Sergeyevsky, A. B.

English

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
Technical Memorandum 33- 736 
Volume // 
Misdon Design Data b r  Venus, Mars, and 
Jupiter Through 1900 
J E T  P R O P U L S I O N  L A B O R A T 3 R Y  
CALIFORNIA INST ITUTE  OF TECYWOLOQV 
CASADEeA, CALI lrnRNIA 
September 1,1975 
https://ntrs.nasa.gov/search.jsp?R=19750024068 2020-03-22T20:40:40+00:00Z
30 September 1975 
NASA S c i e n t i f i c  and Technical 
Information F a c i l i t y  
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Gentlemen: 
Attached herewith a r e  COSATI Technical Report Standard T i t l e  Pages f o r  JPL 
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Two copies each of t he  Technical Memoranda and Spec ia l  Publ ica t ion  l i s t e d  
below a r e  enclosed f o r  your systems input  and l i s t i n g  i n  t h e  unlimited, 
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Pioneer 10--From Apr i l  1, 1972, Through the  J u p i t e r  
Encounter Period,  January 1974 
TM 33-72 i b r a  : An Inexpensive Geodetic Network Densi f i c a t i o n  / /-tern 
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/ 3-73?,. Mission Design Data f o r  Venus, Mars, and J u p i t e r  Through 6flv 1990 
~ 33-73; Hission Design Data f o r  Venus, Mars, and J u p i t e r  Through 
Vol. 1/1.990 
3-736 blission Design Data f o r  Venus, Mars, and J u p i t e r  Through 
I 1990 
Telephone 354-4321 Telex 6 75421 
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TECHNICAL REPORT ST ANLJARD TITLE PAGE 
Report No* 33-736, vole 11 I 2. G o n r m m t  Accessfon No. 3. Recipient's Catalog No. I 
4. Title and Subtitle 
MISSION DESIGN DATA FOR VENUS, MARS, lUJD 
ctUPITER THROUCH 1990 
5. Report Date 
September 1, 1975 
6. Performing Orgonizat ion Code 
9. Performing Organization Name and Address 
JET PROPULSION LABORATORY 
California Institute of Technology 
4800 Oak Grove Drive 
Pasadena, California 91103 
' Author Andrey 8. Sergeyevsky 
110. Work Unit No. 
8. Performing Grganization Report No 
1 1 , Contract or ~ i a ~ t  No. 
NAS 7-100 
13. Type of Report and Period Covered 
2. Sponsoring Agency Name and Address 1 Technica 1 Memorandum 
5. Supplementary Notes 
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
Washington, D.C. 20546 
6. Ahtract 
14. Sponsoring Agency Code 
The purpose of this document is to provide a handbook, containing working 
data to be used in the selection and trajectory design of missions to Venus, 
Mars and Jupiter during the 1975-1990 time period. 
Unclassified I Unclassified I 3-231 I 
7. Key Words (Selected by Author(,)) 
Astronautics (~eneral) 
Astrodynamic s 
Space Transportation 
Lunar and Planetary Exploration 
( ~dvanced) 
18. Distribution Statement 
Unclassified -- Unlimited 
99 Security Classif. (of thb report) 1 20, Security Clasif. (of this pago) 1 21. No. of POQW 1 22. Price 
PREFACE 
This document is  dlvided into three volumer. Volume I comprms the minion deulgr 
data for Venu, Volume 11 the data for Mars, and Volume 111 the data for Jupiter. 
S L  TECHNICAL M-ANDUM S 7 a .  VOL. 11 
TABLE OF CONTENTS 
A. INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . 1-1 
B. DESCRIPTIONOFTRAJECTORY DATA . . . . . . . . . . . . . 1-1 
C. DESCRIPTION OF PLANETARY POSITIONAL DATA . . . . . . . . 1-3 
REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 
LIST OF FIGURES 
1. Definition of B-Plane . . . . . . . . . . . . r . . . . . . . . . 1.4 
2. Definition of Cone and Clock Angle . . . . . . . . . . . . . . . . 1 4  
Contours of Cg ilnd Flight T i e s ,  W, DLA, ZAL, INC, 
ZAP, ETS, LVI, SZE, ETE, THA, SG1, SG2, and SG3 for 
Earth to Mars Missions Launched in 197980,1981 -82, 
1984,1985-86,1988,1990 . . . . . . . . . . . . . . . . . 3-1 through 3-84 
Mars Positional Data for the Years 1975 to 1995 . . . . . . . 34' through 3-231 
A. INTRODUCTION 
MISSION DESIGN DATA FOR VENUS, MARS AND JUPITER 
THROUGH 1990 
Andrey B. Sergeyevsky 
This document prestnts mission design data for direct 
transfer trajectories from Earth to three planets - Venus, 
Miirs and Jupiter, exten5r.g previously published informa. 
tion (see Refs. 1, 2, 3, 4 and 5) through the 1990 depar- 
ture opportunity. 
The primary purpose of this effort is to provide the 
mission analyst with graphical information, sufficient for 
preliminary mission design and evaluation. The data follows 
closely .the format of Reference 4 and reflects methods of 
Reference 2. A specially modified version of the Space 
Research Conic Program (SPARC) (see Ref. 6) was used 
tn genentr the trajectory information presented. The data 
were automatically contour-plotted on the SC4090 plotter 
using the General Plot Program (GPP) (see Ref. 7), then 
hand ;etouched and labeled. A special program (VIEWE) 
was constructed to provide planetury positional data in 
graphical form, plotted on the SC4020, and presented in 
original format. 
The data a n  arranged in three sections by arrival planet, 
in natural sequence. Each section condsts of two parts - 
the trajectory chvracteristics for all available opportunities 
to the particular plnnet, in chronologid order, followed 
by that planet'a porltional datr for ewry calendar year, 
from 1975 to 1995. 
The perwerlng and encouraging inrirtence of manage- 
ment, especially that of Mr. Willard E. Bollman to carry 
this effort through to  completion,.^ well rc the graphic 
md  editorial support of Mr. Richard W. Rackus are 
gratefully acknowledged. 
8. DESCRIPMON OF TRAJECTORY 
CHARACTERILmCS DATA 
The data represent trajectory performance informo- 
tion plotted in the departure datelarrival date space, thus 
defining all possible transfer trajectories between the two 
bodies, within the time-span considered. Fourteen individ- 
ual priuneters are contour-plott: : on the departure enerpy 
(Cj) background contour chart, for each opportunity. The 
following opportunities are presented: 
To Venus: 1975,1976/7,1978,1980,1981,IY83, 
1984/5, 1986, 1988, 1989190. 
To Mars: 1979, 198112, 198314, 1985/6, 1988, 
1990. 
To Jupiter: 1977, 1978, 1979, 1980181, 1981182, 
1983, 1984, 1985, 1986, 1987, 1988, 
1989, 1990. 
2. Definition of Tamr 
The following parameters are displayed on the contour 
plots: 
2 3  
C3 Earth departure energy (km 1 s ~ ' ) ;  same as 
the square of departure hyperbolic excess veloc- 
3 3 ity V;= C3 V i  - ZGM/Rl, w k r e  
VI conic injection velocity (km/sec) 
GM + gravitational constant times mass 
of the attracting body, from 
Reference 8: 
RI = % + hl, Injection radius (km), 
sum of surface radius RS 
and injection altitude PLANET 
h,, where (see Ref. 8): 
R s v ~ ~ l ; s  = 6052 (km) 
Time of  flight (Days) 
Earth to planet communication distance at  
arrival (km) 
Arrival hyperbolic excess velocity 
where 
V = Heliocentric conic arr~val velocity 
at  heliocentric radius R (m). 
Arrival Planet Orbit insertion velocity incre- 
ment AV, at periapse, may be computed 
from V,: 
where R and RA ;re planetocentric peri- 
apse a n t  apoapsc radii (km), respectively. 
Similarly, if specific capture orbi! perlod 
q w c )  and periapse rddiur Rp are derired: 
BPLANE 
T-AXIS 
1.2 
A plane normal to the incoming V, - 
rector and passing through the center of 
planet. 
Axis in B.plane, parallel t o  ecliptic (Earth 
mean orbital) plane (see Figure 1 ). 
DLA 
ZAL 
INC 
ZAP 
ETS 
LV I 
ZAE 
ETE 
TH A 
SGI 
SG2 
Geocentric declination (vs. mean Earth 
q u a t o r  of launch date) of the depar- 
ture V, vector. May impose launch 
constraints. (deg) 
Angle between departure V, vector and 
Sun-Earth vector. Equivalent t o  Earth- 
probesun angle, several days out. (deg) 
Heliocentric inclination of transfer Ira. 
jectory with mean ecliptic (Earth orbital) 
plane of  launch date. (deg) 
Angle between arrival V, vector and the 
arrival planet-to-Sun vector. Equivalent to 
planet-probeJun angle at far encounter; 
for subsolar impact would be equal to 
I8OP(deg). 
Angle in arribal B-plane, measured from 
T-ax~s, clockwise, to projection of Sun- 
to-planet vector. Equivalent to solar occul- 
tatlon region center-line. (deg) 
Planetocentric latitude of vet tical impact 
vs arrival planet eqilator. Note thai Venus- 
ian north is below ecliptic, while Mars' 
and Jupiter's is above. Equivalent to  
declination of the incoming asymotote 
(i.e., the negative of  incoming V,vector) 
in planetary equator system. 
Angle between arrival V, vector and the 
planet-to-Earth vector. Equivalent to  
planet-probe-Earth angle s t  far encounter. 
(Dee.) 
Angle in arrival B-plane, measured from 
T-axis, clockwise, to  projection of  Earth. 
to-planet vector. Equivalent t o  Earth 
ocrult8tlon region centrrllne. (dsg) 
Angle in arrival &plane, from T-axis, 
clockwise, t o  major axis of  error d ie  
pcrsion ellipse (0 - I80 deg). 
Semimajor w i s  maylitude of B-plane 
dispersion ellipse, resulting from a spher- 
ically distributed V, velocity vector error 
of  0.1 m/sec on departure asymptote 
(km). 
%mi-minor axis of above dispersion 
eclipse (km). I t 
r 
JPL TECHNICAL MEMORANOW St=, VOL. II 3 
SG3 Arrival time dispersion, normal to &plane, 
for above error model (sec). 
YR/M/D Year, Month, Date. 
3. Dcrription of Pbtr 
C. DESCRIPTION OF PLANETARY 
POSITIONAL DATA 
a) DECLIN Ceosentric Earth equatorial 
declination of planet (P), plan- 
etocentric plnnetvry equator- 
ial declination of Earth (E) 
and Sun (S). Note that Venus- 
ian north is below ecliptic. 
1. General 
The data represent planetary geometry-related infor- 
mation plotted versus calendar arrival date at  the target 
planet. Ench set of seven plots represents the annual time 
history of 19 parameters, and may be used for flyby and 
orbiter missions. 
b) EC.LON Heliocentric ecliptic longitude 
of planet. 
2. Description of Curve Labels 
c)  CA,KA Cone (ECA) and Clock (EKA) 
angle of Earth and cone angle 
of Canopus (CCA) as seen 
from a Sun-Canopus oriented 
spacecraft near target planet, 
P (see Figure 2). 
P 
E 
S 
C A 
K A 
RlSEXX 
SETXX 
Target planet, equivalent to probe ap- 
proaching or in orbit about target planet. 
Earth 
Sun 
Cone Angle, i.e., Sun-probe-object (Earth 
or Canopus, etc.) angle. (See Figure 2.) 
d )  DISTANCE Sun-Planet distance (SP) and 
Earth-Planet communlcat ion 
distance (EP) ia mill. Lon. 
Clock Angle, i.e., angle between projec- 
tions of the Probe-Canopus and probe- 
object vectors into the plane 11crmal to 
the sun-line (for which CA = 90 O).(See 
Figure 2.) 
e) SUN-EARTH- Sun-Earth-Planet angle (SEP). 
PLANET indicating times of superior 
(SEP 0) and inferror (SW 
" 180") conjunction; SEP 
> 5" is a communicatrons 
constraint. 
Rise time (GMT) of planet through 6' 
horizon mask at DSN Station No. XX. 
(e.g., XX = 14 = GOLDSTONE, 43 = 
CANBERRA, 6 3  = MADRID.) 
r) STATION bw and Set times (GMT) of 
RISEISET planet at 3 DSN Srrtions on 
karth, 6. mask. 
Set time (GMT) of planet through 6" 
horizon mask at DSN Station No. XX. 
JTL TECHNICAL MEMORANDUM J3-7W. VOL. I t  
INCOMING 
*Svrnnorr 
b = IARGEl PARAMETER 
- ORIENTATIO?: OF l 
S - INCOMING LSYMPTOTE 
f = PARALXL TO ECLIPTIC PLANE AND I TO f 
li = l x T  
Figure I .  Dlefinirion of B-Pbne 
Fkure  2. Definirion of Cone and Cbck Attgle 
Clarke, V. C., Jr., Bollman, W. E., Roth, R. T., 
Scholey, W. J., "Design Parameters for Ballistic 
Interplanetary Trajectories Part I. One-way Transfers 
to Mars and Venus," JPL TR 32-77, January 1963. 
Clarke, V. C., Jr., Bollman, W. E., Feritis, P. H., 
Roth, R. Y., "Design Parameters for Ballistic Inter- 
planetary Trajectories Part 11. One-way Transfers to 
Mercury and Jupiter," JPL TR 32-77, January 1966. 
Richards, R. J., Roth, R. Y., "Earth-Mars Trajec- 
loria," JPL TM 33.100, June 1965. 
Kohlhare, C. E., Bollman, W. E., "Trajectory Selec- 
tion Cons~deratiorc; for Voyager M~ssions to Mars 
During the 1971-1977 Time Period," JPL TM 33-210, 
September 1965. 
REFERENCES 
*JPL Internal Document 
Wallace, R. A., "Trajectory Considerations for a 
Mission to Jupiter in 1972," JPL TM 33.375, 
March 1968. 
Roth, R., Zorian, M. D., "Space Research Conic 
Program, Phase III," JPL 900.130, Rev. A. May 
1969.* 
'Ceneral Plot Program," JPL 900-341, Anon., May 
1970.* 
Melbourne, W. C . ,  Mulholland, T. D., Sjogren, W. L.. 
Sturms, F. M., Jr.. "Constants and Related Informa. 
tion for Astrodynam~c Calculations, 1968," JPL 
TR 32- 1306, July 1968. 
N L  TECHNICAL MEMORANDUM 33-7m. VOL. II 

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Mission design data for Venus, Mars, and Jupiter through 1990, volume 2

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