guidance, flight mechanics and trajectory optimization

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4. 5 4.6 4.7 I+. 8 4.9 I.. 10 I+.11 4.16 4.17 4.18 4.19 Bender, D. F. and KcCue, B. A., Conditions for Optimal One-Impulse Transfer. AAS.J. L;1 (1966) p 163-158 Strahly, I..*. H.., Utilizing the Phasing Technique in Rendezvous. ARS Preprint 61-2295 Space Flight Report, New Yor!c (Ott 1961) Bendcr D. F., Rendezvous Possibilitie s with the Impulse of Optimum Two-Impulse Transfer.- Adv. in the Astronautical Science Vol. 16 Part 1. p 271-291. LSpace Rendezvous Rescue and Recovery Edwards AFB (Sept. 1963)J Bender, D. F. , @imum Codanar Impulsive Transfer between Elliptic --- Orbits. Aero Space Eng. 21 No. 10 (Oct. 1962) p 44-52 Goldstein, A. A., and Greene, A. H., Johnson, A. T., and Seidman, T. I., _ Fuel O@,imizaticn ___- in Orbital Rendezvous. -.--- AIAA Preprint 63-354 (Guidance and Control Conference, Cambridge, Wass., Aug. 1963) Bryson, A. E. Jr., -____ Linear __--._- Feedback _______-__ Solutions for Minimum Effort - Interceptiog, --- Rcnde_z_vous, and Soft Lands. AIA;\J 3 (1965) p 1542-1544 Paicwonsky, B. H. and :!oodrow. _---- A Studyf - Time Optimal .------- Rendezvous -- in Three ---~ Dimansions (Vol. 1). TDR No. AFFDL-TR-65-20 >/right Patterson ;iFB Jan 1965 (AD 624218) Iu,cIntyre, J. 1.. , xhg_-Pcntxa.gin Ilaximum Principle, NAA/SID 65-1200-7 - (IC2.y 1764) rq’p, ii. E. , Pnntr~+n l.laxirnum Principle. Ch(apter 7 of Optimization Tochn'outis, Ed. Lertman, Academic :.;icss (1962) I.-:cc!lc !;. A ., -L--.-.1;.-_-..--: ~unsili~earizatlo~ -,-- Detcrrxination -.~ -.I___ of $timum Finitg-Thrust --_-- i?rbitil Trnnsf:rs, 210 66-1278 (to be published in AIiiA Journal) liandelsm.7n, ?4. , Optim:11 Free-Space -- F,,, ;~ed-Thrust ---.-.- Trqjectorics Usin? Impulsive ___--- Trajectories _ _-I_--.--. as Z.tnrt5.n:: Iteratives, AIAA Journal 4 (1966) p 1077-1082 Gunckel, T. L., Near Earth Guidance Techniques. UCLA Short Course on Space Navigations and Guidance. (Sept. 1966) Kelbourne, I;. G. and Sauer, G. G., Optimum Interplanetary Rendezvous TraJJcctories _,__.-- - -- with -.- Power Limited October 1962 Vehicles, JPL TK No. 32-226. (Rev. 1) Gobetz, F. :1., A Linear Theory of Optimum Lo:+Thrust Rendezvous Trajectories. AASJ 3 (196';) p 69-76 - Soule P . ::. Rendeivous. , and iiidd, A. T., Terminal Maneuvers for Satellite Ascent Presented at LAS/ARS Joint Meeting, Los Angeles, June 1961 89
4.20 Bakalyar, G., Continuous Thrust Rendezvous Transfers&roximately Mars mtremized, The Martin Company ~-61-22 (August 1961) 4.21 Eskridge, C. D., et. al., An Adaptive Guidance Scheme for Orbital Rendezvous, Paper 43, AAS Southeastern Symposium on Missiles & Aerospace Vehicles Sciences. Huntsville Alabama (December 1966) 4.22 Miller, B. J. and Abbott, A. S., Observation Theory and Sensors, NAA-SID 65-1200-2 (Dee 1965) 4.23 Townsend, G. E., et. al., Boost Guidance squations, NAA-SID 65-1200-8 (Kay 1966) 4.24 Robbins, H. M., An Analytical Study of the Impulsive Approximation, AIAA Journal,& (1966) p 1417-1423 90 NASA-Langley, 1968 - 30 CR-1011
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NASA CONTRA REPORT CTOR GUIDANCE, F
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- ..a --.
Page 5 and 6:
_- .-- --- I
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110 2.1 2.1.1 2.1.2 2.1.3 2.1.3.1 2
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. 0 i time difference between a ref
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only line-of-sight thrusting is use
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2.0 STATE-OF-THE-ART The significan
Page 17 and 18:
Thus in cylindrical coordinates, th
Page 19 and 20:
In this form the equations are vali
Page 21 and 22:
For all the equations given to this
Page 23 and 24:
of inertial directions which are ta
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which form the columns of F must be
Page 27 and 28:
Thus, the solution is written The t
Page 29 and 30:
This matrix is simply written as G(
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The fundamental matrix for A can be
Page 33 and 34:
2.1.5 Approximate Second Order Solu
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where the superscript p can be eith
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w” 2 E IOOJ- -100 - 200 AV = 400
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cause a significant effect for rend
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Figure 2.1 Polar Coordinate System
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. will attain, z , can be calculate
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This equation may now be solved for
Page 49 and 50: If the matrix 121 model discussed'&
Page 51 and 52: One method which can be employed (a
Page 53 and 54: If a collision is to occur at time
Page 55 and 56: The solution to these equations are
Page 57 and 58: Fixed Range: Range-Rate Schedule Ra
Page 59 and 60: The velocity correction, SVtO) repr
Page 61 and 62: (2.17) The solutions of all of thes
Page 63 and 64: I(7) I COMPUTE c (7) =- MISS g-r -1
Page 65 and 66: 0 MOO0 60000 il 20& 40&o hod00 Y (f
Page 67 and 68: Manipulation of the equations invol
Page 69 and 70: 2.4.1 Optimal Stepwise Thrusting As
Page 71 and 72: Note that if it, can occur, this sc
Page 73 and 74: where F (Q) is the matrix given by
Page 75 and 76: where Since 0 and Eq. 4.23 shows th
Page 77 and 78: In contrast, the fuel optimal probl
Page 79 and 80: significantly reducing the out-of-p
Page 81 and 82: Figure 4.3 Velocity Increments to R
Page 83 and 84: If it is assumed that 4~ is constan
Page 85 and 86: Examples of the effectiveness of th
Page 87 and 88: performed using the Pontryagin Maxi
Page 89 and 90: This equation gives the optimum ste
Page 91 and 92: where 2((t) is given by the first e
Page 93 and 94: Cd&t- d&J dt I where Xc9 #II 2 % 9
Page 95 and 96: 3.0 RECOMMENDED PROCEDURES In the p
Page 97 and 98: For the guidance technique which nu
Page 99: 2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13
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