Optimization method of spacecraft orbital engine installation parameters based on Runge-Kutta algorithm
An optimization method and a technology of installation parameters, which are applied in the directions of instruments, calculations, electrical digital data processing, etc., can solve the problem of large interference torque in the design of the solution
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[0171] Input conditions (known conditions)
[0172] Engine heat label data (thrust vector and action point position vector), as shown in Table 1:
[0173] Table 1
[0174]
[0175]
[0176] The mechanical dimensions of the engine (the distance from the theoretical center of the engine nozzle to the theoretical center of the mounting flange) are shown in Table 2:
[0177] Table 2
[0178]
[0179] The position of the engine bracket is shown in Table 3:
[0180] table 3
[0181]
[0182]
[0183] Spacecraft centroid coordinate data As shown in Table 4:
[0184] Table 4
[0185]
[0186] (2) According to the requirements of the overall design of the spacecraft, the objective function of the optimal design of the engine installation parameters is constructed. The vector of the engine thrust pointing to the target point T is shown in Table 5:
[0187] table 5
[0188]
[0189] (3) Specific solution:
[0190] (a) According to step (2), calculate the v...
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