NASA CONTRACT NAS 2-6518
HEUS-RS APPLICATIONS STUDY
FINAL REPORT - VOLUME I
D2-116262-1
SUBMITTED TO:
JET PROPULSION LABORATORY
ATTENTION: MR. F. L. SOLA
CONTRACTING AGENCY: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION AMES RESEARCH CENTER MOFFETT FIELD, CALIFORNIA 94035
JUNE 1972
N74-115 9 8 (ISACR13 2 7 4 ) HEUS-RS PPLICATIONS Report (Boeinq STUD, VO1UM2 1 Final Wash.) -1- p HC $7.5C Co., Seattle, CSCL 21H Unclas /co G3/2 8 2212
AEROSPACE GROUP - SPACECRAFT DIVISION THE BOEING COMPANY SEATTLE, WASHINGTON D2-116262-1
ABSTRACT
This document is a final report of a High Energy Upper Stage - Restartable Solid (HEUS-RS) Applications Study, NASA Contract NAS 2-6518. The material herein deals with sizing and integrating a high energy upper stage restartable solid motor into a flight stage with various payloads for use with Titan III and Thor launch vehicles. In addition, performance of the HEUS-RS with the space shuttle is briefly examined.
KEY WORDS
Titan IIIB Specific Impulse Thor Propel l ant Thorad Quench Centaur Performance HEUS-RS Mission Model Total Impulse Space Shuttle
PRECEDING PAGE BLANK NOT FILMED
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ABBREVIATIONS AND ACRONYMS
BII Burner II AV Delta Velocity ETR Eastern Test Range FCE Flight Control Electronics GRU Gyro Reference Unit HEUS High Energy Upper Stage HEUS-RS High Energy Upper Stage-Restartable Solid RCS Reaction Control Subsystem ROM Rough Order of Magnitude
TAT Thrust Augmented THOR WTR Western Test Range
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Volume I TABLE OF CONTENTS Page
1.0 INTRODUCTION AND SUMMARY 1.1 INTRODUCTION 1 1.2 SUMMARY
2.0 STUDY TASKS AND RESULTS 7 2.1 TASK 1 - LAUNCH PROGRAM DEFINITION 7 2.2 TASK 2 - UPPER STAGE CONFIGURATION DEFINITION 7 2.3 TASK 3 - HEUS-RS LAUNCH PROGRAM EVALUATION 72 2.4 TASK 4 - ALTERNATE LAUNCH PROGRAM 90 2.5 TASK 5 - PROGRAM COMPARISON 90 2.6 TASK 7 - HEUS/BII SHUTTLE APPLICATION 91 3.0 REFERENCES 96
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1.0 INTRODUCTION AND SUMMARY
1.1 INTRODUCTION
This report presents the results of a Restartable High Energy Upper Stage Applications study conducted for NASA under the technical direction of Jet Propulsion Laboratory, Contract NAS2-6518. The objectives of the study were:
1. Analyze the mission performance capability of a restartable "High Energy Upper Stage" and determine the optimum restartable solid motor size that will provide NASA the most capability in meeting the mission class requirements when it is incorporated into the mission model.
2. Provide a conceptual configuration of a potentially high usage "High Energy Upper Stage" using a restartable solid motor (HEUS-RS).
3. Evaluate and compare the effect of restartable "High Energy Upper Stages" on launch program performance and cost.
Previous studies have shown significant payload performance gains when stop/re-start was incorporated into solid rocket motors. The most significant advantage of re-start capability is realized when used in the upper stage of two stage launch vehicles where the second burn of the upper stage can be used for apogee injection and/or the injection of more than one payload i different orbits. Appropriate application of this capability will preclude usage of more expensive multi-stage vehicles and result in total launch program costs.
The results of the study are contained in two volumes. This document, Volume I, contains the launch program definition, restartable motor definition and upper stage configuration, performance analysis and launch program evaluation. Volume II contains the cost data. During the course of the study four interim reports were made and they are listed as Reference 1, 2, 3, and 4 in Section 3.0 cOfVolume I.
This study originally consisted of six tasks. Task 1 through 5 were technical study tasks, Task 6 was assigned for reporting only. As the study progressed revisions were made to the task assignments, with some items deleted and Task 7 added.
1.2 SUMMARY
1.2.1 Background
Restartable solid motors have been studied by NASA and a feasibility demonstration motor was fired successfully in 1970. Preliminary analysis indicates the most significant advantage of restart capability is realized when used in an upper stage where the second motor burn can be used for apogee injection and/or the injection of more than one payload into different orbits.
The re-startable solid motor fired by NASA incorporated high performance propellant containing a Beryllium additive to the propellant which increased the specific impulse.
1 D2-116262-1
This study considered only Aluminum added to the propellant mixture with a related Is of 303 seconds.
1.2.2 Scope
This study was divided into seven tasks, six technical and one reporting. The work covered in each of the tasks is as follows.
Task 1 - Review the NASA mission model and separate it into four mission classes; Low Earth Orbit, Synchronous, Earth Escape, and Planetary Orbiter. Determine the number of launches for each mission class. These will be used for cost comparison in later tasks.
Task 2 - Perform preliminary performance trades for the mission. Mission classes and boosters listed in Task 1 were used to determine required single and multi-burn times and AZV required to permit HEUS-RS sizing. Design "rubber" HEUS-RS stage configurations for each booster and mission class. Select optimum motor size and design an upper stage that has highest usage rate.
Rask 3 - Perform a mission analysis using the HEUS-RS configuration and determine payload in orbit and trajectory data. Determine the total HEUS-RS launch program ROM cost. Determine a separate ROM cost for development and qualifications of HEUS-RS including launch vehicle and launch site integration.
Task 4 - Determine the total launch program ROM cost to perform the bulk of the mission flights generated in Task 1 mission model.
Task 5 - Compare the costs of Task 3 and 4.
Task 6 - Reporting, reviews, and documentation.
Task 7 - Determine the ability of the HEUS-RS/BII to perform and meet shuttle mission requirements.
During the course of the study, as results became known, changes to the original study outline were recommended and authorized. Some original study tasks were deleted and new tasks were added. These changes include the deletion of Air Force m4ssions from Task 3, the replacement in Task 4 of the alternate launch concepts with launch vehicles and costs generated by Battelle Memorial Institute, the deletion of comparing the performance capability of Task 3 and 4 launch programs, and the addition of Task 7 HEUS/BII Shuttle Application.
A study flow diagram showing work performed under each task and the above mentioned study deletions and additions is shown in Figure 1.2-1.
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HEUS STUDY
TASK #1-LAUNCH PROG DEF *MISSiON MODEL * PERF *BOOSTER SELECTION
TASK #2-CONFIG DEF * AV RQD *BURN TIMES * STOP/STARTS *RUBBER CONFIGj
TASK #3-HEUS PROG EVAL TASK #4-ALIEFNATE PROG *SELECT & INTEGRATE HEUS CONFIG EVALUATION *PERF/MSSION MODEL "OSSA ASSIGNEO L/' * COST-RECUR &- NON RECUR *MULTI P/L'S L' *SESP ISSON=P/L'S *'MULTI LAUNCHES * DETERMINE OLIT COSTS
*BMI ASSIGNED L/V 1 IN *BMI COSTS ] --
TASK #5-PROGRAM COMPARISON " * COSTS-NON RECUR & RECUR TASK #7-SHUTTLE PERF/MISSION] OUT APPLIC S*EVAL CONFIG * STOP/STARTS TASK #6-STUDY REPORT o AV RQMTS .2 REVIEWS *MONTHLY LIR * FINAL PITCH SFINAL DOC
FIGURE 1.2-1 3 D2-116262-1
1.2.3 SUMMARY
1.2.3.1 Launch Program Definition
The mission model provided at the beginning of the study was modified to reflect all available data on the missions listed. These modifications included launch vehicle assignment, revised mission data and deletion of missions where inadequate data, for the purposes of this study, were available.
Assignments of launch vehicles, where none were shown, were based on the NASA Launch Vehicle Estimating Facotrs books 1971 and 1972 (Reference No. 6 and 7). In cases where mission requirements could not be met with the vehicle assignment given, revised assignments were made.
The mission model includes low earth orbit, synchronous equatorial and escape missions. The study results show that the prime requirement for a restartable solid is the low earth orbit missions.
Evaluation of the mission model was accomplished with the HEUS stages in combination with the Thorad, Titan IIIB and Titan IIID. No appropriate applications were found for the HEUS with Delta or Centaur. The Delta and Centaur already offer a restart capability and the additional restart of HEUS provides no increased capability over a non-restartable solid motor.
1.2.3.2 Task 2 Summary
Payload capability was evaluated for three motor sizes, 3000, 5000 and 7000 pounds propellant, that evolved from preliminary sizing studies. HEUS configurations were developed for each motor size, and weight statements defined.
A mission model analysis was used to determine the best motor size for the final HEUS configuration. The impact of the increased propellant weight up to 7000 pounds in the HEUS was to allow the use of a smaller booster for a given mission. However, this impact was secondary compared to the fundamental impact of being able to shut down and restart the restartable solid motor.
Based on this analysis, coupled with the fact that the feasibility demonstration motor was in the 3000 pounds size range, the baseline HEUS configuration of approximately 3000 pounds propellant was selected for the final phase of the study.
1.2.3.3 HEUS-RS Launch Program Evaluation
Launch vehicle performance for the HEUS configuration was determined on a general basis. Payload data for East, Polar and 1000 inclination orbits with the mstartable BE-15B2, TE-M-364-2 and TE-M-364-4 was developed. A general comparison of the relative performance of these configurations is shown in Figure 1.2.3.3-1.
These data include the non-restartable TE-M-364-2 and TE-M-364-4 Burner II stages on a three strap-on Thorad. A significant performance increase :an be realized with the restartable stages. The impact of this performance gain is not totally apparent in the mission model evaluation because program performance requirements naturally gravitate to the current launch vehicle capability.
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PAYLOAD - LBS FIGIRE 1 .2.3.3-1 D2-116262-1
1.2.3.3 (Cont'd)
The performance regime available with the HEUS would certainly attract mission assignments were it a part of the NASA launch vehicle stable. 1.2.3.4 Task 4 Summary The costing of the alternate launch vehicle program is contained in Volume 2. 1.2.3.5 Task 5 Summary The comparison of the costs between Task 3 and Task 4 are contained in Volume 2. 1.2.3.6 HEUS/BII Shuttle Applications The HEUS configurations provide an attractive capability for Space Shuttle interim for various tug. General performance data was dev eloped to show the HEUS capability orbit attitudes and inclination changes. The HEUS configurations provide almost total coverage for the low earth orbit missions of the study mission model. 1.2.4 Conclusions and Recommendations The conclusions and recommendations resulting from this study are as follows: 1. HEUS configurations have a significant impact on low earth orbit missions.
2. Advantages of restartable solids are not completely demonstrated by analysis of this particular mission model since the model was based on existing launch capabilities.
3. Incorporation of quench-restart capability in an existing motor of the 2000 to 2500 pound propellant weight class provides nearly the same low earth orbit capability as the 3000 pound propellant HEUS motor and should provide a significant reduction in development cost.
4. HEUS could provide complete coverage of the low earth orbit missions with small changes to mission requirements for shuttle applications. 5. Larger propellant weight configurations or tandem configurations would be required to provide synchronous equatorial capability in the shuttle applications.
6. Additional study is required to determine HEUS compatibility with the shuttle.
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2.0 STUDY TASK RESULTS 2.1 LAUNCH PROGRAM DEFINITION The mission model used for the HEUS study is shown in Table 2-1. These data reflect the mission model provided at the beginning of the study. The study results show the prime area for application of the HEUS configuration are the low earth orbit missions. The synchronous equatorial and escape missions require a Delta or Centaurttage that already have restart capa- bilities. In these applications the non-restartable motor provides a greater performance capability. Many of the missions in the mission model did not show a launch vehicle assignment or showed a vehicle that could not meet the mission requirements. In these cases assignments were made from the NASA"Launch Vehicle Estimating Factors for Advanced Planning" 1971 and 1972 editions. The mission model included many Scout missions that were included in the prelimi- nary sizing studies but were deleted for the final mission analysis. The actual orbit parameters were used to determine the HEUS assignments. Characteristic velocity requirements were provided but were not consistent. These data are shown on the mission model but were not the criteria for HEUS assignments. Mission model data for USAF missions was not provided in sufficiett detail to allow an overall program comparison. 2.2 UPPER STAGE CONFIGURATION DEFINITION
2.2.1 Task Requirement Preliminary parametric performance trades for the missions shown in the mission model were to be performed to determine the HEUS configuration re- quirements. "Rubber" HEUS configurations for each booster and mission class, were to be defined. This task was to determine the sensitivity of the HEUS propellant weight to the mission model.
2.2.2 HEUS - Rubber Configurations Preliminary weight-estimates were obtained to determine the optimum HEUS configuration as a function of propellant weight and delivered payload. These weights shown in Table 2.2-1 represent "growth" Burner II data used with the restartable motor and large payloads. The fixed weight represents a 3-axis guidance system, telemetry system, power and coast attitude control system. The reaction control system weight has an allowance for H202 motors, tanks, residuals and pressurization system. The structure weight allowance is based on previous Burner II experience with large payloads. This weight is highly dependent on the booster selected for the mission. The rocket motor weight data was obtained from Hercules Inc.
7 D2-116262-1 TABLE 2,1 HEUS - LOW EARTH ORBIT MISSIONS MISSION SHUTTLE MISSIONS CHARACTERISTIC 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 WEIGHT VELOCITY AP PER INCL LAUNCH VEHICLE
ESSA WORLD WEATHER WATCH 1 1 1 1800 28900I 600 600 1010 ATLAS/CENTAUR ESSA LOW 1 675 2 450 700 700 1010 TAT(3C)/DELTA |0 ESSA LOW 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1200 29450 700 700 1010 TAT(9C)/DELTA/ TE 364
ORBITAL SUPPORT MISSIONS 1 1 1 1 1 1000- 26500 350 350 28.50 TAT(9C)/DELTA/ 3000 TE 364
ORBITAL SUPPORT MISSIONS 1 1 1 1 3000- 2 500 350 350 28.50 ATLAS/CENTAUR 5000
NIMBUS 1 1670 28850 600 600 1000 TAT(6C)/DELTA EOS (TYPE I) 1 1 1 2500 29250 500 500 990 ATLAS/CENTAUR e EOS (TYPE II) 1 1 1 3800 29250 500 500 99 ATLAS/CENTAUR EOS (TYPE III) 1 1 1 1 1 1 1 1 1 1 7500 29250 500 500 990 ATLAS/CENTAUR EPS A 1 600 27350 160 160 90 TAT(3C)/DELTA EPS B 1 600 27500 350 350 900 TAT(3C)/DELTA TIROS N 1 1000 29160 700 700 1010 TAT(3C)/DELTA TIROS 0 1 1 1 1500 2 160 700 700 1010 ATLAS/CENTAUR POLAR ERS 1 2 1 2500 29250 500 500 990 ATLAS/CENTAUR MULTI-DISCIP EARTH OBSERV. 1 1 1 1 1 1 1 1 1 1 2500 29250 500 500 990 ATLAS/CENTAUR
SEA - SAT 1 400 28000 400 400 90 TAT(3C)/DELTA MAGNETIC SURVEY SAT. 1 1 1 1 600 2 200 200 200 900 TAT(3C)/DELTA LARGE SOLAR OBSERV. 1 22000 26500 350 350 28.50 TITAN IIIC LARGE RADIO OBSERV. 1 22000 26500 250 250 28.50 TITAN IIIC LST 1 22000 26400 30C 300 33.00 TITAN IIIC LST 1 30000 26400 300 300 33.00 TITAN7IIIC HEAO 1 1 1 1 21000 2 900 200 200 28.50 TITAN IIIC HIGH ENERGY COSMIC LAB 1 30000 26400 350 350 28.50 TITAN 7IIIC OSO I-M 1 1 1 1 1 2000 26400 300 300 28.50 TAT(3C)/DELTA ASTRONOMY EXPLORER "B" 1 1 1 1 1 1 1000 264E0 350 350 28.50 TAT(3C)/DELTA ATMOSPHERE EXPLORER D 1 1000 29600 2100 80 90 TAT(6C)/DELTA ATMOSPHERE EXPLORER E 1 1000 31300 2100 80 150 TAT(6C)/DELTA
FOLDOUT FRAY.,' 8 TABLE 2*4 HEUS - LOWEARTH ORBIT MISSIONS (CONTINUED)
MISSION - SHUTTLE MISSIONS CHARACTERISTIX 74 I~s 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 WEIGHT VELOCITY AP PER INCL LAUNCH VEHICLE LOWER MAGNETOSPHERE -B 1 1 1 1 1 1000 2800 900 900 28.5 TATC)/DELTA/
RELATIVITY B-D l1 1 2000 27 00 430 430 900 TE364 GRAVITY/RELATIVITY A,C,E U1 1 500 26300 300 300 900 TAT(3C)/DELTA PHYSICS EXPLORER 2 1 2 1 2 1 600 29180 800 800 900 TAT(3C)/DELTA EARTH RESOURCES SURVEY 1 1 1 1 1 1 1 1 2000 27!00 300 300 980 TAT(9C)/DELTA OAO -D 1 4660 26(00 400 400 28.5 ATLAS/ENTAUR: OAO E-G 1 1 1 6000 26(00 400 400 28.5 ATLAS/CENTAUR SATS 1 1 1 1 1 1 1 1 600 30 00 300 300 900 TAT(3C)/DELTA
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TABLE 2,,,-l SYNCH EQ. & HIGH ORBIT MISSION CHARACTERISTIC INCL LAUNCH VEHICE 74 75 -6 77 78 79 80 81 82 83 84 85 86 87 88 89 90 WEIGHT VELQCITY AP PER 1000 336(0 19300 100 28.5 TAT(3C)/DELTA SEOS 1 1 1 1 1 1 1300 336 0 19300 100 28.5 TAT(9C)/DELTA SMS CD SMS 1 1 CD/TE364 2000 33600 19300 100 28.5 ATLAS/CENTAUR ATS H 1 33600 19300 100 28.5 ATLAS/CENTAUR ATS I, J, K 1 1 1 1 1 1 1 1 2000 600 336 0 19300 100 28.5 TAT(3)/DELTA SATS 1 1 1 1 1 2000 396.0 19300 19300 0.0 TITAN IIID/ MEDICAL NETWORK 2 CENTAUR
2145 396 0 19300 19300 0.0 TITAN IIID/ EDUCATION BRDCST SAT 2 CENTAUR
2300 396 0 19300 19300 0.0 TITAN IIID/ TROSS 1 2 1 TSSCENTAUR
1 1 1 2000 396 0 19300 19300 0.0 TITAN IIID/ COOPERATIVE APPL. SAT COPRTVIAP.ST1CENTAUR 2 1 1 2 1 2 2000 39600 19300 19300 0.0 TITANIIID/ SYSTEM TEST SAT 1 2 1 Y M TCENTAUR 800 35860 120 K 130 20.6 TAT(9C)/DELTA IMP KK 1 /TE364
675 35700 100 K 200 TAT(6C)/DELTA IMP LL /TE364
1200 33600 19300 100 28.5 TAT(6C)/DELTA AA$ D 1 1 10000 39200 40000 40000 TITAN IIID7/ RADIO INTERFEROMETRY 1 CENTAUR
2000 39200 40000 40000 TITAN IIIC 7 KILOMETER WAVE RADIO 1 1000 39600 19300 19300 0.0 ATLAS/CENTAUR SPECIAL OBSERV. SOLAR ORBIT A 1 1 36200 1.0 A.U. TAT(9C)/DELTA OBSERV. SOLAR ORBIT B 1 1 1000 SPECIAL /TE364 (ST8)
1 1500 96b0 19300 19300 0.0 ATLAS/CENTAUR OPTICAL INTERFEROMETRY A 1 3 1.0 A.U. TITAN / OPTICAL INTERFEROMETRY B 1 1 100 36200 RCENTAUR
- - FOLDOUT FRAVIE 10 I D2-11626 -
TABLE 21 PLANETARY & ESCAPE
MISSION SHUTTLE MISSIONS CHARACTERISTIC 74 75 76 77 78 79 80 81 82 83 84 85 86 887 88 89 90 WEIGHT VELOCITY AP PER INCL LAUNCH VEHICLE VIKING 75 2 7500 39400 TITAN IIID/ CENTAUR VIKING FOLLOW ON 1 1 9700 38400 TITAN II!D7/ CENTAUR VENUS PLANETARY EXPL./PROBES 1 1 1 1 800 37500 TAT(3C)/DELTA ITE364 JUPITER 'TOPS' ORBITER 1 3180 48300 TITAN IIID/ CENTAUR/BII GRAND TOUR 1 1 2 1500 51000 TITAN IIID/ CENTAUR/BII HELIOS 1 1 500 51000 TITAN IIID/ CENTAUR/BII PIONEER H 1 560 48000 TITAN IIID/ CENTAUR/TE364 ENCKE 1 2300 46700 TITAN IIID/ CENTAUR/TE364 MARS HIGH DATA RATE ORBITER 1 7000 37800 TITAN IIID/ CENTAUR VENUS MAPPER 1 7000 38500 TITAN IIID/ CENTAUR VENUS LANDER 1 6000 38500 TITAN IIID/ cenXAUR JUPITER PROBE 1 2000 48500 TITAN IIID/ CENTAUR/BII SATURN ORBITER/PROBES 1 2600 51500 TITAN IIID7/ CENTAUR/BII HALEY FLYTHROUG 1 1200 38500 TITAN IIID VENUS EXPLORER ORBITER 1 1 900 38500 TITAN IIID RELATIVITY 1 500 36200 1 A.U. TAT(3C)/DELTA
FOLDOUT FRAME 11 TABLE 2.2-1 HEUS - RS PRELIMINARY WEIGHTS
CONFIGURATION 1 2 3 4 5 6 7 8 9
PAYLOAD 1000 2500 4000 1000 2500 4000 1000 2500 4000
FIXED WEIGHT 73 73 73 73 73 73 73 73 73
STRUCTURE 105 150 195 155 200 245 205 250 295
REACTION CONTROL 65 65 65 89 89 89 113 113 113
MOTOR INERTS 248 248 248 361 361 361 497 497 497
RESERVE H2 02 18 18 18 30 30 30 42 42 42
WEIGHT IN ORBIT 1509 3054 4599 1708 3253 4798 1930 3475 5020
VERNIER H2 02 18 18 18 30 30 30 42 42 42 MOTOR PROPELLANT 3U000 3000 3000 5000 5000 5000 7000 7000 7000 QUENCH 12 12 12 20 20 20 28 28 28 EXPENDED INERTS 15 15 15 25 25 25 35 35 35
CONTROL H2 02 8 10 12 13 16 20 18 23 28 IGNITERS 3 3 3 5 5 5 7 7 7
SEPARATION WEIGHT 4565 6112 7659 6801 8349 9898 9060 10610 12160 D2-Il16262-1
2.2.2.1, HEUS- RS Motor Sizing
Parametric sizing data for HEUS-RS motors ranging from 3000 to 7000 pounds of propellant was supplied by Hercules Incorporated. This data included the following:
o Motor length and diameter as a function of propellant weight for motor having non-submerged and 35% submerged nozzles (See Figure 2.2.2-1). o Motor mass fraction and vacuum specific inpulse as a function of pro- pellant weight for motors having non-submerged and 35% submerged nozzles (See Figure 2.2.2-2).
o Water quench system weight as a function of propellant weight (See Figure 2.2.2-3). A family of motors was generated using the above parametric sizing data and are shown in Figures 2.2.2-4, 2.2.2-5 and 2.2.2-6. 2.2.3 Stage Configuration
The launch vehicle - HEUS stages - payload combinations investigated during this task are shown in Figure 2.2.3-1.
Rubber configurations of upper stages were generated using 3000, 5000, and 7000 pound motors from the parametric data in Parapraph 2.2.2. The upper stages were designed for use on the Standard Thor, 96 inch diameter Thord, Titan IIIB and Titan III/Centaur launch vehicles. These rubber stage configurations are shown in Figures 2.2.3-2 through 2.2.3-13.
Each of the rubber stages was designed using Burner II hexagonal type structure and a three beam attachment to launch vehicle adapters. The largest diameter motors generated from the parametric data were used to keep the stage as short as possible. This provides maximum payload envelope within the fairing and keeps stage weight at a minimum.
All stages were three axis stabilized and included all the flight subsystems required to launch the payloads. The systems were sized to satisfy the requirements of the various HEUS-RS motor and payload combinations.
Basic Burner II reaction control systems were sized to satisfy the control requirements for HEUS motors with propellant weights from 3000 to 7000 pounds and payload weights of 1000, 2500 and 4000 pounds. The Burner II- type reaction control system provides control moments and thrust on command from the guidance system, starting after launch vehicle separation and con- tinuing until payload separation. The system is shown schematically in Figure 2.2.3-14. It is a dual, mono-propellant system using hydrogen peroxide (H20 ) and nitrogen (N2) control motors. Four H202 motors provide impulse for ooster separation, control during solid motor firing, and vernier control (ff required) of burnout velocity. Eight 2.2 lb. thrust N motors provide impulse for roll control for all mission phases and attituge control during coast. In addition to the normal control functions during boost, the N2 system may perform terminal maneuvers for payload positioning followed by optional payload spinp and soft payload separation. The fN system capacity
13 D2-116262-1
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2.2.3 (Cont'd) is sufficient to provide for H202 system pressurization. The pressure con- trol valve (PCV) regulates the N2 gas to the required operating pressure for the eight N2 motors and the H202'tanks. A relief valve protects the H 0 system against over-pressurization. 2 2
The Burner II RCS was sized to accommodate HEUS motors from 3000 to 7000 pound propellant weight and payload weights of 1000, 2500 and 4000 pounds. H202 motor thrust levels had to be increased, and additional H202 propellant is required. The N2 system remains unchanged except for additional N2 to maintain H202 system pressurization. H202 motor thrust is determined by the effective motor moment arm, payload center-of-gravity offset, solid motor thrust mis-alignment and thrust magnitude. The HEUS solid motor action time was held constant at 50 seconds, and motor thrust was increased as propellant weight increased. A non-dimensionalized HEUS motor thrust-time curve is shown in Figure 2.2.3-15. The resultant H 0 control motor dimension less thrust 2 2 schedule is shown on the lower half of the same figure. H202 motor thrust, as a function of HEUS motor size and payload weiqht, required to provide a 1.25 control margin, is shown on Figure 2.2.3-16. The weight of H20 2 propellant required for control during HEUS motor firing, plus an allow- ance for a 6 second launch vehicle separation burn, is shown on the lower half of Figure 2.2.3-16. For comparison, Burner II is loaded with 18.2 pounds of H20 2 , while the 7000 pound HEUS motor/4000 pound payload combination will require a minimum of 93 pounds of H202. Tank size, in cubic inches as a function of motor size and payload weight, is shown in Figure 2.2.3-17. Again, Burner II uses two 200-cubic inch tanks while the 7000,,'pound/4000 pound HEUS concept will require a!minimum total capacity of 2000 cubic inches. The data shown in Figures 2.2.3-15,16, and 17 is summarized in Table 2.2.3-a.
2.2.4 Performance Evaluation
The payload capability was determined for each of the "Rubber" HEUS config- urations combined with the selected booster family. Boosters considered were the standard and "straight 8" Thorad with 3, 6, and 9 strap-on casters, the Titan IIIB and the Titan IIID.
Figures 2.2 4~lthrough 2.4-3show the payload capability of the standard- Thorad with the three rubber HEUS configurations. Similarly, Figures 2.2.4-4 through2.2.4-6snow the "straight 8 ' Thorad family. Data provided includes last launch from CTR and p6lar orbits from WTR. Figures 2.2.4-7 and 2.2.4-8 show the Titan IIIB and Titan IIID parametric performance. These data were used as a basis for evaluation of the mission model to gain an insight into the best HEUS propellant loading.
Each of these figures indicate that the maximum performance would be achieved with a propellant lodding greater than 7000 pounds. However, application of these data to the mission model indicates that the 3000 pound propellant motor can provide a significahlt impact.
Table 2.2.4-1shows a summary of the potential HEUS use for the 3000, 5000 and 7000 pound propellant weight configurations with respect to the current launch vehicle assignments. These data include Scout missions that were eliminated from consideration in the final phase of the study. The Table shows that the HEUS could meet the mission objectives for 161 out of the 167 launches in the mission model.
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FIGURE 2.2.3-17 37 HEUS RCS STUDY
TABLE 2.2.3-1
CONFIGURATION 1 2 3 4 5 6 7 8 9
PAYLOAD WT., LBS 1000 2500 4000 1000 2500 4000 1000 2500 4000 V) u THRUST, LBf 76 95 103 117 144 159 162 192 210
C-, SwH 202 WT., LB 22 28 30 35 43 47 48 57 62
o IMPULSE H202, LB-SEC 2370 2980 3210 3660 4530 4970 5050 6010 6580
PROPELLANT, LB 3,000 5,000 7,000
MAX. THRUST, LBf 23,000 38,400 53,600
z AVG. THRUST, LBf 18,200 30,300 42,400
- WEB Bo THRUST, LBf 10,000 16,700 23,300
u ACTION TIME, SEC 50
TOTAL IMPUSLE, LBf-SEC 909,000 1,515,000 2,121,000
H202 WEIGHT FOR SEPARATION - LBS 11 14 15 17 21 23 23 28 30
TOTAL H202 WT. - LBS 33 42 45 52 64 70 71 85 93
H202 VOLUME REQUIRED - CU IN 733 920 997 1130 1400 1540 1570 1860 2040 62 NUMBER D2-1162 -I
THE , IP 1, " COMPA 1, REV LTR
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F 2 LAUNCH VEHICLE ASSIGNMENT
3000 LB. HEUS 5000 LB. HEUS 7000 LB. HEUS
CURRENT 0 0 O0 LAUNCH O0O VEH ICLE
TITAN III D 5 0 0 0
12 12 12 36 12 12 12 36 ATLAS/CENT 36 12 24 36 -- -Z- z
5 14 DELTA -9 14 9 5 14 6 3 5 14 6 3
1 23 1 2 3 DELTA -6 3 1 3
75 DELTA-3 75 2 5 68 75 757575 75
33 33 SCOUT 34 33 33 33 33
TOTALS 16712336 3 5 102161 121815 1 5. 1011 1218 15 1 16151 6
TABLE 2.2.4-1 D2-116262-1 2.2.4 (Cont'd)
Increasing the propellant weight in the HEUS would allow the use of a smaller booster for a given mission. However, the impact of this is relatively small compared to the basic gains made by going to restartable solid stages for the overall mission model. 2.2.5 Selected Stage Configuration
After the mid-term review of the stage configurations and performance analysis described in paragraph 2.2.3 and 2.2.4 respectively, the decision was made to concentrate on configurations using 3000 pound HEUS-RS motors. The motor selected for use was the Hercules motor configuration shown in Hercules Phase II final report No. H250-12-6-7 dated July 1970. (Ref. No. 5). The size of this motor is very close to the feasibility demonstration motor. It contains approxi- mately 500 lbs. more propellant. The launch vehicles selected for use were the 96 inch diameter Thor and Titan IIIB. 2.2.5.1 Configuration Sizing
Stages were designed using the 3000 pound propellant HEUS-RS for use on Titan III's and the 96 diameter Thor and are shown in Figures 2.2.5-1 throdgh 2.2.5-4. The payloads used with these configurations weighed 2400 and 4000 pounds. The total launch configuration is shown in Figure 2.2.5-5. All stages were three axis stabilized and included all the flight subsystems required to haunch the payloads including electrical power, telemetry, tracking and command, and attitude control.
The difference in payload weights resulted in two selected stage configurations. The stage for use with 2400 pound payload is hexagonal in cross-section and has a three beam attachment to the launch vehicle adapter.
The stage for use with 4000 pound payload is also hexagonal in cross-section, however, it has a six beam attachment to the launch vehicle adapter to carry the additional load.
Structural sizing was done for both stages and the configurations shown are structurally acceptable for the payloads. A longeron area of 3.0 square inches was selected as an upper limit for which concentrated load redistri- bution into the adapter section could reasonably be expected. All other stage structural components were sized to be compatible with the longerons. The first mode bending frequency for the stage was calculated to be 14 cps, which is high enough to provide a frequency of about 6 cps for the stack above the booster and be compatible with the booster control system. The booster adapters are constructed of .125 inch aluminum skin with long- itudinal stiffness equivalent to the total longeron area of the stages.
48 P- Z-- FAM~I
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FIGURE 2.2.5-5 53 2.2.5.2 Reaction Control System the A Burner II-type reaction control system (RCS) has been sized for BE-15B2 HEUS motor and two payload weights; 2500 pounds and 4000 Hercules with 100 selected RCS provides a 1.25 control torque margin pounds. The are also used for and 108 pound thrust H202 motors. These H20, motors Roll con rol and coast phase pitch/yaw payload/launch vehicle separation. II control can be adequately handled by standard 2.2 pound thrust Burner pairs are used for roll control and four are used for pitch/ Np motors. Two and Four Burner IIA 400 cubic inch H20? tanks are required yaw control. attitude control will provide sufficient H202 for booster separation and during injection motor burn. Excess H202 is available for vernier control of burn-out velocity if required. A pair of standard Burner II N2 tanks the required N for H202 tank pressurization and roll control will provide 2 pounds during injection motor burn. One pound of N2 at rated thrust and 3.44 remains for vehicle controT during toast. Table 2.2.5-1 of N2 in blowdown summarizes the HEUS summarizes the H202 and N2 RCS data while Table 2.2.5-2 BE-15B2 solid motor performance data used in sizing the RCS. Figures 2.2.5-6 will occur -7 present the calculated H202 and N2 upsetting torques that and is also during the solid motor burn. H202 and N2 motor torque capability shown. Adequate control margin is provided. Due to manufacturing and assembly tolerances, vehicle c.g., vehicle center line, and thrust axis will not be in exact alignment. An upsetting torque will be developed. Possible upsetting torque factors include - 1. Payload lateral c.g. uncertainty 2. Stage lateral c.g. uncertainty 3. Payload-to-stage mating 4. Payload-to-stage structural deflection 5. Motor-to-stage mating 6. Motor c.g. offset 7. Motor c.g. excursion 8. Nozzle centerline offset 9. Lateral thrust displacement 10. Angular thrust mis-alignment 11. Expendables offset 12. Expendables Height Differential
and stage lateral c.g. uncertainty combined with the solid motor Payload of the angular thrust mis-alignment usually constitute approximately 95% total upsetting torque. Figure 2.2.5-8 shows these upsetting torque factors. Because the HEUS solid motor thrust varies with time, and as the total ve- hicle c.g. shifts axially with time, the upsetting torque also varies with time. As the solid motor thrust-time history plays a major role in the RCS sizing calculations, it is repeated here as Figure 2.2.5-9. The neutral thrust-time trace of the BE-15C1 solid motor is shown for comparison (growth version - 3109 vs. 2926 pound VKT propellant). The regressive thrust char- acteristics of the BE-15B2 motor limits vehicle acceleration to less than expended 5 g's as shown in Figure 2.2.5-10. Motor c.g. travel and the motor weight history is shown in Figure 2.2.5-11. A 260-pound structure and equip- ment assembly weight (less mtb6r) was assumed for both the 2500 and 4000 pound c.g. shift payload configurations. The effect of motor c.g. travel on vehicle was calculated for both payloads. The vehicle c.g. moves approximately 47
54 D2-l16262-1
TABLE 2.2.5-1 RCS DATA
H202 SYSTEM - PITCH/YAW CONTROL PAYLOAD WEIGHT LBS 2500 4000
H202 MOTOR THRUST - LBf 100 108 NUMBER OF MOTORS 4 4 CONTROL TORQUE MARGIN 1.25 1.25 USAGE - BOOSTER SEPARATION - LBS 14.3 15.5 - INJECTION CONTROL - LBS 34.4 36.7 TOTAL REQUIRED - LBS 48.7 52.2 VOLUME REQUIRED - IN3 974 1044 NUMBER OF TANKS REQUIRED 4 4 TANK SIZE - IN3 400 400 WT OF H202 LOADED PER TANK - LBS 17.2 17.2 TOTAL LOADED INTO TANKS - LBS 69.8 69.8 TOTAL AVAILABLE - LBS 68.0 68.0 AMOUNT REMAINING - LBS 19.3 15.8 WT. MARGIN = AVAILABLE/REQUIRED 1.40 1.30
N2 SYSTEM ROLL & COAST PITCH/YAW CONTROL
PAYLOAD WEIGHT - LBS 2500 4000
N2 MOTOR THRUST - LBS 2.2 2.2 NOMBER OF MOTORS REQUIRED - ROLL 4 4 - PITCH/YAW 4 4 CONTROL TORQUE MARGIN 2.00 1.95 USAGE - PRESSURIZE H202 TANKS - LBS 2.42 2.42 - INJECTION CONTROL - LBS 1.10 1.12 TOTAL REQUIRED - LBS 3.52 3.54 NUMBER OF TANKI REQUIRED 2 2 TANK SIZE - IN 340 340 WEIGHT OF N2 LOADED - LBS 5.85 5.85 REQUIRED AT REGULATED PRESSURE - LBS 3.52 3.54 AMOUNT REMAINING AT REG. PRESSURE - LBS. 1.02 1.00 TRAPPED IN N2 TANKS - LBS 0.29 0.29 AVAILABLE IN BLOWDOWN MODE - LBS 3.44 3.44 MARGIN @ RATED THRUST 1.93 1.89 @ RATED + BLOWDOWN THRUST 5.05 4.96
55 D2-116262-1
TABLE 2.2.5-2
BE-15B2 MOTOR PERFORMANCE DATA
TOTAL IMPULSE - LB. SEC. 889,000
SPECIFIC IMPULSE - LB. SEC/LB 296.33
ACTION TIME - SEC 50
AVERAGE THRUST - LBf 17,780 MAX. ACCELERATION - g's 2500 LB P/L 4.80 MAX. ACCELERATION - g's 4000 LB P/L 3.74 STARTBURN 3314 PROPELLANT 2926 INERTS 388 INERTS EXPENDED 74
E- TOTAL EXPENDED 3000 BURNOUT 314
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inches forward during motor burn, as shown in Figure 2.2.5-12. The net effective H202 motor pitch/yaw moment arm, shown in Figure 2.2.5-13, increases as the vehicle moves forward, enhancing the RCS H202 torque capability. As- suming a nozzle misalignment schedule as shown in Figure 2.2.5-14, typical for a 3000 pound propellant motor, and a 0.20 inch payload lateral c.g. location uncertainty, the maximum upsetting torques in pitch or yaw, shown in Figure 2.2.5-6, is calculated. The pulsed (a normally OFF, pulsed ON, mode is used to control upsetting torques lower than the maximum system cap- ability) H202 motor thrust required to maintain vehicle control (± 30 basis) is shown in Figure 2.2.5-15, and is used to size the H202 tanks. Allowance is also made for the H202 expended during the 6 second launch vehicle separa- tion burn. The 6 second burn produces the following separation velocities (5 to 6 fps is considered minimum):
Payload Wt - lbs. &V fps 2,500 11.9 4,000 10.3
Four cubic inch H 02 tanks provide a weight margin of 1.40 and 1.30 for the 2500 pound and 4000 pound payloads, respectively. Roll torque is the net effect of rotary flow through the HEUS motor nozzle and from unavoidable misalignment (t 0.50) of the H202 pitch/yaw control motors. Figure 2.2.5-7 shows that the standard 2.2 pound thrust Burner II N2 roll motors will provide adequate roll control during the HEUS motor firing intervals. Roll control requirements during coast are minimal, as the vehicle is merely oscillating between the attitude error dead-band limits. Figure 2.2.5-16 presents the required N2 roll motor thrust required to offset the induced roll torque. The area under this curve represents the weight of N2 required for roll torque control. As shown in Table 2.2.5-1, two 340 cubic inch Burner II N2 tanks will provide adequate weight margin for injection roll torque control and H 0 tank pressurization. Long duration coast periods (greater than three hoursi Will require additional N2 tankaqe. The two N2 and four H202 tanks can be located symmetrically around the stage structure.
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6HEE i 2.2.6 Selected Stage Performance Table 2.2.6-1 shows the performance weight statement for the BE-15B2, TE-M-364-4 and TE-M-364-2 HEUS configurations used in the mission model analysis. The data on the TE-M-364 motors includes the estimated weight for a salt quench system. Figure 2.2.6-1 shows the ideal velocity capability of these configurations as a function of payload. Variations in the percent of first burn will cause slight variation in the stage capability. The data shown represents the average velocity capability. 69 D2-116262-1 TABLE 2,2.6-1 HEUS CONFIGURATION PERFORMANCE WEIGHT STATEMENT BE-15B2 TE364-4 TE364-2 BURNOUT WEIGHT 651.5 401.1 340.7 VERNIER H202 4.5 12.3 6.3 SOLID BURNOUT 655 413.4 347.0 PROPELLANT WT 2926 2256 1425.0 QUENCH 43 24 15.0 EXPENDED INERT 49 13.5 13.5 CONTROL H202 & N2 49 15.3 15.3 TOTAL 3692 2722.2 1815.8 PAYLOAD FAIRINGS TITAN - 2000 LBS THORAD - 1200 LBS HEUS TO BOOSTER ADAPTER TITAN - 260 LBS THORAD - 500 LBS 70 :-:-i I !.i- ! ,; ; .::.: ; : -- - . 1 : ..I I .., ...... :! 1:11i li I .-.. -;-.-!: L.z:*T . .-_.::. ::IE :.-* -*l iil l .. i 4.: 11 !-!:illml:1:li . '111 . -!: ' i:i*i ..i,.... -..- 's-.. -:.-.-. ; t -. .: ., : : I i:i: ;i:;:!:1!:::]Hi:::.H:i :::!:! ...... - ... .. - 1 - -- HI I . - .. . , L 1 --... 44.. -;. - -'...- -- ... .1 i;. I !: H ]D :1lE T :I : :.-..7....1 . . .:I-. i 1.1-: i :- . :.:I- ; :. : -;.:.:_; : .. . * .7 .:: : ...-...-L : . . !:;.;.:..;-:.; ;..; -- j, ...... 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I . : . -- -*:74 i i-";: i -i t : : ;--: --..-f 1- ! - . ------''",------!0 4.. .:0 i liF-- --ii H i -.- I : ----":i t7- .;; : : . - ] ...... : . . : ; ..: . . ...: . . . .:: 1.:::-.j::.:-:- - ... D2-116262-1 2.3 HEUS-RS LAUNCH PROGRAM EVALUATION 2.3.1 Task Requirement Task No. 3 requires an application of the HEUS performance capability to the mission model defined in Task No. 1. Payload on orbit for each mission is defined for the HEUS vehicles described in Tasks No. 1 and No. 2. Mission ana-ysis is limited to assurance that the HEUS/BOOSTER combination can meet the mission requirements. 2.3.2 Mission Analysis General performance data has been developed for the final HEUS configuration and the restartable TE-M-364-2 and TE-M-364-4. These data are presented for the standard Thorad, the "straignt 8" Thorad,the Titan IIIB and the Titan IIID. Data is provided for east launch from ETR and polar and 100 ° inclination launch from WTR. Magy missions in the mission model require sun-synchronous inclinations hence the 100 inclination data. These data approximate sun-synchronous inclinations over the altitude region of interest. Figures 2.3-1 to 2.3-3 show the standard Thorad for the three launch azimuths. The performance gain for this family is greatest with propellant increases in the upper stage. The performance increase from the TE-M-364-2 to the TE-M-364-4 is virtually equivalent to the gain from 3 to 9 strap-ons. Figures 2.3-4 to 2.3-6 show similar data for the Thorad (straight 8) booster. The percentage of first burn for all the Thorad vehicles falls in the 80% to 99% region. This requirement can be met by the BE-15B2 quenrh system. The mission applications require two starts and one quench stop, the final stop being burnout of the solid motor. Variations in the impulse of the second burn would be compensated by the H202 vernier system. Figures 2.3-7 to 2.3-9 show the Titan IIIB data. This launch vehicle provides an attractive capability for mission requirements in excess of the TAT(9C)DELTA capability. Figure 2.3-10 shows east and south launch payload capability for the Titan IIID. The Titan IIID somewhat limits the HEUS capability. For example, the BE-15B2 configuration east launch requires less than a 50% burn for altitudes above 475 nm. The percentage first burn reduces to 0, or a single burn at an altitude of 1050 n.m. At altitudes above 1050 n.m. there is insufficient impulse in the HEUS to take advantage of the Titan IIID capability. This limits the capability to the payload attainable by the HEUS when providing the apogee circularization velocity. This results in a requirement to cutoff the Titan IIID early and results in wasting Titan IIID capability. It should be noted, however, that the HEUS provides a significant increase in performance over the basic Titan 1ITD. 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I 1 6 2 -;. !: : ------] I: DTI D 1 1T ;__t:...__:r: !- - .. .II. :::::: . -. ; *! I. * -. : ..... :: :: D2-116262-1 I Two basic booster launch vehicle families were considered. The first includes the Titan IIID, Titan IIIB and the standard Thorad. An overall summary of the assignments made for each HEUS configuration is shown in Table 2.3-1. These data represent 35 low earth orbit type missions and 127 launches. The second family replaces the standard Thorad with the "straight 8" Thorad. Table 2.3-2 shows the summary for this family. Table 2.3-3 shows a comparitive.summary of the two families indicatinq the number of mission types as well as the number of launches. These data indicate that no significant gain is attainable in this mission model using the BE-15B2 configuration. This effect tends to be biased by the mission model since there is a good overall performance gain with the BE-15B2 configuration. Table 2.3-4 shows a detail breakdown of the vehicle assignments made on a mission by mission basis. Booster assignments are noted along with the payload capa- bility fr each HEUS configuration. Booster assignments were made based on using a lower cost vehicle than the existing assignment. Although the mission model analysis demonstrates the value of a restartable solid the mission model tends to favor the current launch vehicle stable because assignments are made based on current launch vehicle capabilities. Table 2.3-5 shows the synchronous transfer capability of the Titan IIIB. While no missions appear in the mission model that are applicable to the Titan IIIB/HEUS, this vehicle provides an attractive gap filler for future mission requirements that exceed the TAT(9C)/DELTA/TE-M-364 capability and do not justify an Atlas/Centaur. 83 LAUNCH V\tH\CL AS\&tNM NT JI TkTAm MvC 9 9 9 9Cq i . ATLS-CETA P, LILN 4I 3 33 5 TTAN IT B o D'ELTA 5 5 5 SELTA o 9 6 (o o oELT 3 37 I6\ 3 T 2 24 34 29 28 -TOTS ; ag q ~ IO oG I (o 3 34' 28 2L 8 873 76 - ABLE 2.3 - 1 LAUNC14 VECHKLE AssIGNMENT Lowv EC1 OREQVTssioiS ~----'SmA1H9 -MCOAD -- c TiTAWL O TTAD &LW T AsO c THMA C TNORA' 3 To atAS A d' L:K IV Alt I Ir Oa /~~~~ ;i i1di4/ J T%-4 MT1TAN1IVIV c 9 9 q . 9 9 9 .' ZELTA 31 ~ 25 15 -1\ aS--E.A IA I t I S DE-LTA C 3\ 2 o 156 23. 20 S-L_ _ o . - 6 - 6 1 6 ELTA 3 A5 i 2 3 - 129 . o 11 4 71 3427 l oo TOTAL _12q__ 31 31 - i- iU4 TABLE 2.3-2 D2-116262-1 TABLE 2.3-3 HEUS CONFIGURATION ASSIGNMENTS # TYPES OF # OF FAMILY/CONFIGURATION MISSIONS LAUNCHES MISSION MODEL TOTAL 35 127 STANDARD THORAD BE-15B2 28 88 TE-M-364-4 27 83 TE-M-364-2 25 76 STRAIGHT 8 BE-15B2 30 104 TE-M-364-4 28 100 TE-M-364-2 26 80 86 02-116262-1 MISSION ASSIGNMENTS TABLE 2.3-4 STANDARD THORAD "STRAIGHT 8" THORAD PAYLOAD CURRENT # BE-15B2 TE-M-364-4 TE-M-364-2 BE-15B2 TE-M-364-4 TE-M-364-2 MISSION -, REQUIRED ASSIGNMENT LAUNCH VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD ESSA WORLD 1800 ATLAS/CENTAUR 3 TITAN IIIB 4500 TITAN IIIB 4300 TITAN IIIB 3900 TITAN IIIB 4500 TITAN IIIB 4300 TITAN IIIB 3900 WEATHER WATCH ESSA LOW 675 TAT(3C)/DELTA 1 TATI3C) 820 TAT(3C) 730 TAT(9C) 710 TAT(3t) 990 TAT(3C) 850 TAT(6C) 850 ESSA LOW 1200 TAT(9C)/DELTA/ 15 TAT(6 ) 1390 TAT(9C) 1270 TE364 ORBITAL SUPPORT 1000- TAT(9C)/DELTA/ TAT(9C) 2200 TAT(9C) 1850 TAT(9C) 1420 TAT(9C) 2600 TAT(9C) 2350 TAT(9C) 1840 3000 TE364 5 r ORBITAL SUPPORT 3000- ATLAS/CENTAUR 4 TITAN IIIB 7050 TITAN IIIB 6800 TITAN IIIB 6500 TITAN IIIB 7050 TITAN IIIB 6800 TITAN IIIB 6500 5000 ,I NIMBUS 1670 TAT(6C)/DELTA 1 EOS TYPE (1) 2500 ATLAS/CENTAUR 3 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 ! EOS TYPE (II) 3800 ATLAS/CENTAUR 3 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 EOS TYPE (III) 7500 ATLAS/CENTAUR 10 EPS -A 600 TAT(3C)/DELTA 1 TAT(3C) 1320 TAT(3C) 1210 TAT(3C) 820 TAT(3C) 1560 ThT(3C) 1960 TAT(3C) 1000 EPS -B 600 TAT(3C)/DELTA 1 TAT(3C)/ 1140 TAT(3C) 1090 TAT(3C) 650 TAT(3C) 1360 TAT(3C) 1150 TAT(B~) 850 TIROS 0 1500 ATLAS/CENT(STD) 3 TITAN IIIB 4280 TITAN IIIB 4050 TITAN IIIB 3650 TAT(9C) 1500 TAT(3C)/DELTA(ST8) ffROS N 1000 TAT(3C)/DELTA .- TAT(6C) 1000 TAT(9C) 1000 TAT(C) 00 TAT(6C) 1110 TAT(9 POLAR-ERS 2500 ATLAS/CENTAUR 4 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 MULTI-DISCIP 2500 ATLAS/CENTAUR 10 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 TITAN IIIB 4700 TITAN IIIB 4500 TITAN IIIB 4150 EARTH-OBS. SEA SAT 400 TAT(3C)/DELTA 1 TAT(3C) 1100 TAT(3C) 950 TAT(3C) 680 TAT(JC) 1310 TAT(3C) 1110 TAT(3C) 800 MAGNETIC SURVEY 600 TAT(3C)/DELTA 4 TAT(3C) 1275 TAT(3C 1090 TAT(3C) 790 TAT(3C) 1 1510 TAT(3C) 1310 TAT(3C) 950 SAT LARGE SOLAR OBS. 22000 TITAN IIIC 1 TITAN IIID23000 TITAN IIID23250 TITAN IIID23500 TITAN IIID23000 TITAN IIID23250 TITAN IIID23500 LARGE BAD18 OBS. 22000 TITAN IIIC 1 TITAN IIID23795 TITAN IIID2OOOCTITAN IIID24250 TITA IIID237995TITAN IIID24000 TITAN IIID24250 LST 22000 TITAN I.IIC 1 TITAN IIID23430 TITAN IIIDe2600 TITAN IIID23850 TITAt IIID23430 TITAN IIID23600 TITAN IIID 23850 LST 30000 TITAN 7 IIIC 1 TITANIIIID34140 TITAN 7IIID34300 TITAN 7IIID34410 TITAi7IIID34140 TITAN7 IIID34300 TITAN7IIID34410 HEAD 21000 TITAN IIIC 4 TITAN IIID24500 TITAN IIID24400 TITAN IIID 24590TITA? IIID24200 TITAN IIID24000 TITAN IIID24690 TITAN IIID33700 TITAN IID30000 HIGH ENERGY 30000 TITAN 7 IIIC 1 TITAN7 IIID33540 TITAN7IIID33700 TITAN 7 IIID30000 TITAN7 IIID33540 7 .COSMIC LAB. OSO I-M 2000 TAT(3C)/DELTA 5 TAT(9C) 2200 TAT(6C) 2420 TAT(6C) 2100 ASTRONOMY 1000 TAT(3C)/DELTA 6 TAT(3C) 1560 TAT(3C) 1335 TAT(3C) 1020 TAT(3C) 1840 TAT(3C) 1610 TAT(3C) 1200 EXPLORER B , 87 02-116262-1 MISSION ASSIGNMENTS TABLE 2-J.-UICDNTDD STANDARD THORAD "STRAIGHT 8" THORAD PAYLOAD CURRENT # BE-15B2 TE-M-364-4 TE-M-364-2 BE-1 5B2 TE-M-364-4 TE-M-364-2 MISSION REQUIRED ASSIGNMENT LAUNCH VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD VEHICLE PAYLOAD LOWER 1000 TAT(6C)/DELTA 6. TAT(3C) 1100 TAT(6C) 1140 TA (3C) 1300 TAT(3C) 1120 TAT(6C) 1070 MAGNETOSPHERE /TE364 ATMOSPHERE 1000 TAT(6C)/DELTA 1 TA (9C) 1000 EXPLORER -D ATMOSPHERE EXPLORER -E 1000 TAT(6C)/DELTA 1 RELATIVITY B-D 2000 TAT(3C)/DELTA/ TE364 3 GRAVITY/RELATIV- ITY A,cC, E 500 TAT(3C)/DELTA 3 TAT(3C) 1D80 TAT(3C) 1020 TAT(3C) 735 TA (3C) 1410 TAT(3C) 1200 TAT(3C) 880 PHYSICS EXPLORER 600 TAT(3C)/DELTA 825 TAT(3C) 828 TAT(6C) 630 TAT(3C) 5380 TAT(3C) S80 TAT(3C) 850 TAT(3C) 600 EARTH RESOB0CES 2000 TAT(9C)/DELTA SURVEY OAD -D 4660 ATLAS/CENTAUR 1 TITAN IIIB 6900 TITAN IIIB 6650 TITAN IIIB 6300 TITAN IIIB 6900 TITAN IIIB 6650 TITAN IIIB 6300 OAO -E-G 6000 ATLAS/CENTAUR 3 TITAN IIIB 6900 TITAN IIIB 6650 TITAN IIIB 6300 TITAN IIIB 6900 TITAN IIIB 6650 TITAN IIIB 6300 SATS 600 TAT(3C)/DELTA 8 TAT(3C) 1185 TAT(3C) 1020 TAT(3C) 735 TAf(3C) 1410 TAT(3C) 1200 TAT(3C) 880 l DUT FRAE 88 D2-116262-1 TABLE 2.3-5 SYNCHRONOUS TRANSFER ORBIT CAPABILITY - TITAN IIIB UPPER STAGE MOTOR PAYLOAD BE-15B2 1900 TE-364-4 1700 TE-364-2 1440 89 D2-116262-1 2.3.3 Program R.O.M. Cost The total HEUS-RS launch program ROM Cost is contained in Volume II. 2.3.4 HEUS-RS Development and qualification Costs The ROM cost for development and qualification of the HEUS-RS including launch vehicle and launch site integration is contained in Volume II. 2.4 TASK 4 - ALTERNATE LAUNCH PROGRAM 2.4.1 Task Requirement An alternate approach to meeting the mission model was required. The mis- sion model requirements generated in Task 1 required review and concepts defined for performing the missions without the HEUS-RS restart capability. 2.4.2 Alternate Launch Program Costs The alternate launch program costs are contained in Volume II. 2.5 TASK 5 - PROGRAM COMPARISON 2.5.1 Task Requirement The HEUS-RS launch program costs developed in Task 3 and the alternate launch program costs developed in Task 4 were compared and the costs are contained in Volume II. 90 D2-116262-1 2.6 HEUS/BII SHUTTLE APPLICATION 2.6.1 Task Requirement This task is to define the shuttle application of the HEUS configuration in terms of payload capability. 2.6.2 HEUS/BII Shuttle Performance The HEUS configurations were evaluated for use as an interim tug for space shuttle applications. General payload data has been defined as shown in Figure 2.6-1. These data show the capability of the HEUS to given mission altitudes as a function of inclination changes. The host orbits for the shuttle are assumed to be 100 nm inclined at 28.50, 550 and polar. These inclinations require some inclination changes to meet mission model require- ments. Tabl(2.6-1 shows a summary of the HEUS configurations capability to meet the mission model requirements. These data assume no maneuver capability in the shuttle and all mission requirements must be met by the HEUS. The mission model used represents the 1981-1990 portion of the mission model presented in section 2.1.1. The summary shows that the HEUS-BE-15B2 con- figuration can meet the requirements for 63 of the 75 missions. The mission model shows that the 12 missions outside the HEUS capability represent 3 mission types. One 10 launch program and two single launch programs. Table 2.6-II shows a detailed breakdown of the mission model and the HEUS configuration assignments. In several cases the HEUS capability exceeds the requirement by a large factor. These missions can be designed to meet the payload requirements desired. The data shown reflects only the maximum capability. Virtually all shuttle application missions fall in the 40% to 60% first burn regime. This requirement may precipitate minor modifications in the restart- able solid motor design for shuttle applications. Consideration was given to synchronous equatorial applications of the HEUS configurations. Figure 2.6-2 shows the synchronous equatorial capability as a function of propellant weight. These data indicate that a larger propellant weight motor than the BE-15B2 is required in order to provide a reasonable capability for these missions. An alternative to a larger propellant weight motor would be two stage configurations. Since these applications require only one restart, the tandem configuration would include one restartable and one single burn motor. The restartable motor would be placed in the stack as required to meet the mission objectives. For instance, in the synchronous equatorial application, the perigee burn would require the complete burn of the lower stage and a partial burn of the upper stage. Apogee injection would then bp provided by a second burn of the upper stage motor. The HEUS configurations do provide an attractive capability for shuttle applications. However, a more detailed study is required to verify the validity and compatibility of the HEUS with shuttle operations. 91 1400 -.--. . .. i. :: ....-.. :- L-* -----ii -iL - i...... iIi~: t :.:=i.i.:.:..:...... L'.i.ii... -liiii ~.i :- ii:i::i'ii!ili-:i :i::-ii ii ...... ii .i i..... 1200 I ...S. .-: ...... " V ...... -- i' -'------~-~ ...... i ...... l...... - - i: -i I " ". -" ! i i: i :::::::::::::::::::: :::::. :-ii--:- l.... ======N I 4~ A 0- R I I I :i~i:;:ili::i.------il. - (li lt l . ii.ii o 14 A N1.E.~ : ..,._ ...... : 400~ li...... --. ~ .. I ...... " ,M . E.. .V .... 1 11. " 11111111. "!" ,...... 1 00 Eta i 1 10SRR ...... -I .....:+-,,! :.-...... :':'. ,...... : ...... ;..;...... :.. :. :: ...... t.:::i: El ::..: .: :- : :":::::.::' l~i: : :::::::" :::- 4 ~ t oil...... ,.. ;"'' " - :::: ::-:i::::: ::::-:: : : 'i::::::1:r:::::i:: : ::::: J1071: f:i-- Z • :--ii c -' . "" ...... t...--...... - ...... i .- m w - a. : :: : :t I::T::::::- i: :: : ' " " ...... ;: .. ':::....I':'::::::;: LE TI W , Il::i!:: I::::::'" ~ ------II-' ' -F ::1::":-. .: . =I i-.: =i : = - ...... ~; I- ...... -- ( .. . :--- -:-1- , -- ---: i::: i 51i " 80 M K' 'I..;::Ii::I '' ' ~' ' -:i-:I: 64- ..; c;--- i . :---:-i - -ti: - t~ -: -i-- -i -r-! -c-- -i--::-l: 'i:1i~i!-:i::: i::1::::::i:::::::::-:: i::al - 0 4-- - k :7 1 ! --JI::i::::::iT:::::- rD 2 :. ;04 -:: :::: :-:'".6 'U -- :::.:-.' :--!.- 8--- ...... ---- I --- 10 ::-:-T.,- --:. :: - .--. " ' : . -.:: :.-.12: - :.--- : ::14: :- ,:.,..::.16 .-;--;-- 18 ::. 20- O :::i :: :::i:i:::::i: :::i:-PAYLOAD .... -1000 LBS:-::i:::::: :::::-::::::::::::::::lI rU 2.6-1..- ii .~-.. .:...:.. :::::::::!:.FIGURE . . qjl 02468 10 12 14 16 18 20 PAYLOAD - 1000 LBS FIGURE 2.6-1 TABLE 2.6-I POST 1981 SHUTTLE MISSIONS CURRENT LAUNCH VEH. BE-15B2 TE364-4 TE-364-2 TOTAL TITAN IIIC 6 1 2 1 4 ATLAS/CENTAUR 24 7 7 14 TAT(9C)/DELTA 20 20 20 TAT(6C)/DELTA 5 5 5 TAT(3C)/DELTA 20 20 20 TOTAL 75 1 9 53 63 ASSIGNMENTS BASED ON SMALLEST STAGE REQUIRED HENCE: TE-364-2 53 MISSIONS TE 364-4 62 MISSIONS BE-15B2 63 MISSIONS SHUTTLE APPLICATION TABLE 2.6-II TOTAL LAUNCH MISSION 81 82 83 84 85 86 87 88 89 90 WEIGHT AP PBBL INCL BE-15B2 TE364-4 TE364-2 MISSIONS VEHICLE ESSA LOW 1 1 1 1 1 1 1 1 1 1 1200 700 700 1010 4100 2900 1850 10 TAT(9C)/DELTA - /TE364 I 1 1 1 1 1000-3000 350 350 28.5 30000 22000 14300 5 TAT(9C)/DELTA ORBITAL SUPPORT /TE364 ORBITAL SUPPORT 1 1 1 1 3000-5000 350 350 28.5 30000 2200b 14300 4 ATLAS/CENTAUR 10 ATLAS/CENTAUR EOS (TYPE III) 1 1 1 1 1 1 1 1 1 1 7500 500 500 990 EIROS 0 1 1 1 1500 700 700 1010 4100 2900 1850 3 ATLAS/CENTAUR MULTI-DISCIP EARTH OBS 1 1 1 1 1 1 1 2500 500 500 990 4300 31001 7 ATLAS/CENTAUR MAGNETIC SURVEY SAT 1 1 1 1 400 400 400 900 26230 18850 12000 4 TAT(3C)/DELTA LARGE SOLAR OBSERV 1. 22000 35Q 350 28.5 30000 22000 1 TITAN IIIC LARGE RADIO OBSERV 1 22000 250 250 28.5 67000 48000 1 TITAN IIIC , TITAN IIIC LST 1 22000 300 300 330 1 LST 1 30000 300 300 330 1 TITAN 7IIIC TITAN IIIC HEAO 1 21000 200 200 28.5 80000 57100 36830 1 HIGH ENERGY COSMIC LAB 1 30000 350 350 28.5 30000 1 TITAN 7IIIC OSO M 1 2000 300 300 28.5 32000 26000 22000 1 TAT(3C)/DELTA ASTRONOMY EXPL. 1 1 1 1 1000 350 350 28.5 30000 22000 14300 4 TAT(3C)/DELTA LOWER MAGNETOSPHERE 1 1 1 1 1 1000 900 900 28.5 9600 6800 4400 5 TAT(6C)/DELTA /TE864 RELATIVITY B-D 1 1 1 2000 430 430 900 21500 17100 11000 3 TAT(3C)/DELTA /36V RELATIVITY A, C, E 1 1 500 300 300 900 32000 26000 22000 2 TAT(3C)/DELTA PHYSICS EXPL 1 600 800 800 900 11000 7800 5000 1 TAT(3C)/DELTA EARTH RESOURCES SURVEY 1 1 1 1 1 2000 300 300 980 4500 3150 2050 5 TAT(9C)/DELTA SATS 1 1 1 1 1 600 300 300 900 32000 26000 11000 5 TAT(3C)/DELTA 73 FOLDOUT FRAME 94 . 4 0;;; .: . .. . . 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T N E P ND D WEG T , UR 00 B 26- D2-116262-1 3.0 REFERENCES 1. 2-1109-3600-570, HEUS Study Status Report for October 1971, dated 4 November 1971 2. 2-1109-3600-655, HEUS Study Status Report for November 1971, dated 14 December 1971 3. 2-1109-3600-153, HEUS Study Status Report for February 1972, dated 6 March 1972 4. .2-1109-3600-238, HEUS Study Status Report for February 1972, dated 10 April 1972 5. Report No. H250-12-6-7, July 1970, Final Report, Phase II, High Energy Upper Stage Motor Program. Volume 1 through IV, Prepared by Hercules Incorporated, Wilmington, Delaware 6. NHB 7100.5 NASA Launch Vehicle Estimating Factors Handbook, January 1971 Edition 7. NHB 7100.5A NASA Launch Vehicle Estimating Factor Handbook, January 1972 Edition 96