weight From Aerospace dab. bwCost Weight From weight estimating rclationships (WERs) developed by LMSC from results of Payload Effects Study, for full application of low-cosl techniques. Baseline Costs From LMSC cost estimating relationships (CERs) Low Cost From LMSC CERs based on results of Payload Effects Study, for full application of low-cost techniques. The sub-heading Risk denotes application of accessibility savings (formerly 0 called risk acceptance) in which a cost reduction is made, at constant total mis- sion reliability and confidence, because it is possible to check out a payload after placement and bring it back if it has failed. No Wsk denotes costs when this effect is not applied. The factors in parentheses hcsidc the cost ta1)ulations for experiments, stnlctures, and electrical power allow for complcxity in thcsc subsystems and are applied to the costs derived from the CEHs for a complexity factor of unity. The ratio of inert weight (less propellants) to total weight was maintained constant at the factor shown, and the propellant weights were computed accordingly. The "minimum weightsware stops to prevent the payload weight from ever going below the baseline weight for the expendable mode, or going below the baseline weij&t (as modified by providing refurbishability) for the retrievable mode. The weight increment for refurbishability is shown on the third line of the first column; it is derived from an LMSC WER and applies to either baeeline or low-cost payloads if refurbishable. It results from spacecraft design modularization and hardware provisions for retrieval (e. g. , rendezvous/docking equipment). Pruvis ion w.w c, made for fixing Ihc weight of some subsystems (filth line, sc!coml cwlumn) when it / LOCKHEED MISSILES & SPACE COMPANY LMS('-l)l5J.IO8 Vol UI w:~sk*11 l11:11 low-c-osl. loc!hniclucs worc no1 :q)plic::d)lc. '1'11~ low-c:osl p:lvlo:ltl wcbipj~t inc.littltltl ~)l'ovihit111 for ~.cCit~~l)ixl~:ll)ilily([or IliaLori c::ll t.c:~aons). In ol.tltkr lo ink r.- ~)ol:~lt*(for o:lt.li:kl :~l)plicalionof cost t.cduc:tion will1 weight incrr!:lsc) thr! wciglit c:h:mgc'c!s duc lo low-cost lcchniqucs only, the factor &/c- B/L - IC ICY (L/c)), which rc.prc!scnts this inc re we, was computed. 'Chc accessibility snvings (i. e. , Risk Acceptance) were applied i~.full to rc- trievnblc payloads. For expendable payloads, which could still be checked out after reaching low earth orbit but before placement by the Tug, 40 percent of the full savings was applied (third column). Cost Spread Parameters and Miscellaneous Data. These entries are largely self explanatory. The duration of the R&D phase (or phases, if new-experiment R&D is required) and the investment phases (purchase of new units), and their spread-function shapes are given. The launch-rate-dependent operating cost is that associated with a launch and is applied in the years of hunch. The launch-independent costs listed are per-year per-vehicle active on orbit, and are applied as shown in the schedule. The Fixed Portion Initial Investment (usually zero) provides for addi+ional ground facilities if required by the mis- sion. I'rovision was mndc (but not used) for retrieving less than 100 pcrccnt of the plnced p:tylond wcnight. l'hc Cost Confidencc cntry is u sul~jcqlivccvnlua- lion of thc v:tlitlity of thc cost data. 5-5 / LOCKHEED MiS51LES & SPACE COMPANY Table 5-1. I'ASLOAD COSTS AND CEIARACTERISTICS FOR MISSION NO. 2 MISSION FL~W~~G~UUBLRI 2 ~UIC~ELOI 0 NAHEI RIOIO ASTRONO*V EXPLORE@ 0. mlSS10N 1 CAYLOIO DATA 0. nISSION CCUE ~LRBEAI MISi4I 0. IIASEL~NE4 LOU COST) 0. ~~CLINATICNI28150 OEOAEES ODBITI 1912JWiC) / 19128WlA) ~VI 12959. FT/SEC AVERAGE POUERI 180, WATTS LIFE) 3 3 VEARS SIZEI DIAMETER 5,o rt. LENCTM 4,o rl, NUMBER 6c PCTIVE PAVLOIOS ON CRIITI 8 OENSITVI ii,~LBS/FTJ *.LIUMCY SCbSOULEl 0. @*VEAn.* 19 80 81 82 83 84 0 86 87 68 89 *O 91 92 98 94 99 96 t? VU%F.a OF LbUNCZES 2 1. 1 2 1 2 VcY UVITS lEXPtC3bBl.E) 2 1 L 2 1 2 WG*.lE4 3F RETRICVALS 1 2 11 h€w USITS n-6 IKV ~REUSLAILE) 2 1 L ixPCR1*ENT RCO LPPLlCATlOn WF*ATION INDECCNOEMT COST A~CLICITIOL e.*.....e.e.. .* ubISMT8 ( COSTSl a* rn.wElG~T ILBS).e *mR(O COST tS*)am D*CNIT CJ8T lS'4)** M/L* .LIC* oIr8ELIVE. ~LCYCOSTc M~SELIWE* *L'.' COST. ~SIIOSVSTEM.. .NO RISK. .R]S** avo n;sr. .n~sQO 1,538 lnSP4 1,123 STA~~L~TV4 CohTSI; 40, 910 ?a421 6,329 S.612 ,510 ,791 ,645 ATTlTU3E COYTRQL 14, 349 10500 11)81 ,708 *O?s no?) ,079 PnODJLSIO\ 30, @Il 7,501) 121468 11 221 ,442 ,997 ,907 T~rcKl\: b TELEMETRY SO, 36, 11 I423 10,792 ~:b77 1,979 1,bpC 1,338 INVlRfih9EhTAL CONTROL $5. 698 1,175 1,052 ,949 * 165 1 ,180 IWE~~AILCCOOP. 4 @ASSES 100, 2698 1000 ,000 ,OOO *080 8000 rOOO 0. TOTAL a. 890, tlvl, 818682 70aOS bSs99b (*101 b2lO 7,957 *IN, I'iEnT KT, EXPEWABLE C/L QE~UW, I~ERT ulr ml~,TOTAL ~7, EXPEWAILE C/L 893. ~EFUS~.CROP, uT, bbs .nIIg SIVIYCS ((*I. *~EISE,*.EXCE40,. QfFbW, L/C s/S dl, 584. *I3 EX*E~1'EVT 1'7999 07E81 RECUQB. TOYAL VT, ~EuSEI~LE?/L 984, L/C SU~SVSTEWS UT, 8394, TOTAL 380 7 2,bbJO *IN, CQOPELLANT WTl AEUSEAELE ?/L 1bIq CIrE3 SUBSVSTE*S YT, 0. ?OVAL UNIT a6929 a2bl2 *lMr INERT Ute REUSEAIL€ CIL 1309, CICTORl IL/C-~~L-REF~L/C)I # 91VIJ4 MIY~ TOTAL VT, REUSEbIILE P/L 1474, ~~AT~OII~E~T UT~/TOTIL UT~ ,#87b4 A80 PYbSEl S80 VEARS A40 SPREAD 30% TIME AT 140 CDST NLU EIPERI~ENTl1Ol VES I EVE@V.** LAUNCHES I WERATING COST1 oc~EWErrTs r,28e PILLION/L&~*CM, INOE~ENOLNTS 2.024 niLLlOM~vErl FlXEO COR~~ONI~ITI~C ~~vLSTMENT~ 1 ,008 MILLION IWVEST~EWT mrsrl 2,oo vcrns lrvrst*rwt tpcnrot ,or TIME AT ,SO COST . CtnlCEL ALflTbOEI' 19StSr00 N,?. ACOCEE ALTITuOEI 19323,OO IM~TIAL WHIT l":~l~r~l~~~Z~,SO CCC~EES TUC rrtaslo~W~~ITIOW~ .OO nouns r #TR~EVIO CIYLOAO nlcwt~tr mw t r ~oo,~rw WOL 2 r ;oa,s --, . ,.,,- ,. - . -, ., - -b REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR.^ - . . " ,.,- ,-.,.-- - .- ,_ LMSC -Dl 63408 Vol 111 mcr oernor scocI.*o .-....--.....,*,Od, stfSf = --an Ct "r~ o kg,: I ;;;:l8.zwg%t§fJ,, 3s -*.y52cl ,l-!Cf - ::ma.rl E~GZ-~BC~:WIG C)XC,LC -ts .=".".rlL t uw LOCKHEED MISSILES & SPACE COMPANY REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. 1~MSC-l)i5340S Vol I11 -* r CWO C -a.r --a* I- CC *&ma- 331) r\* \Y)WQ3 C -nt+. PI Y)Y)U* WVUC>\I zu \*maw -& A* a-5 - - -ID-- mmm3 a- wbawnoo a23 w*- *r*v*ub- www\--r OIEAbbI * ..--*-.---- I Z a noncvOommooo 0 -a no4or-q onoo n w\ .lC( .a no WY) am W .. YW WWWW = 2 .. AA AAA-1 U 0 om mmmm WA -* -4-- 0 U % - qy wwww*n*m OW a w WW 3333 OH L w n ha WWWW w La 1OEl OCV)>- 5s HW )&I- -.- m lUw -- ..* 02 -wu W 8: LO*-- m- A &E 4U u CCU u- I.L Ob *O -0 9k'mcDa Pi5 . I do Z I : w33rfr" WU'. -w .: -.4OUC i3B0 --1 YO W SIa-6 +:a4 0-bX C I m rn~u&r#wt f +,33 C /w-• 0 IU4O U) WO UCW'UI OC ,nus a-ec>U)* 4 :but-* n ~a -+-on. OC-C~U~X. (~~v'bUrn-BU-Y -nm W-COI)~ Ort ACCmaZM -WnWn IICYY Table 5-4. 1'AYLOAI) COSTS AND CH.4FLACTERISTICS FOR UISSIOX SO. 5 I\CLIIA*:C%I 28.93 DEGREES I?a:e, rr/sEc LICEI 3,D "A~S svroga Or (ctlv~rrv;~&Ds OM OnrlTl 2 rlrcu ronvtm lulrlrb tsvLstMnT1 s ,000 RILLIW I*V€STr€V' ?WASE! 2~00VEA(IS tMVLIttW41 QMAOI MI Tl*L A? ,SO COST WRlCtE ~&Tl?b:El m00 Non, ACOGEC 66' I *J:E I 060 lw'ltlib 0~~1tl*#lw~lO~l a0a5~ OEG~S TUG NtSftOY DbR~?IDTl -00 YmS ...... - --- , , ,, '"---*k".i REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. LMSC1-Ill 5:I.IOH Vol Ill cmerunmnoromn Nrn*enonn.rr eon*nmianL---.*.--.-- om --LC maw r nrn r - 4 a Y .. f C- I 2 S 8 d % - UC V W -vt - 3KLZ6 ~~,ctz'f;?~ -1.. a 0.L ua-I UILU vaS Y)3%CZIO ,:"wet U C 3SZk2fg I - -a" AW rwr-c *r.> W2l .06 m WR- *.aY.W 3'*-UI*& CIdZW0 1 1 .OCKHEED MISSILES & SPACE COMPANY ..L ,. REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. LMSC -Dl53408 Vol 111 -. 0.-- .>rb rnnr nu noon rm r 00 -#A a>a> a.\- .as*\\\- WW YWWW JA ff t2:: 35 %$%% zg 3$$p ww .- I C-OCKHEED MISSILES & SPACE COMPANY REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. ' LMSC-D15:3408 Vol 111 0 Am dr no o uooon .ab-r~ tsc-nr or-or -.dm dnormoor*orr r ---.-.-r..- L .v 014n wn m - - -5" - n nr gg "" -. ClC 2% L,Y--a- C 00 =.#* JJ wwaa .I .I zsU a ** OCC YYAd O..OO -0I I a a** 82 w % Y. w. . C. rn n I.WIY . -- .. -4- .a do- - m.ooco-c n nnwum d \ wb. -rr- den d 33 0 n-m ;r u unr -Ir m ..- - t Wt, C -qlw 'a ZZZ . I\ X J b.C... DO * %>(I) - 8 a'.*e8I%C.C#'r.l a . now... .oa,usInnorr \HWID\. - C J daDV-OIUnmDI -On C. ,,, -r.-----r-. (.a WOUC H *CCN~~rn wuv, \m * rndr.0 *.. - ZQ\OOJW. .. J,,IJVt % n -. I- pi$$zE; du 323 YC- (LIIrUXUC #!-- r"lYr3;T:: 5 3 0aa** 0 *a4 I WY UIAd -I I HW> fEgWWW -%-' O -- 5.. a- w -2 w I.. A s.R,#S "= PC- 8IL.UJZ7 mI.. 5Wd r6 - *- .. : EaaJnr-PI)~C '5-2:WAW W s4a-< C2.i .b# *I c .ma u/-,w. IW*. *J f-.,I O U*#UCW-U a. pm* J.-..#bY)/P* I I.-** A 9 A-crn. U+*UC--C>WI #. y-lvm-. U"W .....f~UlCU* .'C.-.a,--rurur. t: uu5: / LOCKHEED MISSILES & SPACE COMPANY LMSC -Dl 53108 Vol I11 00 N)PILQNIOW w .,nnroNCamCOD .------.----n -me r *-aomnoo rE rdN n n I). d 0 - - n . WY 00 00s r - - -2.C 00 w-e-ft C - m-2 00 my-3 a*JJ -* U* f $3, La > roe**- WYJJ -000 z2 02 0z z WW a-X X UL - w Y -0u x* 3 ::nc - *- 0- .. a d -&: an 0 0 WW * \GO& U -\ -> omdm 6x .. &* - 3 U am =-:a a> XEC nwww- IX NDL nor J om- 0 d a- (. Y* - *----.3 b W -=dm r rwuz - gw-m8 2 - 10 -- r.a YW 00% f- T- 2% 00 P -2 0 *JA * Crr= -OI LaI* r =-X *a 2 WW33 - UI 0- mm -e* S r' "g 2 L WW YWWW " mWWW > > JJ AJJJ 5* fi- 0-- f* oaa YIC zz tZ51' nor, 00 WWWW >'*? L*Cw W 3 -0 71 mmmm WY 2373 'f.. r ZRE . WCU "I - a* aa WYlYY _..it' Z - w -uc LN RE.= U W Am -4 NJWaw YW -- z.. am-tCPO cwn>-a= r..ma .& *,.w-'a O YWWJ> 07lLE 1 OW m-a. w31*'"" 2-0'Kt C.. 2 Awl. aY 0rhmbY)I/ 30- u* WO U L., ' 0 - - .au i.n I-c .Y'2,.I>B m - x-a1nw,.I I. 3W~~,I~P 221 .',.I0 1 LOCKHEED MISSILES & SPACE COMPANY Table 5-9. PAYLOAD COSTS AND CHARACTERETICS FOR JIISSIOS SO. 11 rtt ltuc~cortio~ - P~~PUL~~O* Tn~cUlhCr TLLE*ET?Y ENV1465~EhtALCONtROL ExPt~5rn~ECROP, 4 t4lSES ** TOTIL *a *llrl INEPT UT, EYFE..CAC;E P/L 2540, ~EFu~B,IhERT wT. 759, *lNa TGtbL UT, ErP;'.:A9bE PIL 23209 ~ECUS0, PaOP, wt, 519 amI8S SIV~NGS ((*I* *~LJSE,~*CX~SYD,~ nEFUS9, LIC (IS VT1 0;1, 140 LXPEII*~NT 1'4377 1979) ~EVU~B,TOTAL WT, ~ELSEA~LEOIL 111, LIC SUBSVSTEMS YT 9a~7~ iljrr,g 41~7s 9lw1 PROPELLANT TI *EUSEA.LE DIL 2111 pIXEn ~UOSVSTE~Shg 01 TOTAL'OTAL UNlT'" $,3679 1l4?$ *IN, ~h~ntvtl *E;s€A~-E *tc 31191 IACTORI ~LIC-BIL-RL~(LIC)I v zs4blr) *IN, tetrc u?, PE~~EA~CECIL 333%~ nbtl01 lhtat wt,/totb~ ut, e .93b91 sro PYASEI 4,s VELIS 149 SPIEAO 908 TIWE AT t2~'~~s~ NEW EXPERlPEhT 04Cl TCS ( EVERV 1 LIUNCWE8 ) rlxto Pontt9r rwlrlrc I\vtitMCNTt s 0000 ~ILL~ON 1wrStrr"T PwrrE~1,Co *EARS lhvc8~n~~TSPRCIOI SOX trnc AT ,SO COST PIC COST C1N~lOtMCt~.1111) P~R~GELALIITLOEI 900 ha*, APOCCE ALT1 TuOL I 100 N,*I f*ItIJb WIIT I~C~IW~?IONItOr9O OICRECS TUG HlSSlON OuRATIOrl .DO rOUnS r rrrrnsvro rricoro wctewtl IN MOD# i D ioota AW in moot 2 a ;oolu ..- 5 REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR # 7 , , -, , .,, --. - -. .- , ,. , ,, , ~ ------. ,.__ . - -- - - . LMSC -Dl 534CH Vol 111 . .. C-- C 0-0 OU 0.JQ D J -- av no NY WW z- no00 0 J s 2 - Y 5; (I)-m Y - -- .#~nnmnmoooo~ 0 r. -..h",lnC'mmOL x-Y - .-A -9- On- OChOn 00- U ------or* >A 2 mu- .. - s1 .I arn Ww 24 YU-- nozz YY *a.L1 WY a I W* 0 .. o La Lw WY, . a *w . -2 m J - - 1 0U 00- U- onc 4s- r CWO C oa- C -sac0. 0 r. 0- rn W* CC IRA- t - .* & .7m TXC n0 - C 1 ,nwm= -- --a* U W -mum * OWN2 aa wm~c f 0 >-Y YUU., \I 0N 2 U I ma CE \um-Bw -P -Dm-4 - n> - - - - -6C- C - - m.nm3 o - -0w UP0 crco 4 u 333 W* - was 0 ,.Yk UXU* 0 WwW\-- WW RE= -I= r3 - 00 * IL ma0 3 mo Y, -" 0 0 hm 00. SP' am - A> YY D>a- m0nw > a* " >a a333 WW \\ \\\- 2 NO amJd a L a. Iaaa .. C -4 n IIw>- ww wwww -- WW W AJ 2AJ-I a 2 o-- 00 L..(DQ 0 Y OXI. ..-a- 2 00-. wwww .1 B; EC*WW zz Y)mY)Y) a - ww s3.a~u-10 3YZQ 2-0 = $2 ""4' - ==Pa *a L-2 1 .. a- m YW -- nc A- Z - 2.. 02 t*3 3 ow- t r 0' f .* w- *OU r.A u0 n J LP IV U CC- -- LU UUV>z z ow Q wa 2 m a -= =.- Yi5 - taw -. Y) W10 WUL. Q 5s C*. . Y)0>0(. 3 v. aw-xae -- s. -2OUC W-ma tan w* w C:** U C(I) ViCILWC om rr U4 a2 s z * 7WI> 0 WAO - n waucw-vxmr mns. 3--DlIZ- >Wrcl A3-I-On. ncTUt-b~w~zm:~~;~~~jaJJg nrcawcrazr -wmu* -a* WW LOCKHEED MISSILES & SPACE COMPANY -.-. ..-. .. ,,-,, - ., . - -L ,,- ..,--,. ,. ", . .. L,*, REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. 1 , . LMSC-D1534US Vol 111 *. WW 0 3' - ..m n -I 4 C10 ww.-z L em U 12 R WW f -mw - **a C -C I- -> 01 - 0 a OC . w m -rn rr.. m 0 C WW (I, \a01 >, 0 0 -\ 4an m 0... Cx A a I --we w- aab- - w. gs5- WWL A oa- 0 ml 0- W * a -U & - C--- Y -awu s ~WHL I>-Y z 0--0 -0. ------n r -.rr*.-non-.-- mu LC....". ,...a4 a< CINO~~nrnr -3. ..dd m , --*------z WW 0. .~..'~".~'.O"'.I,Lr "- r F.. o- - 8 DnLt>t.O -049 UR 0 maJJ - * .. W\ 4 w- n- t NN n on-n r * m W n --- 1- N 0 W r> n>> Y' ~2 ;q 5 w a WWW n 0 8 0 0- 0-- wz aocu Y ul 9 OEI * .Y JD db- 1 2- 0 * L*C (II :. a- " -- = m 3: mt: 2 IIX -., 2 * zm dm o ;a, a L- -0 0 ZW Wt 3 - -", O" * m OLD- -2 w - - 02 -r u zx ct rw --3b rrr w4 *dZ ~3 znma w.r = 3 mx "E Z 3. cr o 20 urn YWW LU U CLI -- ,-* *O -0ol. A** OW u WX we as .&z ss te-0 m -rPCA ro - (OW RX N 4.0 Y) YlZO WYP. .r 5 o:: w2 00 ;L tr C.. . IX - i ZSbSE &*g09 .W 2 on' UY: 5 W L-a 2 **PA a WW -c Y c -0 c r OD 2 =g a- = n 58nn,v"'w' mz 0 aUAa 2% 0 r- r- r n woucw-urm~ mnr .---nnr 7r :>w-tu 23.a-Unm *-I JF-+JXDZ. n w>ern-au-u .-am YSCO-ZL OXF_lWCR(LZI -W(*Y1U)-&cuw / LOCKHEED MISSILES & SPACE COMPANY ntsstav ILEWI~G %UVBEBI 22 ZLBF~ELOI o NIMEI SVhCe EARTM ORSERVATIOC M:SS15Y / PAYLOAO OA~A.a MISSION CCUE hUUaERl NEE03 e* (ObSE~lut1 LOW COST) .b ~~CLINATICNI ,OO OLCREES OWJ~TI 1~313~0) I i9)23*f~) ~VI 141EO. FT/SEC AVERACE COUEUI 400~UATTS LIFEI 2,o YEARS SIZE) DIAMETER r,c r~,L~NCTC 6,0 IT, NU~BEROF ~CTIVE PAVLOADS ov ~R~ITIr OENSITVI ~S,I ~6SlFl3 ACCEPTA~LEMISSION nOOESl 0. YES.* *ETRIEVAILE CAVLOA~( MOO€ ) 0. YEP*. RET?IEVIBLE PAYcOAO ( MOO€ 2 ) **LAUNCH SCNkDULEl @*YEAl.* 79 80 41 82 I3 (4 b$ 16 07 08 0 90 91 92 93 94 93 96 97 vumeEa OF LAUNCPES , 1 1 1 I I 1 VEU UkllS (EXPECOIBLE) 1 1 1 1 1 1 YU''5EQ OF IETRI~VALS 1 1 1 1 Niu UNITS N-n INV IREUSFAOLE) 1 EXPCR~~ENT~6o ~PPLI~ITION t • OPERbllON INOECLNDE~~ COST LPPL~CAT~O~ ababee..beaa *.R&D COST OM).. ~OASELIUC. .LOU COST. ah0 "IS#. .RtSua ' 8.12 1'11 23,527 21,694 SlnuCTca~srm ~ECUANIS~S 1,769 3,3:b FLECTRICAL POWER 71900 1,110 ~TA~ILITV 4 CO~TRCL 7 6.664 ATtlTUCI? CONTROL PROPJLS raN UIU. ~~ERTCT, EXPENDABLE P/L 030, ~EFIJ~B,lhERT wt, 914, WIN. TCTAL Ute LXPENOA~LE P/L 1C32e QEFbPBe PREP1 WTI 43. IlXLD PORTlOh INITIAL INVESTMENTI 1 0006 *ILLtON INVESTUCMT CHISLt 1100 YEARS IhVESt*EYT SCRCIDI 5OI TIME by 190 COST PCR~CCEACIITLOLI 1932s,00 rere IWCEC ILT~~UOEt 1912~100N.M, 1UlT1b~WllT I~CLIN~TIONI 28,SO CECREES tUC MlSSIOW OURITIONI .a0 HOURS -.----. .------. . . am---. ...- . - . .- Ira . REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. I.. *-.- . . rrn..n- or mrnor YOdN10N00N00 v,c>m- nmnq o +on .I - *------.*- .. ta r. d .. n 0 -C 0 7hm- D-- 0 2" om *30 3 a 1 \WI 2- OJ -w mmnr r-0. -.. C 0- 0 o ------0 ha 40- - U. onrn -c 3 .L UI * . .I \ L1 22 x t a w- W 2- 0- '3 Y, - (r 00 9 00*a o3 A3 a>a- a> WW n am32 Nm --a WW WWWW 0 0 > > >J AAJA -W WWYl - re mmmM a z 0-0 .a ---a .I. W3 WIG- 00 WY)WW DII mx a E CCWW nom t zz nwwm - 0 0 *a . 3 -0 Z Yxm m rw 5)>23 OU a . wtU PR WWWY zm3Y ZRI0 oo a- IX W- -uD- a~a~ - W - - 5s oW OCUIW U) w do -r WW 4-3 4 03WAY W -- DUE- n > a-02 CC am--za 0 >om-I - * r WI 3 3 . 0 II'C > -a z -wv -. I.. - 7 8" - mLm ex.? u ..LO xo he 42 c! EE*wz l. l. AUv UU-N ol. mwwA* > -- z; :": => %?=Fa xo Crl -0 - won. N m wne nl n aura, 7 7 C..a nOrOE > O. 00 2- a x >-a .. waLT r. -2ouc -- .C -w x-0 L Wa0-I - L *U) rm' 7 =) mu2 -I wm W 9 -0 C U -(r x DOC OD- YO mu, 0 Y)z *Y)>/tu1* UIICWC0 QYJO- -- 1 w-3 0 - -a- *JZ ,WIW t-c rr - '7 W(I uv-w-LSL mt - i w~ rn o 'n 71 w.7- nn a ~--e,rn.- / >-.>.I.W S.t,LF zz.<;yy:- >t.6 JdXO P 4,. ' a1.7...'$ &I-11, 'd ,r WU . -PPl.l-COIwP .'>I# JCC(IIZL -~~Y)H-IcwY) 5-18 LOCKHEED MISSILES & SPACE COMPANY Table 5-14. PAYLOAD COSTS AND CHARACTERISTICS FOR 31ISSION NO. 24 MISSION FLEMlh6 NURBLRI 24 SU8CIELOI 0 NAMEI SVNCI ~PTEOROLOCICAL SAT a* MlS¶ION / CAVLOAO OAT& *O MlSSlON CCYE hUWBLR1 NEOw8 (BASELINE 4 LOW CO8T) b* I~CLINATIC~I ~00DEOREES OR81Tl SVNC~MICI / SINC.M(AI ~VI I~ZCP. PT/SEC AVERACE COVER1 300. WATT8 LIFEI 2 0 VEA~S SIZEI ~~AMETER),a FT. LENCT~ 8,0 CT, NUMBER & 4CTIVE C4VLOADI ON ORBIT1 & OENfilTYl 8~6LBS/RT3 ~OLAUNCYSCCbDULEt a* NUMBER OF LAUNCPES stw UYITS iEXPEN311Lf) OPERA~IONINOEPCVDENT COST *~YEIGMT ILIS)~. ~.R(D COST (s~)*- *B/Lo .L/C* *~ASELILIE~ &LOU COST. ..SV9SvSTEMoa *NO nlwa .RISU~ ADAPTEil 35 82. 1'20 ,437 ,437 EXPE~~YENTwtsslo* EctL~rrL~r 259, 459, 25e3i~(214~) 2Ce52J 19,JnI STaucTbfiEs AND ~ECUAN~BMS 160, 439, 4 I; s,nev ~422 ELECT~ICALCOYER 250e 468, 121400 tIe?Sl 0~017 7.939 STr31~1Tv8 CONTRCb 70, rcz, LOQ*~~ 8,209 7.034 rTTllUCE CONTROL 50, 40)~ 2,950 3,201 2.801 Cao+uLs Ioh 0, 0, 1 000 ,000 ,000 T@bCntNG 4 TELEYTNV 100, S6.u 18,241 20,893 i8.803 ENVl~OkMEhTALCONTBOL )Om ia@S!l 1 I0474 EXPENDABLE PROP, 8 CASSES 90, 254, ,000 ,000 ,004 *a TOTAL b. 1055, 2vlbr 77 ,799 67mbOI 61slEl rtq, INERT VT. MIYO TOTAL V7s REFURB. TOTAL * Y, PROPELLAM1 mfNm 1LERT bTm MlNm TOTAL YT* RIO CYASEI 3,) VEARS R~I SC~EIE 308 rr*E AT (40 coat NEW EXCERIIIENT R40l NO ( EVEPV 0 LAUNCHES I C/L COST C~~*lOE~CElGOO0 ACOGEL bLTITUOEl 19S25~dON 111 TUG MISSION OURATIW@ . .01 MWR8 ~...- -.- ---... . , - - ..ah*, .' REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. .. --.in ooot .c-.C aeon w --- om0 OU t om A0 .*A - - I1 nr w ww WNU - 00 x- 00s x . 0-8 -wnn -" I*-2 2: E? C 00 -co- L - -a .-a! 00 >J 0wa3 . a >4 U I .. ::>A L L > a- I Ob- C WWA2 0-09 ItC 44* Y - v 00ZZ WWa-xx a OCOOOOOOOOL a no- OOOOOOOO* - x Inoo 000000000 s WY *"-..--.-.-.. -0 Cl C C Y). N N = 4 - 0 a 3 man.. 0 WW>* 2."6 .----- m - a. om--0- nrcr -c- - b- dt US - m- 03 u \ wa 0 22 C3 0 -ut 0 - b-WO -2CO . C -*a- -vA- -= C Z ,C- ,110:: C v XYY) Z.C - .*YO1 U:z C -mscs WL: an ww* 00 WUUC* -a rax*u)>w L4- 3 Z -a A* m-5 -3 I .mm- cam;,- a- -- nnnvlrr>o a 73J wc- .. 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LOCIUC-C~WYZ. 0 a W3urn-a U-Y .-c.u WlCOeZa OIF4CCI8al 1Y)nWUaICWY I LOCKHEED MISSILES & SPACE COMPANY -.., --.,. --. . ,- ,- - . ' '* ' - . . - .." . -"'-.- ' ..-kt' REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR. z 1,MSC-Dl53408 Vol 111 * n 4-0 doroom l. Qrn".arUC ONOO* accmmrnonror l. .r. .- -..... -N *a .~-oot mm n cra ma -rr 0 (1 U.x ~n~ncrnromoo~ .CD-Q~O~~~OCOOL AamLCwoaOrOOL . ---I------.x 0 woo01 NW * II z ndno od n - . *. N *(IP --.. o mom * ?9L. 0-. ---dNd RW./ OCOmO~PCP00 O~OnnmOOOOr .-J ~C~LO~OCOO~ ", -.----r--r- u ~cronmrr I -4-0 ...I -.I a r. n C f ..-.-----.- YW 0. .~000r~O0000a 00a A -3 mvcao-n ooon W- NONOU~ rnrn Tm ..dud 0 a*>-*- WWW .. fzg . WW Ct &" Pa m " 0 K w (I) -w a- I C*. -1 4 x.. O,f *OW nm ,,Y J fE* WYYA* > OW r. WI 2. Z5SSr( 5%. t*.. . 2 2tOo'uOc' w'A,OO Z *:a;: U g L'I-g U.I m CYI-l UIIIWC * tWI* 0 wa0 m WEUCW-urac pn.. ~--nnvc- >w-CI -1a-n~-n -I-r Ub--C3uZX. OW3a3m-OU-U ..-a Um-CU-WI c,*CA*CIe*I IYOWUtOCYIY LOCKHEED MlSSfLES & SPACE COMPANY Tablc 5-1 9. PA IZO.4D COSTS AND CHARACTERISTICS FOR JIISSION XO. 29 alsslou FbC*lhC ~i**etl~29 SUIC:~LOI 0 NhwEl $*ALL APCLIC TECH SAT A .a ntsslOY ICAvi.OA0 OlTA am *lSSICh CCCE hC?dCPl NCN-2A a. (IASELlwE L LOU COST, 0. *.LhUlCH SC*C?ULEI * ..VLAn*. 79 bO 81 02 0 84 83 84 0) ;b 69 90 91 92 93 94 99 94 97 ~U~BEROF L UN eS i1~1111l1~1~ rtu UVITS ~CKPE~O~CLE) ~III~LLILIII ~UWEQCC ~E?R~cVILS tllll11Lli ~ic:s'rlTS N-• IKV IREUICAUE) 1 I EI*L~~VEP:T rco ~PPLICITIOIU o.o.o...... o?tnrt ION INOE~~WCE~T~CST rrr~lcr~tob ...... a...m .~UC1Gul YIL. 2C m 150a it,. 15Ce 25 * 30, Om LO. 101 620. 5 REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR, ' - - nr WW no 00--l r rn 00 --,.J>, a* WW am>A a 1 I> 0 WWzz .a .nNNdW dOOOOU WWI rm-rcnoo&ro rn a Uln4O-?NOOrOOn .-.I I...... CI dnrrrr o. n m .d n 0 . Ud mm.. WW ..--.0- .. Ole. -0- - OWAO -C w 9- U1 .4 \ -4A a C - ewo-- b- .SEC --a* ox Ct .war a*n 1 \I- \mwm. C -Us*. 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LfC SfS WT. 618, a40 EXCI~l*L*t 1;1431 ,473) RE?u~B, TOTAL ut, oiLSEA5LE P~L ($81 LfC SU8SlSTE*S UTf 2818, TOTAL R40 4 2 1,8855 *IN, P~CDELLIYT i~,OELSEABLE P~L 218, FINE^ SUBSVSTE~SUT, 3, TOTAL UNIT ! 1205s RIM, I~EOT .*, *E~SEABLE P~L&roo, ~ACTORI IL/C-~/L~RE$(L/CII e ti99r72 WIN, TCTAL #TI eEUSEABLE P/L 1618, WATIOI INERT UT~/TOTAC0, • ,8000 R4O PUASEl 1.9 VEaaS R4D SPREAD 90% TIME AT ,4O COST HEY EXPEa1rEhT 0491 k0 ( LVERv 0 LAUNCHES 1 ?/L COST C3N~lOENCEl POOR APOaEt ALTITUJEI 19329100 Yen, TUG nlsslon DLRATIO~I .OD nouns Table 5-28. PA'I'T.OAD COGTS AND CHARACTERISTICS FOR IIISSION NO. 50 ntsSIc~FLt'lhG 4UYBEm8 5: SFlvfELOl 0 NAVE1 MARS VlKINC *a MISSIOY / PAYLOAD DATA eo *1SSlCN CCVE hb"aE91 4PL.l ** IIASELINE b LOW COST) 0. ..rcc COST (I*).. *.UNIT CJST fS"J.* m8rsELIrt. .LOU COST. .BASELI~E. .L9* COST. .NO ~ISUa.llSu* .uo atsu. .a~sd. ,761) 7t0 ro,lco 37:203 s,~t~5,247 ELE~T~~CALPOLEI - b6 5,9:8 STr3l~lTvb CCuTRCh 6,740 5.796 rrTrtsoC COKTROL i1748 1.571 PROPULSIO~ 47,316 42,585 TabClflkG b TELEUPv8Y 16,874 15.186 EYVlRO**ESTAL CO#T40L 14 i.Oi EXPEhJlaLE PROP. b CbSSES a000 00 *. 1011L 80 i27,*07 tib:ooP MIN. IMRT UT, EIPE*OABLE PIL 44x5, rfruqg, ISERT WT, 10~5. *IN, TCTAL uT, EXPEWABLE C/L 772Ce qtrur6, PRCP, d~, 820. 0RISlf SAVINGS (la). @BEISE,**EXD~'~~* ~ECIJQI, L/C S/S vl. 1468, pro EXPE~IVENT 2 1,1228 RECU~~.T3TAL UT, REUSEIDLE PlL 1Vl'o LIC SUSS*S?E*S YT, 04CV. TOTAL I40 li:9008 6,7632 M]Y, P~OPELLAYTYT, oEuSEA~LE P/L 4125, FIXE3 SU6SVSTEUS bTt 2558. TOTAL UNIT 293526 et4ll MjN, ;tERT bTe REcSEACLE P/L 55109 FACT~RI ILIC-B/L-REFtLlCl I l $7781 )? maw, TCTAL UT. REUSEABLE P/L 9634, ~ATI~I lhERT U?,/?O~AL uT, r ,5?i8V OPERATING SOST1 OEPENOENT S 4.380 PILLION~LAU~CM~INOEPENOENT 1 7,200 M1LLlOY/VEIR FIXEO POWfOE INITIAL IhVESTMENII 1 ,000 RILLlOh ~NVESTRENTPhASEl 3,10 *ELIS I~vEST~EYT 6PREAOI SOX TlnE AT ,SO COST */L COST COh*l:ESCEl 6300 CEllGEE &L1ITLOEI 100 N,", APOGEE ALTITLIOEI ,bO N.M. INITIAL OnUlt INCL~N~TION~30800 OCCREES tUC MliSlON OURA?JONl ,06 r3URB Table 5-29. P;\\'LO.AD COSTS .\SD CIIARAC'rERLSTICS FOR JIJSSI(.)S NO. 31