guidance, flight mechanics and trajectory optimization

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where the subscript 70 refers to the condition at the time of periapsis passage. If the nonlinear terms are omitted and the target orbit is circular, Equation (1.66) is identical to Equation (1.49) and a solution for x, y, a can be found in terms of the initial conditions x,, yO, zO, 4, fO, &, by .the use of the transition matrix Equation (1.58). If this solution is de- noted by the subscript 1'~" then The solution to the nonlinear equation will be defined in terms of this solution and small corrections; that is, the solutions to the set (1.66) have the form If this solution set is substituted in (1.66), a set of differential equations for the variables 6~ , 6% , and 62 is produced. This set is then simplified by neglecting the s;naller terms such as x,6x , =6x , ec , eZv, etc. The resulting differential equations are 8.2 +8-i? = 3~52, -3ezc cfm(r-7,) This set of equations is linear in terms of the known. forcing functions; therefore, the solution is straightforward. For convenience the solution is given in two parts indicated by where the superscript 0 denotes the solution when the target orbit is circular, and the superscript e denotes the effect of small eccentricity on the solution. These solutions are given by Sxp=Aof + /f&n z +/~+KI r tAjP& 2 r +/4~cooZ r + A5%. 23
where the superscript p can be either o or e. are then given by 24 The constants A: , B' Cj i '
Page 1 and 2: NASA CONTRA REPORT CTOR GUIDANCE, F
Page 3 and 4: - ..a --.
Page 5 and 6: _- .-- --- I
Page 8: 110 2.1 2.1.1 2.1.2 2.1.3 2.1.3.1 2
Page 11 and 12: . 0 i time difference between a ref
Page 13 and 14: only line-of-sight thrusting is use
Page 15 and 16: 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
Page 25 and 26: 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(
Page 31 and 32: The fundamental matrix for A can be
Page 33: 2.1.5 Approximate Second Order Solu
Page 39 and 40: w” 2 E IOOJ- -100 - 200 AV = 400
Page 41 and 42: cause a significant effect for rend
Page 43 and 44: Figure 2.1 Polar Coordinate System
Page 45 and 46: . will attain, z , can be calculate
Page 47 and 48: 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 and 100:
2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13
Page 101:
4.20 Bakalyar, G., Continuous Thrus
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