Method and system for quickly generating deep-space small-thrust flying-over orbit
A small thrust and orbital technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as slow calculation speed, large calculation amount, and reduce calculation amount, and achieve the effect of avoiding the global optimization process
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[0026] Example one
[0027] As attached figure 1 As shown, the embodiment of the present invention provides a method for rapidly generating a deep space small thrust fly over orbit, which includes the following steps:
[0028] S1, given starting point position r 0 And the target point position r f And starting point speed v 0 , The flight time from the starting point to the target point T = T * , And initialize the current time t 0 And the integrated time variable Σ t ;
[0029] S2, by solving the Lambert problem, the velocity increment Δv is obtained 1 ;
[0030] S301, in the speed increment amplitude||Δv 1 || When less than the impulse threshold ε, increase the speed by Δv 1 Converted into a small thrust vector F; when the above-mentioned speed increment amplitude meets the set impulse threshold ε, it means that the calculation program of this scheme has a solution, and the small thrust vector can be obtained according to Newton’s second law and can be based on the small thrust Vect...
Example Embodiment
[0035] Example two
[0036] As a further improvement of the first embodiment, continue to refer to figure 1 :
[0037] S1, given starting point position r 0 And the target point position r f And starting point speed v 0 , The flight time from the starting point to the target point T = T * , And initialize the current time t 0 And the integrated time variable Σ t ;
[0038] S2, by solving the Lambert problem, the velocity increment Δv is obtained 1 ;
[0039] S302, in the speed increment amplitude||Δv 1 || When greater than or equal to the impulse threshold ε, and meets When, output small thrust vector:
[0040] Among them, F max Is the maximum small thrust that the propulsion system can output, m is the mass of the spacecraft, and δt is the integration time;
[0041] S4. Perform numerical integration of the time length δt on the first-order dynamics equations of the classic spacecraft two-body orbit under the action of the small thrust vector, and update the starting point position r...
Example Embodiment
[0045] Example three
[0046] As a further improvement of the first embodiment, continue to refer to figure 1 :
[0047] S1, given starting point position r 0 And the target point position r f And starting point speed v 0 , The flight time from the starting point to the target point T = T * , And initialize the current time t 0 And the integrated time variable Σ t ;
[0048] S2, by solving the Lambert problem, the velocity increment Δv is obtained 1 ;
[0049] S303, in the speed increment amplitude||Δv 1 || When greater than or equal to the impulse threshold ε, and does not meet When, output small thrust vector:
[0050] Among them, F max Is the maximum small thrust that the propulsion system can output, m is the mass of the spacecraft, and δt is the integration time;
[0051] S4. Perform numerical integration of the time length δt on the first-order dynamics equations of the classic spacecraft two-body orbit under the action of the small thrust vector, and update the starting point ...
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