1974 (11th) Vol.1 Technology Today for The Space Congress® Proceedings Tomorrow

Apr 1st, 8:00 AM

Shuttle Ground Turnaround Operations

Robert H. Buckley Shuttle Turnaround Ground Operations Manager NASA/John F. Kennedy Space Center Kennedy Space, Center, FL 32899

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Scholarly Commons Citation Buckley, Robert H., "Shuttle Ground Turnaround Operations" (1974). The Space Congress® Proceedings. 1. https://commons.erau.edu/space-congress-proceedings/proceedings-1974-11th-v1/session-6/1

This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. SHUTTLE GROUND TURNAROUND OPERATIONS

Robert H. Buckley Shuttle Turnaround Ground Operations Manager NASA/John F. Kennedy Space Center Kennedy Space Center, FL 32899

ABSTRACT The Space Shuttle is the first manned program requiring systems to have "reusability" built This paper will primarily address and define for within. The qround checkout philosophy utilized the Shuttle Vehicle elements; the basic aspects during previous programs, resultina in long check­ of ground turnaround operations being developed out dwell times, but as history records, the by the Kennedy Space Center (KSC). The current operations were very successful. Six months at baseline approach to ground operations will be KSC was not uncommon for manned vehicle checkout outlined including a discussion of the planned operations. turnaround evolution from the Development Phase of the Program to the Operational Phase. Typical To achieve a Shuttle turnaround of two weeks will turnaround activities for each element; e.g., indeed require new innovative and creative ideas Orbiter, External Tank, Solid Rocket Booster, for ground operations, in addition to a flight will be described and will include the integra­ and ground hardware design conducive to oper- tion of the elements up to launch. A brief ability and serviceability. description of the major KSC facilities will be included for clarification of the turnaround process. SHUTTLE APPROACH TO GROUND OPERATIONS To achieve the requirement of a two-week turn­ INTRODUCTION around for the Shuttle vehicle during the Oper­ ational Phase, an approach to qround operations For the past four years Kennedy Space Center has been selected that implements proven tech­ (KSC) has been actively participating in the niques and reduces system level checkout as per­ development of the Space Shuttle Program. A formance confidence is achieved. Flight hardware typical Space Shuttle mission profile is shown performance data baselines will be established in Figure 1 for reference. The KSC contributions during factory and vendor checkout, development have been in many different areas; however, one tests, and the vertical flight test phase at of KSC's most significant contribution has been KSC. The performance data and information base­ in the development and definition of the Ground lines, as used within this paper, are considered Turnaround Operational concepts and philosophies to include timelines, techniques, routines, pro­ that will be required to achieve the Program cedures, and software used during the qround Objectives. operations turnaround. The objective to recycle the flight vehicle to a This baseline will be updated on each succeed!no launch configuration in two weeks and maintain turnaround until the operational baseline is a launch program that is cost effective is a con­ attained. This is estimated to be after approxi­ tinuing challenge. Previous manned programs such mately six (6) flights from the KSC launch site. as Mercury, Gemini, Apollo and Skylab had program goals that required rigorously exacting ground As experience and confidence are gained and operational techniques and methods. Complete system/vehicle performance, data accumulated, and thorough checkout of the entire space vehicle redundant checkout (repetitive testing) will be was the norm. Since there was, relatively eliminated, subsystem level checkout will be speaking, little baseline data available on com­ reduced if not totally eliminated, and the level plex and intricate systems, it was necessary to of of inspection will be optimized. Ultimately, exercise each and every system repeatedly. the qround operations goal* is to utilize the Sufficient data and information on a given maximum amount of data and information from the system and "black box" was imperative to give previous flight during the turnaround, relying on the engineering and management team absolute broad "end-to-end" tests and "go/no-go" type data confidence for a mission commit. The hardware for flight readiness. design for these programs did not contain the operational features that made such demands The ground turnaround approach is basically one quick and easy; but then again, it was not in­ of building blocks. This approach provides for tended to be. Each system was designed to per­ the early turnaround operations (first fliahts) form and function for one mission and one mission to include detailed inspections of hardware only. systems, and systematic checkout of avionics and fluid mechanical systems. The initial process-

6-1 hazardous payload safe. These tasks include ing of the Shuttle System at KSC is planned to be ground months, connection to facility power, facility approximately six-(6) coolant, and Launch Processing System (IPS), Flow Includes positioning of access stands, installation of The first Vertical Flight Operations and engine covers, removal of a Flight Readiness Firing of the main engines engine gimbal locks flow. Subse­ access panels, and safing of any unexpended which is unique only to the first payioads will be removed quent turnarounds will reduce testing and oper­ ordnance. Hazardous ations in an evolutionary manner until the two- during safing operations. as shown week ground turnaround goal is achieved lines are connected, in Figure 2. It should also be noted that during After drain, vent, and purge Test Phase, the fuel cell tanks will be drained and purged. the course of the Vertical Flight be vented from the pro­ incremental demonstrations of operational turn­ High-pressure gases will to pulsion and the Environmental Control Life Support around capabilities will be accomplished The hyperqolic systems verify that the vehicle hardware, ground support System (ECLSS) systems. techniques will be drained of excess propel!ants, and the equipment, procedures and operational with the Main Pro­ support of the two-week goal. interface connections, along can the achievement pulsion System (MPS), will be purged. At the completion of these deservicing/safing operations, the Reaction Control System (RCS) and Orbital OPERATIONAL TURNAROUND Maneuvering System (QMS) modules will be removed the Hypergolic Main­ Ground operation processing of the Shuttle and will be transported to elements are performed in parallel prior to mating tenance Facility. The Logic and obtaining a launch configuration. a visual in­ Flow Chart shown in Figure 3 represents the Following the safing operations, Shuttle element processing for launch spection of the Thermal Protection System (TPS), simultaneous selected structure, landinq gear, tires, etc., readiness. will be made to determine if any damaae was sus­ In addition, a Safing of the Orbiter after landing is the first tained during flight or landina. The Orbiter system performance review will be conducted to phase of the ground turnaround cycle. reports, configuration in Figure 4 and the Shuttle Vehicle evaluate all previous data, inspection for reference onboard flight data, and pilot reports to deter­ Configuration in Figure 5 are shown verifications only. The landing phase begins when communi­ mine fixes, chanaes, and special at the required to ready the Orbiter for launch. cations are established with the Orbiter and the point of post blackout, and continues through the Anomaltes discovered during inspection (TAEM), autoland, system performance review will be scheduled for Terminal Area Energy Management period. and rollout phases. The point of post blackout correction during the maintenance will occur at an altitude of approximately 160,000 140 nautical A maintenance and checkout effort will be per­ feet and a range of approximately subsequent miles. Control of the flight from this point will formed to. prepare the Orbiter for at the landing site. mating and prelaunch operations. Scheduled main­ be supported using facilities component/system Orbiter independent position updates will be tenance to perform programmed supplied by ground tracking systems. These up­ changeout, thermal protection system refurbishment, dates will enable ground controllers to assist modification, etc., as well as corrective main­ negotiate tenance to correct those anomalies determined the Orbiter flight crew to successfully will be made the post blackout and TAEM phases. Once final from inspections and fault isolation interception, ex­ during this operation. Refurbished flight com­ approach begins at glideslope RCS/OMS ternal control of the Orbiter is expected to cease. ponents previously removed, such as with comm­ modules, etc., will be reinstalled during the main­ Coordination of the Orbiter landing of the main­ ercial and/or private air traffic will be required. tenance effort. At the conclusion tenance/modification period, there will be a During this At the completion of Orbiter touchdown and rollout period devoted to power-up testing. of preliminary time, the majority of Orbiter systems testing, at the KSC landing area, a series retests, will securing operations will be performed while the including modification and component will be performed usinq the previously connected GSE. vehicle is on the runway. These tasks the Orbiter for basically consist of toxic vapor detection and The operations required to prepare establish­ the payload installation will be performed in the safing, landing gear lock installation, checkout. ment of ground communications, connection and OPF in parallel with the Orbiter systems cooling, and the initiation of ground purging and checked out and connection of the ground tow vehicle to the The payload(s) will be completely egress while the ready for flight prior to installation. After in­ Orbiter. The flight crew will Orbiter and tow vehicle is being hooked up to the Orbiter. stallation, only the interface between of these pre­ payload will be verified, however, monitoring Immediately after the completion the payload liminary securing tasks, the Orbiter, followed by (as required) of conditions within will be towed to the will continue. After completion of all in­ the ground support vehicles, : 'v/n checks, an Orbiter Processing Facility (OFF). spections, maintenance, and sub:?.: integrated systems test will be performed. This of safing tasks test will exercise and verify all onboa' ..' ;ystems, Upon arrival at the OFF, a series systems to the will be performed to render the Orbiter and any including mechanical and propulsion

6-2 extent possible. The data from all inspections, reviewed as received from the element contractor's subsystem checks, and the integrated test will be manufacturing facility. reviewed to assure that the Orbiter is ready for mating and prelaunch processing. The initial tasks of the subsystems checkout flow involve three operations. The first task is a Following the maintenance and checkout operation, thorough inspection of the external insulation of all GSE and access equipment will be removed and the ET. In parallel, the ship-loose hardware the Orbiter will be towed to the Vehicle Assembly such as the L02 and LH2 feed, vent, and pressuri- Building (VAB) where erection hardware and slings zation lines, and the "ship-loose" SRB and will be installed. Using overhead cranes, the Orbiter interface attachment hardware will be in­ Orbiter will be hoisted and rotated from the stalled and aligned. horizontal to the vertical position, transferred to the Shuttle Integration Cell (High Bay 1 or 3), The next sequential tasks consist of the connection and lowered and mated to the External Tank (which of the ground support equipment (GSE) and the had previously been mated with the Solid Rocket Launch Processing System (LPS) to the appropriate Boosters on the Mobile Launch Platform (MLP)). interfaces to perform electrical, instrumentation, and mechanical functional checks, and L02 and LH2 After mating the Orbiter to the External Tank/ umbilical line leak checks, which will be perform­ Solid Rocket Booster (ET/SRB) assembly and ed in parallel. One set of LPS equipment will be connecting aft umbilicals, a Shuttle Integrated available to each of the four ET vertical checkout Test (SIT) will be conducted to verify Shuttle facilities via switching equipment. Verification vehicle interface compatibility and readiness. of electrical, instrumentation, and electro­ It should be noted that the only testing intended mechanical interfaces and functions will be per­ is to verify the new hardware interfaces that were formed using the LPS to provide stimuli and made in this configuration. At the completion of response verification for each respective sub­ the SIT, ordnance will be installed and connected. system. Verification of fluid and gas interfaces The MLP and vehicle will then be prepared for will utilize standard leak check procedures. transfer to the launch pad. Upon satisfactory checkout of the ET subsystems, The vehicle/MLP will be transferred by the the GSE and LPS equipment will be removed and Crawler Transporter to the pad to begin the pre­ stored, and the closeout of the ET will be launch operations. After the MLP has been mated initiated. Intertank platforms will be removed, to the pad, forward umbilicals are connected, and insulation replaced as required, and forward an interface verification test will be run to hoisting equipment attached. Mobile platforms verify the integrity of the pad/Shuttle System will be stored and permanent platforms opened in interfaces for launch. Hypergolic and related preparation for transfer. pneumatic systems will be serviced and countdown preparation operations will continue up to T-2 The ET will be hoisted vertically with the over­ hours, at which time a 75 minute cryogenic pro- head High Bay crane and transferred to the Mobile pellant loading operation will be performed Launch Platform (MLP), where it will be attached followed by a 1 hour count leading to launch. to the SRBs at the interface points.

External Tank Processing Solid Rocket Booster Processing Initial operations for erecting the ET in one of It is baselined for planning purposes only that the four vertical facility checkout cells shipment of the SRB segments shall be by rail (adjacent to both sides of Tower B - two in High transportation from the manufacturino facility to Bay 2, and two in High Bay 4) include positioning KSC. The segments will be transported in a of mobile access platforms to facilitate removing horizontal position and will have individual end shipping covers and attachment of forward and covers. These covers supply handling points and aft hoist slings and tag lines. The ET con­ environmental and grain protection, and each is figuration is shown in Figure 6. provided with instrumentation to monitor in-transit shock loads, temperature, and humidity. The ET will be hoisted from its transporter by an overhead High Bay crane, positioned to vertical, Upon arrival of the SRB segments at the KSC SRB and transferred to the Vertical Checkout Facility. Facility, the segments shall be off-loaded In either facility cell, both permanent and mobile utilizing an overhead crane. The SRB con­ platforms will be positioned to provide access to figuration is shown in Figure 7. The segments inspect the ET and associated hardware for possible will then be placed on chocks or fixtures where damage experienced in transit, and to remove the receiving inspection shall be performed. The hoisting equipment and special shipping instru­ inspection shall consist of an overall visual in­ mentation. spection of grain, liner/insulation, external case, and general overall examination of each In parallel with the transfer and erection tasks, segment for possible shipment damage. The forward documented configuration and historical data will and aft (closure and nozzle assembly) segments be reviewed to determine exact configuration shall be inspected in a like manner. status. Weight and balance data will also be

6-3 The inert elements, i.e., nozzle extension cone, performance received from flight as to cutoff time, interstage section, recovery section, nose shroud, separation time, and related data. SRB avionics aft skirt, raceways, thrust vector control (JVC) will aid the recovery vessels in locating the systems, etc., shall be placed in a controlled area boosters after splashdown. within the SRB Facility where receiving and in­ spection functions will be performed. The segments The recovery vessels will proceed to their desig­ will remain in storage until they are required for nated area and acquire visual contact with the processing to support a Shuttle launch. The SRB. The SRB will be inspected and rendered safe. storage facility shall be capable of accommodating The nozzle of the booster will be plugged by eight Solid Rocket Motors (SRMs) in the segmented divers, and water will be pumped from the booster configuration. by pressurizing the case with air to reorient the booster from a spar buoy mode to a log mode suit­ Selected subassembly and inspection operations will able for towing. be performed in the SRB Facility prior to transfer of the segments to the VAB integration area. The The parachutes will be recovered while these forward structural assembly will be built up and booster activities are being performed. As pre­ mated to the SRB forward segment. This buildup sently planned, the parachutes will have flotation will consist primarily of avionics system in­ at the apex whicb will permit attaching a line to stallation and checkout; recovery systems in­ the apex which can be used to pull the parachutes stallation; and separation motors installation. onto a palletized drum. The palletized drum will In a similar manner, the aft skirt will be built up be the handling fixture for the parachute through­ and mated to the SRB aft segment. The aft skirt out the recovery operation up to the beginning of avionics will be installed and verified. The TVC the refurbishment operation. The parachute and system will be installed, serviced, and leak check­ drum will be covered to provide additional pro­ ed, and separation motors will be installed on the tection from sunlight and physical contact. Upon aft skirt prior to mating the SRB aft segment and completion of these activities, a tow line will be the aft skirt assembly. attached to the SRB, and the SRB will be towed to port. The individual SRB element assemblies will be trans­ ferred to the VAB by means of a transporter towed Arriving at the port, the SRBs will be removed by a prime mover. Upon arrival at the VAB, the from salt water and cleaned with fresh water. transporter shall be routed into the VAB and They will be inspected and processed in the SRB positioned in High Bay 2 or 4 as appropriate. The Facility for shipment to the manufacturer. The first SRB element assembly (assembled aft skirt/ parachutes will be moved on their respective aft segment) will be hoisted from the transporter, palletized drum, and placed in the refurbishment transferred to and positioned on the MLP. cycle to prepare them for the next launch. Upon completing preparations for the propel!ant If, during the launch and recovery operations, an grain interface, the second segment will be mated. SRB sinks,, the recovery aroup will mark the Each succeeding segment will follow the same location and notify the appropriate maritime sentience until the forward structural/segment authorities. A decision will be made by NASA as.^ , y installation is completed which will com­ whether to salvage/recover the booster and the plete the basic SRB. The actual stacking sequence support services to be utilized to accomplish will be to stack segments on both SRBs in an salvage. alternating fashion. The a 1 ^rwnt check of the two SRBs will actually Payload Processing be P , ,ncd after the installation of the forward s ;.:ral/segment assembly. The SRB raceways The Payload Processing System at KSC will be a ar away cables will be installed and continuous flow of experiments, equipment, and electrically checked, Integrated and automated personnel in the processing facilities motivated systems testing of the assembled SRB will be around a viable quick-reaction launch site con­ accomplished on the MLP utilizing the Launch Pro­ cept. Candidate payloads and carriers derived for cessing System (LPS) to supply ET/Orbiter sim­ Shuttle applications are categorized into the ulation. following three classes, and are individually dis­ cussed relative to their unique launch site pro­ cessing. SRB Recovery Concept Spacelab (including Servicing Missions) The Shuttle developmental launches will also be used for final perfection of the recovery tech­ Spacelab missions are sortie missions utilizing niques and systems. It is assumed at this time a pressurized manned laboratory and/or external that a tow-back method of recovery will be used. unpressurized pallet, and suitable for conducting science, applications, and technology activities. The KSC recovery vessels will be stationed at a Payload servicing missions are accomplished with a safe location outside the SRB impact footprint at version of the Spacelab consisting of a systems launch time. The SRBs predicted impact area will module which contains the necessary subsystems be transmitted to the recovery vessels based upon and an experiment module containing a variety of

6-4 scientific payloads. fs returned to the launch site and transported to the safing area in the Orbiter cargo bay. After Following initial test and checkout of the Space- safing has been completed, the lUS/Tug and space­ lab systems module in the Payload Processing craft will be removed as a unit from the Orbiter Facility (MSO Building), the experiments module cargo bay. They will then be transported to the will be mated with the support module and checked lUS/Tug Maintenance and Checkout Area, where the out as an integrated payload. Upon completion of spacecraft will be demated. Following this, the the integrated Space!ab checkout, the entire pay- lUS/Tug undergoes maintenance and refurbishment load will be transferred to the Orbiter Processing to restore it to the prescribed safety and reli­ Facility (OPF) where it will be Installed in the ability specifications. System level testing will Orbiter. then be conducted on the lUS/Tug to insure readi­ ness for mate. The spacecraft will be transported Automated Payloads to the lUS/Tug Maintenance and Checkout Area, mated, and interface verification accomplished. These experiment packages and experiment carriers, The mated unit will then be transported to the OPF or spacecraft, are derivatives of current un­ or pad where it will be installed in the Orbiter. manned spacecraft and, as such, will be processed After the cargo bay doors have been closed, the similarly to previous unmanned payloads at KSC. lUS/Tug will be maintained in a quiescent state Automated payloads which require more capability with only critical parameters being monitored than the Shuttle alone can provide (e.g., for until final launch readiness checks are performed higher orbits or interplanetary missions) will to confirm system status concurrently with Shuttle require a kick stage. final preparations. Propellant loading will be performed during final operations on the pad and The scope of ground operations for the automated sequenced with Shuttle countdown preparations. payloads includes the necessary planning and pre­ paration prior to hardware arrival at KSC, and all activities from arrival of the flight hardware KSC FACILITIES BASELINE and ground support equipment (GSE) through launch. This planning and preparation will include re­ The current KSC major facilities baseline for the sponsibility for payload deployment in final orbit, Shuttle System include the Orbiter Landing at its final station, or in its final trajectory. Facility, Orbiter Processing Facility (OPF), Test and checkout of single payloads (experiments Vehicle Assembly Building (VAB), Launch Pads 39A and spacecraft) will be performed by transient and 39B, Solid Rocket Booster Facility, Payload crews from the Lead Payload Development Center Processing Facilities and the Hypergolic Main­ representing the various agencies associated with tenance Facility. the experiments and the experiment integrators from the development center. These crews will The Orbiter Landing Facility will be located assemble and install the experiments in the space­ approximately one and one half miles north and craft, and will deliver it to the appropriate Pay- west of the VAB and extend 15,000 feet to the load Processing Facility for conducting prein- northwest. It will be 300 feet in width with stallation/mating tests and checkout. overruns that extent 1 ,000 feet beyond each runway end. Final launch readiness checks of the Automated Payload/Propulsive Stage interface will be made A landing aids control building will be con­ to confirm status concurrently with Shuttle final structed near the southeast terminus of the preparations. Fueling operations will be perform­ runway. Connecting the runway with the Orbiter ed during final operations on the pad and sequenced Processing Facility will be a tow-way approxi­ with Shuttle countdown preparations. mately 9,000 feet in length to allow the Orbiter to proceed to each of the designated processing Initial Upper Stage/Tug stations. The landing facility will be equipped with lightning and navigational aids to support Shuttle payloads which require more capability automatic landing of the Orbiter. than the Shuttle alone can provide (e.g., for higher orbits or interplanetary missions) will The Orbiter Processing Facility will be located require a kick stage. Early in the Shuttle Pro­ near the northwest corners of'the VAB (reference gram, this kick stage capability will be provided Figure 8). It will have two identical hangar bays, by the DOD-developed Initial Upper Stage (IUS). 193 feet by 146 feet with a ceiling height" of 82 The IUS will be a growth version of an existing feet. The hangars will be separated by a two- stage, presumably the Transtage, Agena, or Centaur. story service building approximately 235 feet lonn It will be reusable, but will not have the cap­ by 98 feet wide. This portion of the buildina will ability to retrieve payloads. Later in the Shuttle house electrical and electronic systems, a communi­ Program, a fully reusable Space Tug with payload cations equipment room, mechanical equipment, retrieval capability will be developed. general shop and a thermal protection system (TPS) processing area. lUS/Tug ground operations can be divided into three phases: Post landing operations, main­ The OPF hangars will have the capacity to simul­ tenance and refurbishment, and prelaunch and taneously process two Orbiters, one Orbiter in launch operations. After its mission, the lUS/Tug each hangar. The bay areas will be environ-

6-5 mentally controlled by providing class 100,000 clean air, conditioned to 75 degrees F and 50 percent relative humidity. The VAB is an existing facility at Kennedy Space Center (KSC) that was designed originally to support integration and checkout of Apollo/Saturn V launch vehicles at Launch Complex 39. Ihe build­ ing and its capabilities will be modified for the Shuttle Program to provide for Shuttle element mating and integration, External lank processing and storage, and other related support tasks. The launch pad (Complex 39A and 39B) (See Figure 9) utilized for Shuttle launches are existing facilities at KSC that were designed to support the Apollo/ Saturn V Program. The Shuttle processing concept will require modifications of the existing pad facility which will include (1) a fixed service and access tower on the launch pad, (2) a payload changeout room triangular, 50 feet on each side and 70 feet tall, which can swing to interface with the payload bay of the Orbiter and retract for pro­ tection during launch, and (3) relocation of mechanical, electrical and communication systems to accommodate the Shuttle vehicle service inter­ faces. The SRB Facility, Payload Processing Facility and the Hypergolic Maintenance Facility have not been baselined at the printing of this paper.

EXTERNAL TANK SEPARATION AND DISPOSAL

TERMINAL PHASE CROSSRANGE = 1085 NM DOWNRANGE = 4700 NM h - 50.000 FT

HORIZONTAL LANDING DESIGN TOUCHDOWN VELOCITY = 165 KNOTS MAX a = 15 DEC

SPACE SHUTTLE MISSION PROFILE TYPICAL

FIGURE 1

6-6 26 WEEKS FIRST VERTICAL FLIGHT (INCLUDING FLT. READINESS FIRING)

13 WEEKS SECOND FLIGHT

9 WEEKS THIRD FLIGHT

FIFTH FLIGHT 5 WKS

EVOLUTION OF TWO WEEK GROUND TURNAROUND OPERATIONS SIXTH FLIGHT 4WKS

SEVENTH FLIGHT 3WKS|. . 2 WKS

T T 10 20 30 40 50 60 70 WEEKS FIGURE 2

SOLID ROCKET BOOSTER KSC SHUTTLE FLOW LOGIC ARRIVE BY BARGE OR RAIL

LAUNCH COMPLEX 39 SOLID ROCKET BOOSTER SOLID ROCKET BOOSTER RETURN CASINGS TO MFG. STORAGE, DISASSEMBLY RECOVERY & BUILDUP FACILITY

ORBITER VAB

FLY IN FROM MANUFACTURER HI BAY 3 HI BAY 1

VTRANSFER LANDING FACILITY AISLE

HI BAY 4 [HI BAY 1 \

EXTERNAL TANK c ARRIVE BY BARGE

I______- FIGURE 3

6-7 WING VERT TAIL

AREA (SQ FT) 2690 413.25 AR 1.265 1.675 ALE 45<> 45<>

2 QMS/RCS PODS • OMS THRUST = 6K/EA • RCS THRUST = 0.95K/EA

-122 FT -

3SSME 26.9% LB 470KTHRUST/EA FWO RCS

-BIEIF BODY LENGTH l'LB f * 107.5 FT 1528 ORBITER VEHICLE CONFIGURATION

FIGURE 4

SOLID ROCKET BOOSTER (SRB) 324IN.DIA 142IN.OIA EXTERNAL \ TANK |ET| —————*-

78 FT

SRBTHRUST ATTACH

TANK/ORBITER ORBITER AFT ATTACH

75.9 FT

TANK/ORBITER FWD ATTACH

— 20.25 FT

SPACE SHUTTLE VEHICLE CONFIGURATION

FIGURE 5

6-8 ,AFT ORBITER ATTACH FITTINGS SUBSYSTEM UMBILICAL PLATES ' LH 2 FEED LINE

/CAVITY PURGE LINE

/L0 2 ANTI-GEYSERING LINE /EXTERNAL LH 2 VENT LINE DIMENSIONS EXTERNAL LH 2 LENGTH , . 155.4 FT PRESSURIZATION DIA . , . . 324 \H. \ L0 2 FEED LINE

FWD ORBITER ATTACH FITTING LH2 VENT VALVES LH 2 TANK 53,800 CU FT L02 ANTI-VORTEX BAFFLE EXTERNAL LQ 2 PRESSURIZATION LINE

LH 2 LOADING SENSORS

INTER TANK STRUCTURE

SRB FWD ATTACH FITTINGS

ANTI-SLOSH BAFFLES'

GROSS WT • • • 1,633000 LB L0 2 TANK 19,500 CU FT ASCENT PROP WT • 1,550^000 LB LOX VENT LH 2 LOADING SENSORS'

EXTERNAL TANK (ET) CONFIGURATION

FIGUKt 6

DIMENSIONS

LENGTH 145.1 FT DIA . . 142.3 IN.

4 SEPARATION MOTORS (23,000 LB THRUST) EACH-

SRB/ET AFT ATTACH,

NOZZLE & TVC

AFTSKIRT& LAUNCH SUPPORT

4 SEPARATION MOTORS

SRB/ET THRUST ATTACH GROSS WT ...... 1,163,500 LB RECOVERY WT . . . . . 154,250 LB THRUST (SL) ...... 2.5M LB -FWD SKIRT

-RECOVERY SUBSYSTEM PARACHUTE PACKS LOC/NAV AIDS

^NOSE FAIRING

SOLID ROCKET BOOSTER (SRB) CONFIGURATION

FIGURE 7

6-9 ORB1TER PROCESSING FACILITY (OFF)

FIGURE 8

LJOHTNINO MAST

STIFFLEO DERRICK

OH* VENT ARM

EXTERNAL. TANK SERVICE AND ACCESS TOWER SOLID ROCKET BOOSTER

RCB INSTALLATION ROOM

INOREBS/EQREBS ARM

SUPPORT TOWER FOR CHANGED UT PAYLOAO CHANOEOUT ROOM ROOM

MOBILE LAUNCH PLATFORM

AD TO MLP LOX VALVE COMPLEX INTERFACE PEDESTALS

FLAME DEFLECTOR

FLAME TRENCH LHa VALVE COMPLEX

LAUNCH PAD SERVICE AND ACCESS TOWER (View Looking North)

FIGURE 9

6-10