Results of the Third Saturn IB Launch Vehicle Test Flight AS-202 Vol II

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MPR-SAT-FE- 66- 13

October 25, 1966



Th_contains information affecting the n a t_e

of the United Sta _ "_i in of th ° _ aw_ Title 18,• " ents

in any m a nner to a n un a uthorized person is prohibited by l a w.



M_PR-SAT-FE- 66- 13

RESULTS OF THE THIRD SATURN IB LAUNCH VEHICLE TEST FLIGHTAS-202

By

Sa turn Flight Evalu a tion Working Group

George C. M a rshall Space Flight Center

(U) ABSTRACT

S a turn IB AS-202 was launched a t 1215:32 EST on August 25, 1966from KSC LC34, under surface conditions of light winds, moderate tem-per a ture and humidity, and good visibility . The vehicle lifted offa fter a total del a y of 45 min due to holds, on a launch azimuth i00 deg

east of north and rolled to a flight azimuth 105 deg east of north.The actual trajectory was near nominal.

All m a jor systems performed within design limits a nd close to pre-dicted v a lues throughout flight. Although no malfunctions or deviationsoccurred th a t a dversely affected flight or mission, cert a in refinementsfor future flights are indic a ted in camera coverage, camer a recovery,guid a nce, and SPS ignition sequence.

The AS-202 test flight demonstr a ted the structur a l integrity a ndcomp a tibility of the stages of the launch vehicle and the sp a cecr a ftduring powered flight and coast. It permitted evalu a tion of performance

of the launch vehicle propulsion, guid a nce, control, sep a r a tion, struc-tural and electrical systems, and the efficiency of mission supportfacilities a nd oper a tions.

The report is contained in two volumes: Volume I cont a ins onlyunclassified dat a ; Volume II only classified.

Any questions or comments pertaining to the inform a tion contained

in this report are invited and should be directed to:

Director, George C. Marsh a ll Sp a ce Flight CenterHuntsville, Alab a ma 35812

Attention: Chairm a n, Saturn Flight Ev a lu a tion Working GroupR-AERO-F (Phone 876-4575)



t_{_t..?_/m---,. ,.dr .,,_Ln_m m-_., -,_ n q- n • •

GEORGE C . MARSHALL SPACE FLIGHT CENTER

MPR-SAT-FE-66-13

RESULTS OF THE THIRD SATURN IB LAUNCH VEHICLE TEST FLIGHT (U)AS-20 2

VOLUME II

SATURN FLIGHT EVALUATION

WORKING GROUP

dl,=,,,. ,._ ••.,., ,., .; _ ,Z;qT;AL -





(U) TABLE OF CONTENTS

VOLUME II

Page

i_O (U) Introduction 1

2,O (C) Launch Vehicle Guidance Error Analysis 2

(U) LIST OF FIGURES

Figure Page

2-i (C) ST-124M3 Stabilized Platform System Error Sources 4

2-2 (C) Platform Velocity Component Differences 6

(Tracking Minus Guidance)

(U) LIST OF TABLES

Table Page

2-1 (C) Guidance Intelligence Errors 3

2-11 (C) Guidance Platform Velocity Comparison 5

2-111 (C) Guidance Comparisons (S-IVB Cutoff and 8

Spacecraft Separation)

iii



1.0 (U) INTRODUCTION

Volumes I and II of this report, present the results of the early

engineering evaluation of AS-202, the third Saturn IB vehicle flight-tested. Volume II presents only those data which are classified. The

evaluation is centered on the performance of the major vehicle systems,

with special emphasis on malfunctions and deviations.

This report is published by the Saturn Flight Evaluation Working

Group--composed of representatives of Marshall Space Flight Center,

John F. Kennedy Space Center, and MSFC's prime contractors--and in

cooperation with the Manned Spacecraft Center. Significant contributionsto the evaluation have been made by:

George C. Marshall Space Flight Center

Research and Development Operations

Aero-Astrodynamics Laboratory

Astrionics Laboratory

Computation Laboratory

Propulsion and Vehicle Engineering Laboratory

Industrial Operations

John F. Kennedy Space Center

Manned Spacecraft Center

Chrysler Corporation Space Division

Douglas Aircraft Company

International Business Machines Corporation

Rocketdyne Division of North American Aviation

The official MSFC position at this time is represented by this

report. It will not be followed by a similar report unless continued

analysis or new evidence should prove the conclusions presented herein

to be significantly incorrect. Final stage evaluation reports will,

however, by published by the stage contractors. Reports covering major

subjects and special subjects will be published as required.

/_II_i iP i I_lPIk I--PI • il



2.0 (C) LAUNCH VEHICLE GUIDANCE ERROR ANALYSIS

The velocity errors shown in this report are within the accuracy

of the established postflight trajectory data and the preflight estimatesof the guidance hardware errors.

Preflight estimates of the component and system errors were obtained

from a series of laboratory tests made several weeks prior to vehicle

launch. Prelaunch telemetry was sampled for an indication of platform

orientation errors. This telemetry, adjusted for preflight estimates

of accelerometer bias a nd scale factor errors, indic a ted that the ST-124M3

stabilized platform was aligned well within the 3 _toler a nce. Postflightanalyses also verify this.

The predicted errors of the ST-124M3 inertial platform sys_m forthe AS-202 flight test were based on laboratory calibration of the

ST-124M3 stabilized platform system. These errors are shown in Table 2-1

and Figure 2-1 a long with guidance error solutions based on both thepostflight reference tr a jectory and GLOTRAC dat a . The 3 _ v a lue foreach error component is also shown.

Telemetered pl a tform velocities a t principal event times are shown

in Table 2-11 for comp a rison with corresponding v a lues taken from the

postflight and preflight reference trajectories. The differences between

the telemetered velocities a nd postflight trajectory data are within the

noise level of the data compared. The cross range velocity telemetered

from the guidance computer included about 28 excess negative pulses

(-1.4 m / s) a ccumulated due to vibr a tions during the first 8 sec of flight(See Vol. I, Section 12.4.2,2). The differences between the telemetered

data and the preflight trajectory reflect the non-stand a rd performance

of the vehicle as well as sm a ll errors in the guid a nce hardware per-form a nce.

The telemetered guid a nce velocities were differenced a gainst both thepostflight reference trajectory and GLOTRAC data. These differences

(tracking minus guid a nce) are shown plotted versus range time in Figure

2-2. The _ 3 o velocity component errors at S-IVB cutoff a re shown forcomparison. Guidance error analyses were made to determine sets of

guid a nce system errors that would simulate the observed velocity dif-

ferences for both the postflight reference trajectory a nd GLOTRAC d a ta.

Before comparisons were made, the telemetered cross range velocity was

a djusted for the excess pulses accumul a ted during the first 8 sec of

flight. Velocity differences associated with the error solutions are

shown as points enclosed in squares and triangles for the trajectoryand GLOTRAC data, respectively. GLOTRAC lost lock at a bout 415 sec and

the error solution was terminated at that point. Although the error

solutions fit the velocity difference curves, the accuracies associated

with the tracklng data a re no better th a n + 0.5 m / s a t S-IVB cutoff.



TABLE 2 - 1 ( C) G UID ANCE INTEL L IGENCE ERRORS

Lab o ratory and Err o r So u rce Error S o ur c es 3P a ramet e r Symbol Units P re- Laun c h Me s s. Establlshe d Fm. Established F_ n. Error

Err o r So u rces TraJ An a lysis GLOTRAC An a lysis Band

I. System Errorsa. Pl a tfo rm Le v e l ing des

i) About X Axis LX 0.4 x 10 -3 O.105 x 10-3 0.5 x 10-22) About Z Axis LZ -0.6 x 10 -3 -0.85 x 10.3 0.5 x 10 -2

b, Flight Azim u th Alignment A z A des -0.1 x lO -2 -0,47 x 10-3 0.01

c. A c c e lerometer Misallgnm e nt desl) R a nge (X) Aec el Ro ta ted Tow a rd Z Axis MXy -0,4 x 10-3 -0.4 x 10 -3 -0.4 x 10 -3 0.01

2) Altitude (Y) A c cel Rot a ted Toward X Axis Myz -0. 2 9 7 x l_ "2 -0.3 x 10 .2 -0. 8 x 10"3 0.42 x 10-23) Altitude (y) A cc el Rot a ted Tow a rd Z Axls Myx -0. 5 x 10"_ -0. 5 x 10 -3 -0, 5 x lO -3 0.89 x 10-2

d. Gyr o Dr i f t Rat e s, Co nstant deg / hrI) y aw (X) Gyro (Abo u t X Axis) _X 0 . 0 1 3 0 . O14 0.081 O . lO02 ) Rol l ( y ) GymJ ( Ab out y Axi _) 2 ¥ 0.0 29 -0. 0 _ 5 -0. C3 6 0 . 0753) pitch (Z) G y r o ( Ab out Z Axis) _Z 0.037 0.035 0.036 0.075

e. Gyro Drift R at es, g- De pe nden t deg / hr / g

I) yaw (X) Gyro (A b o u t X Ax i s Due to _) _X / X -0.004 0.028 0.0 2 0 O , 1002) yaw (X) Gyro (A b out X Axis Due to Yl _X / Y -0.0015 0.054 0 . 051 0.0603) R o ll (y) Gyro (Ab o u t y Axis Due t o X) _Y / X -0 . 007 0.020 -0.031 0 . 0604) Roll (y) Gyro ( About Y Axis D u e to Y_ _Y / Y -0.0005 -O.044 -0.06 0.07 55) Pitch (Z) Gyro (Ab o ut Z Axis Due t o X) _Z / X 0. 0 18 -O,O39 0.013 0.07 56) Pitch (Z) Gyr o (Abo u t Z Axis Due to y) <Z /q 0.007 -0.071 -0.04 0.060

2 . Co mponent Er r orsa. Accelerometer Bias m / s / s

I) R a nge (X) Aeeel er o meter BX 0.24 x 10 - 3 0.22 x 10-3 0.19 x 10 -3 0.3 x 10 -32) Al t it u d e (y) Accelerome t er By 0.5 x 10 -4 0.5 x 10 -4 0.33 x 10 -4 0.3 x 10 -33) Cr o ss R a nge (Z) Ac c el e r ome ter BZ - 0 .9 x 1 0 -4 -0 . 12 x 10-3 -0 . 96 x 10 -4 0.3 x 10 -3

b. Acc elerometer Scal e Fa ct o r g/gI) R a nge ( X) Aceelerometer g X 0.9 x 1 0 -5 -0. 2 4 x 10 -4 - 0.58 x I0 " 4 0.3 x I O-4

2) Altit u de ( Y) A¢celerometer 8y 0.22 x 10 -4 -0.35 x 10 -4 0.23 x 10 -5 0.3 x 1 0 -43) Cr o ss Range (Z) Ac c elerometer SZ -0.I x 10 -5 -0.1 x 10 -5 -0.I x 10 -5 0.3 x 10 -4



Aecelerometer Bias (m / s / s) Accelerometer Scale Factor (g / g) Accelerometer Misalignment (deg)

0.0005 0.00005 0.01 .......BX By BZ SX Sy SZ ....

MXy Myx Myz

Nil ....o-0.0005 -0. 00005 -0.01 .......

Ini t ial Platfom Constant Gyro Drift g-Dependent Gyro Drift

Mis a lignment (deg) Rate (deg / hr) R a te (deg / hr / g)

6x, O.Ol .... O.lO .... 5y _z O .lO .... gx /_ _Y /_ 6z /_

o ..-.- o rl _ o _ n__ n

-0.01 -0.i0 ...... 0.i0 .... F] Prel a unch Me a sured Err or Sourc e

Tra je ct ory An a lysis

_ GLOTRAC Analysis3e

FIGURE 2-i (C) ST-124M3 STABILIZED PLATFOF_I SYSTEM ERROR SOURCES



, 5

TABLE 2-II

(C) GUIDANCE PLATFORM VELOCITY COMPARISON

Event Telemetered Trajectory

Range Time (sec) * Accelerometer Computer Postflight Preflight

1553.55 1553.55 1552.62 1565.95

IECO y 2359.45 2359.45 2358.90 2337.86

139.57-23.35 -24.75 -23.08 -11.86

1627.10 1627.10 1625.58 1622.04

OECO y 2401.60 2401.60 2400.48 2369.99143.47

-24.25 -25.65 -23.97 -12.39

1776.45 1776.45 1776.64 1769.02

Guidance Initiation Y 2488.15 2488.15 2488.02 2454°69

172.40-25.25 -26.65 -25.08 -15.22

6768.05 6768.05 6768.20 6784.16

S-IVB Cutoff y 4126.70 4126.70 4125.57 4209.67

588.47-0.75 -2.15 0.42 -1.79

6774.80 6774.80 6774.98 6789.81

SpacecraftSeparation y 4127.90 4127.90 4126.76 4210.49598.70

-0.75 -2.15 0.23 -1.91

* _ - Range Velocity (m / s)y - Altitude Velocity (m / s)

- Cross Range Velocity (m / s)

** Preflight values are based on nominal event times which do not necessarilycoincide with the actual event times.



Range Velocit y Differe nce (m / s) [_ Trajectory Curve Fit

] • GLOTRAC Curve FitF

i . O _'-

i00 200 300 400 500

Ra nge Time (sec) - -3 o

- 1 . O -

!

Altitude Velocity Difference n / s) - +3 o

1.0-_

100 ' ' 200 J_--_# "_t_-"._---;_--,L_-. _,__\ f= ._% , 500-_F_- -_ ,;\.._ "_a_ -._ _ Range Time (sec)

-I.0 - _!" !D_ _-_ , ,

-30' Cross Range Velocity Difference (m / s) m +3 q

i ...... : _ _._.

1.0 -- ..--._._ . ._:_'"

. F ,_#.

o ......... : ........ .... 1 1 I200 300 400 500

Rang e Time (sec)

- 1 . O 1

I- -3o"

FIGURE 2-2 (C) PLATFORM VELOCITY COMPONENT DIFFERENCES(TRACKING MINUS GUIDANCE)



f'_f%i_ I i'-lir_r"i_ i"l"l • i

The AS-202 vehicle was successfully guided to satisfactory end condi-tions as shown by the comparisons in T_le 2-111 for S-IVB cutoff a ndspacecraft separation.

The component differences between the postflight tr a jectory andguidance computer values are well within the 3_ tolerances. Since theIGM guid a nce scheme does not constr a in the flight to a prescribed tr a -

jectory, the differences between the preflight and telemetered positionand velocity components merely reflect non-standard vehicle performanceand environmental conditions. The total velocity shown for the preflighttrajectory indicates a cutoff velocity error of 0.32 m / s. However, the

preset value for the guidance computer was 6800.00 m / s, compared withthe actual cutoff velocity of 6799.95 m / s.

_i4VI'_II I llWii. • . ....



TABLE 2-III (C) GUIDANCE COMPARISONS

(S-IVB Cutoff and Spacecraft Separation)

S-IVB Cutoff Spacecraft Separation

Parameter Symbol Units __ Tr ajectory Guidance Trajectory GuidancePrefligh t Postfligh t Computer Prefligh t Postfligh t Co mpu t er

Total Velocity V S m / s 6799.63 6800.22 6799.95 6798°58 6800.23 6799.89

Radi a l Distance R S km 6592.061 6591.943 6592.1 5 1 6596.716 6596.695 6596.910

p a th Angle 8 deg 3.996 3.986 3.994 3.832 3.822 3.834

Displacement: *

Ra nge X S km 1875.677 1831.924 1831.806 1941.970 1899.872 1899.770

Altitude YS km 6319.418 6332.129 6332.373 6304.227 6317.032 6317.280

Cross Range ZS km -45.284 -43.698 -44.723 -46.156 -44.572 -45.623

Velocity:

o

Range XS m / s 6636.88 6647.26 6647.21 6616.02 6627.52 6627.41

Altitude YS m / s -1476.19 -1431.63 -1430.48 -1563.18 -1520.48 -1519.31

Cross R a nge iS m / s -87.60 -85.61 -87.81 -86.99 -85.07 -87.41

• E arth-Center Plumbline Coordinate System



APPROVAL MPR-SAT-FE-66- 13

RESULTS OF THE THIRD SATURN IB LAUNCH VEHICLE TEST FLIGHTAS-202

VOLUME II

By Saturn Flight Evaluation Working Group

The information in this report has been reviewed for security

classification. Review of any information concerning Department of

Defense or Atomic Energy Commission programs has been made by the MSFC

Security Classification Officer. The highest classification has beendetermined to be Confidential.

Stanley L. F_agge ' / •

Security Classification Officer

This report has been reviewed and approved for technical accuracy.

J , _ / _indberg Fligh_aluationtEvh_man, Saturn " Working Group

llermann K. Weid_ e r

Director, Research and Development Operations

L. B . J a mes

Saturn I / IB Progr a m Ma nager



i0

DISTRIBL 'F ION :

Dr. vo1_ Bra,n, DIS R-ASTR (Cont_ R-P&VE (Cent)Dr. R o es, DER-T Mr. R . Smith, R-A_TR-E Hr. Aberg, R-P&VE-V

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E-S Mr. Hose n thi e i1. R-ASTR-F Mr. Devenish, B-P&VE-VN H ( 2 )

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Mr. S'_ i_i) , E - S Hr. Ferrell, R-ASTR-GSA Mr, Rothe, R-P&VE - XF

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I Hr. F owei[, B-ASTR-I Mr. Boone, R -P&VE - XK

Mr . Pri_e, R-ASTR-IE_'n. O ' Conn_r, !-DIR I _p[ : Mr. Av ¢' rv, R -ASTR - IMDDr. Mr,!z ek, I-DIRMr . deb t :son, I-I,IB-C Mr. El) , , R -ASTR - IRD Mr. Grau. R-QU AL- DIR

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Mr , e rr , R-ME - M Mr. Ec wo rds, R-TES T-M

R&B Mr, Fran k li n , R-ME-T Mr, Drisc c ll[_ R - TES T- S

Mr--' 7Weidner, R-DIS Mr, Wuencher, R-ME-X

Dr, Johnson, R-EO-DIR MS

Mr, Willi a m_, R -A S-D IS ( 2 ) _-S - RMr, M e sser , R-OM-V

Mr , D a vids o n. R-S (M a il e d under " MSC) R_P&VE MS-IDr, Luc_s, R-P&VE-DIR blS-IP

Mr. Ri c hard, R - TO-BIB Mr . He ll e brand . R- P&VE- DIR MS - IL (_)

R-_ERO Hr . P a[ _o ro . R -P&VE-DI R MS- D

Dr . Geissler , R-AERO-DI R Mr. Goern e r , R-P&_ ' E- A

Mr. Jean, R-AERO-I)IR Mr, Stern, R-P& VE-A CC ° P

_r, Da ' _., R_A ERO-A (2) Mr, Kingsblr\ ' , R-P& VE-M Mr. Wofford, EC - P

M r. Hold ere r , R-AER O- A Mr. Thompson, R-P&VE-PA

Mr, Wilson, R-AERO-AT Mr. Fuhrmann, R-F&VE-PM KS CC

Mr , Need. R-AERO-AU Fir . IBoU, R-P&VE-PPE Dr. Debts, DIRMr . H orn . R-A ERO-D Mr. McK_y, R- P&VE-PPE (2) Col. B a g n ula, EDV

,_r. D e ,_toe, R - AERO-DA .Mr, Bl_ck, R - P&VE-PPE Mr. Pap p el, EDV-I

Mr . Rynn, R-AERO-DD Mr . Nt,lso r_ R- P&VE-PPB Mr. Sparks, EDV-17

Dr, McDOnough, R- AERO- DDS Hr. Wood, R-P&VE-PT Mr. D a rby , El)V-16 2

Hr. Lindberg, R-AERO-F (33) Mr . M_Anelly, R-P&VE-PTD .Mr. Se.ndler, INS (4)

Mr, Baker , R- AERO-G Mr, Plait. R-P&VE-PTF Dr. Br u n s , IN S -I

Mr , McNa ir, R-AEBO-P (3) Mr , Hun_, R-P&VE-S Mr. Col[i_, INS-4

Mr . Teague. R - AERO- P Mr. Blumrich, R-F&VE-SA Mr . JeI e n, INS-13

Mr. C u e : *nlngs. R-AERO-T Mr . Katz , R-P&VE-SER Lt. Coi . Pecrone, PPR (3)

Mr. Va u ghan. R-AERO-Y Fir. Sho_oers, R-p_VE-SL Mr. Mathe_s, PPR-4

.Mr. S co gg in s, B -AERO-Y Mr, Fr ederick, R-P&VE-SS Mr, BodY, PPR-6

Mr. O. E. S_ith, R-AERO- Y_ I copy Hr. Furm a n. R-F&VE-SJ Dr , Knothe, ]ECMr. D a iliels, R-AERO-Y j blr. G a ss_w a y, R-P&VE-SV Mr. Lee , I-I-I / IBR*ABTR Mr . Gossett_ 1.X,O .22

Dr , Ha e u sserm_ n n, R- ASTR-D!R

Hr. DiBesu, R-ASTR-A LVOMr. Fi c htner R-ASTR-E Dr. Gru e ne_ JA

Mr. Rigell , JA

Mr . Edwa rds, d E

Mr. Fannin_ JD

Mr , P ickett, JF

Mr. O'Har a , JF

Mr , G. Willlams_ HJ



ii

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Documents

Results of the Third Saturn IB Launch Vehicle Test Flight AS-202 Vol II