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Method for rapidly estimating long-term orbital rendezvous optimal speed increment under J2 perturbation

A technology of optimal speed and orbit rendezvous, applied in the field of aerospace navigation control, can solve the problem of high estimation accuracy

Active Publication Date: 2020-02-14
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

This method solves the problem of quickly estimating the optimal rendezvous velocity increment without an exact solution, and the estimation accuracy is high

Method used

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  • Method for rapidly estimating long-term orbital rendezvous optimal speed increment under J2 perturbation
  • Method for rapidly estimating long-term orbital rendezvous optimal speed increment under J2 perturbation
  • Method for rapidly estimating long-term orbital rendezvous optimal speed increment under J2 perturbation

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Embodiment Construction

[0084] refer to figure 1 , is a flow chart of the present invention, and the present invention provides a fast estimation method for the optimal velocity increment of long-term orbital rendezvous under J2 perturbation.

[0085] Step 1, calculate the orbital element difference between the spacecraft and the target at the moment of rendezvous;

[0086] Known mission spacecraft and target at transfer start time t 0 The six orbital elements of are [a c (t 0 ),e c (t 0 ),i c (t 0 ),Ω c (t 0 ), ω c (t 0 ), M c (t 0 )] and [a t (t 0 ),e t (t 0 ),i t (t 0 ),Ω t (t 0 ), ω t (t 0 ), M t (t 0 )].

[0087] where a c (t 0 ),e c (t 0 ),i c (t 0 ),Ω c (t 0 ), ω c (t 0 ), M c (t 0 ) respectively represent the spacecraft at the transfer start time t 0 The six orbital elements of , respectively are the semi-major axis of the orbit, the orbital eccentricity, the orbital inclination, the right ascension of the ascending node, the periapsis angle, and the mean...

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Abstract

The invention discloses a method for rapidly estimating a long-term orbital rendezvous optimal speed increment under J2 perturbation. The method includes the steps of calculating the orbital element difference of a non-maneuvering spacecraft and a target at the rendezvous moment, calculating an optimal control amount when only the ascending node ascensional difference is eliminated, substituting the optimal control amount as the initial value into a control amount optimizing model for eliminating the semi-major axis, dip angle and ascending node ascensional difference at the same time to obtain a new optimal control amount, modifying the control amount according to the phase difference in an orbital plane, modifying the control amount according to the eccentricity ratio vector difference,and finally obtaining the estimated optimal rendezvous speed increment. The method realizes the purpose of rapidly estimating the optimal rendezvous speed increment when precise solution is not neededand is high in estimating precision and suitable for the situations with large initial ascending node ascensional difference from a target orbit and small element differences from other orbits.

Description

technical field [0001] The invention belongs to the technical field of aerospace navigation control, and in particular relates to a method for quickly estimating the optimal speed increment of long-term orbital rendezvous under J2 perturbation. Background technique [0002] In low earth orbit, the J2 term is the most important perturbing term. In the optimization design of the rendezvous orbit, the influence of the J2 term must be considered, but the calculation amount will increase correspondingly compared with the two-body dynamics model. [0003] Most of the existing methods for solving the optimal velocity increment of orbital rendezvous are numerical optimization algorithms, and it takes at least several minutes or even several hours to calculate a single multi-pulse orbital transfer. In some orbit design applications, the size and direction of each pulse may not be concerned, and only the total velocity increment needs to be known. In this case, a fast and accurate es...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24G01P3/00
CPCB64G1/242G01P3/00
Inventor 罗亚中黄岸毅李恒年伍升钢张进杨震
Owner NAT UNIV OF DEFENSE TECH
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