CN-122019915-A - Multi-turn double-pulse track transfer minimum speed increment estimation method and system under J2 perturbation

CN122019915ACN 122019915 ACN122019915 ACN 122019915ACN-122019915-A

Abstract

The invention particularly relates to a multi-circle double-pulse track transfer minimum speed increment estimation method and system under J2 perturbation, wherein the method comprises the steps of uniformly representing an initial track state as six spring points taking flat longitude as a phase quantity, determining a limited transfer circle number search window by utilizing flat longitude drift characteristics and pulse capacity aiming at a transfer structure of a first pulse, a middle section drift and a second pulse, constructing a closed equation constraint system of total variation=first pulse variation+middle section drift variation+second pulse variation, ensuring track state to be strictly closed, decomposing the pulse into tangential components, normal components and radial components to cooperatively solve, realizing phase closed loop by updating a half-path increment, and carrying out low-dimensional nonlinear optimization in limited circle numbers to quickly obtain minimum speed increment estimation. The method and the device remarkably improve the calculation efficiency while ensuring the precision, and are suitable for large-scale sequence optimization in the near-earth orbit multi-target access task.

Inventors

Yan Xunliang
NING XIN
ZHANG SHUMING
WANG ZIHANG
WANG YUXIN
Cao Xiuyang
LIU SUYI
MA SHICHAO
LIAN XIAOBIN
WANG YUAN

Assignees

西北工业大学

Dates

Publication Date: 20260512
Application Date: 20251229

Claims (10)

1. A method for estimating minimum speed increment of multi-turn double pulse orbit transfer under J2 perturbation, the method comprising: S1, initializing, namely acquiring initial orbit numbers, transfer time and single pulse speed increment upper limit constraint of a service spacecraft and a target spacecraft, converting the initial orbit numbers into six spring point numbers taking a flat longitude as a phase quantity to respectively obtain a starting point state vector and an end point state vector, wherein the six spring point numbers are expressed as Wherein Is a track semi-diameter, Is of eccentricity A component of, Is of eccentricity A component of, Is the inclination angle A component of, Is the inclination angle A component of, Is a flat longitude; s2, deducing and calculating six track numbers by using average spring points And (3) with Wherein, the method comprises the steps of, To serve the flat longitude rate of change of the initial orbit of the star, Sensitivity to radius for a flat longitude rate of change; s3, determining a limited turn search window, namely calculating the maximum achievable additional transfer turns N max based on the single pulse speed increment upper limit constraint, the starting point state vector and the sensitivity of the flat longitude drift rate to the half-diameter, and using And N is the range of the integer as the limited number of turns search window; And S4, traversing the turns and optimizing and solving, wherein for each candidate transfer turn N in the search window: S4.1, based on the phase closed loop requirement, preliminarily estimating the semi-diameter increment caused by the first pulse by using a phase closed equation containing the number of turns N ; S4.2, using first pulse to make four variables except for semi-diameter and flat longitude in six spring points 、、、、 Amount of change in (2) 、、、 As an optimization variable; s4.3, calculating tangential, normal and radial velocity increment components of the first pulse according to a perturbation kinematic equation of six spring points based on the half-diameter increment required by the first pulse and the current optimized variable value 、、 And obtaining the instantaneous state after the first pulse; S4.4, pushing the number of eccentric vector complex numbers and the number of track plane orientation complex numbers in the instantaneous state after the first pulse by using an analytic formula of complex plane rotation mapping, and calculating the end state of the drift section after the transfer time and before the second pulse; S4.5, calculating the change quantity of the second pulse to six spring points required for reaching the end point state based on the closed equation constraint of total change quantity = first pulse change quantity + middle section drift change quantity + second pulse change quantity, and further calculating tangential, normal and radial velocity increment components of the second pulse 、、 ; S4.6 increasing the half-diameter by the first pulse estimated in step S4.1 Updating by using the actual pulse components calculated in the steps S4.3 and S4.5 to obtain updated semi-path increment And re-executing the steps S4.3 to S4.5 based on the step, and performing iterative correction; s4.7, constructing an objective function based on the two pulse speed increments, solving a variable optimal value for minimizing the objective function by adopting a nonlinear optimization algorithm in the feasible domain of the optimized variable, and recording the corresponding minimum speed increment; S5, outputting a global optimal estimation result, namely comparing the minimum speed increment corresponding to all the candidate turns N, and taking the minimum value as a final rapid estimation value of the total speed increment of the track transfer section.
2. The method according to claim 1, characterized in that the calculation of the maximum achievable additional number of transfer turns N max is in particular: In the formula, A flat longitude change rate of an initial orbit of a service spacecraft, The semi-path of the service spacecraft in the initial orbit; is a mathematical substitution; A maximum tangential velocity increment that can be provided for a single pulse engine; total transfer time for the service spacecraft to the target spacecraft; the change in longitude of the total level from the service spacecraft to the target spacecraft; The speed of the service spacecraft in the initial orbit; N max is a non-zero integer, if N max is calculated to be smaller than zero, it proves that the pulse has no solution under the current DeltaV t_max , the maximum tangential velocity component DeltaV t_max needs to be increased, meanwhile, attention needs to be paid, deltaV t_max is not excessively large, otherwise N max can be excessively large, and the calculation efficiency is possibly affected.
3. The method of claim 1, wherein the preliminary estimate of the half-path increment required to be caused by the first pulse The method specifically comprises the following steps: Wherein, the Is the average angular velocity of the service star.
4. The method of claim 1, wherein the tangential direction is used to match a semi-path with an average motion, the normal direction is used to correct a track plane and calculate a flat longitude variation, and the radial direction is balanced in a closed-form manner and the adaptive regularization is superimposed to resolve an in-plane residual.
5. The method of claim 1, wherein the updated half-path increment The method specifically comprises the following steps: Wherein, the 、 The flat longitude changes generated by the first pulse and the second pulse respectively.
6. The method of claim 1, wherein the objective function is expressed as: 。
7. a multi-turn double pulse orbit transfer minimum velocity delta estimation system under J2 perturbation, comprising: the initialization module is used for acquiring and processing input parameters, including initial orbit numbers of the service spacecraft and the target spacecraft, transfer time and single pulse speed increment upper limit constraint, and converting the initial orbit numbers and the transfer time into six spring point number states based on flat longitude; the preprocessing module is used for calculating initial phase drift and determining a limited transfer circle number search window according to pulse capacity and phase sensitivity; the core estimation module is used for traversing the candidate transfer turns in the search window, and for each turn, the following operations are executed: estimating a semi-path increment initial value of the first pulse based on the phase closed loop requirement; taking the six number change of partial spring points caused by the first pulse as an optimization variable; calculating the velocity increment component of the twice pulse, wherein the middle section drift adopts complex plane rotation mapping to carry out analysis and propulsion; solving a second pulse increment by using a closed equation constraint relation; Correcting the semi-path increment estimation through iterative updating; invoking a nonlinear optimizer, solving the optimal first pulse increment by taking the total speed increment minimization as a target, and recording the minimum estimated value under the circle number; And the output module is used for comparing the minimum estimated values under all the candidate turns and outputting a global optimal total speed increment estimated result.
8. A storage medium having stored thereon a computer program which, when executed by a processor, implements a multi-turn double pulse orbit transfer minimum velocity delta estimation method under J2 perturbation according to any one of claims 1 to 6.
9. A computer program product comprising a computer program which, when executed by a processor, implements the multi-turn double pulse orbit transfer minimum velocity delta estimation method under J2 perturbation according to any one of claims 1to 6.
10. An electronic device, comprising: Processor, and A memory for storing executable instructions of the processor; Wherein the processor is configured to implement the multi-turn double pulse orbit transfer minimum velocity delta estimation method under J2 perturbation of any one of claims 1 to 6 via execution of the executable instructions.

Description

Multi-turn double-pulse track transfer minimum speed increment estimation method and system under J2 perturbation Technical Field The invention relates to the technical field of aerospace navigation control, in particular to a multi-circle double-pulse orbit transfer minimum speed increment estimation method and system under J2 perturbation. Background The near-earth orbit multi-target access task has the characteristics of multiple targets, long time domain and strict window, and a service spacecraft needs to access a plurality of targets in sequence in a given epoch to finish multi-section transfer and reduce the total speed increment as much as possible. The sequencing of the sequences directly determines task time consumption and fuel cost, and the upper-layer sequence optimization often needs thousands of evaluations of the transfer cost between any two targets. If the inter-target transfer is regarded as multi-pulse transfer, each evaluation is equivalent to solving a parameter optimization problem with time constraint, and numerical optimization can give high-precision speed increment, but dense propagation and repeated iteration are introduced, and the calculation load grows exponentially with the target number and the candidate time window, so that unacceptable time complexity occurs in upper-layer sequence optimization. Therefore, developing a method that can rapidly and accurately estimate the speed increment between two targets at a given origin-destination orbit and transfer duration is a key basis for supporting large-scale sequence design and task real-time decision. The existing rapid estimation technology is mainly of three types, namely a database method, the database method is rapid in online retrieval, but the construction of the database method depends on a large number of track optimization samples, the database generation cost is extremely high, the coverage dimension is limited, the scene migration capability is weak, and the database method is difficult to adapt to changeable track design requirements. Secondly, a machine learning method is adopted, the method is based on a neural network to realize rapid inference, but the method relies on a large-scale labeling data set, training takes tens of hours, a model is severely limited by a training scene, accuracy rapidly deteriorates when track parameters deviate from sample distribution, and generalization capability is insufficient. Thirdly, the analysis/semi-analysis method directly establishes a mapping relation of 'track root number difference-speed increment' from the approximate of perturbation dynamics. However, the representative work of this type of approach is mostly based on the near-circular orbit or small-change assumption, which is coarser for the long-term perturbation of J 2 and the orbital plane-phase coupling effect. When the method is used for processing the track transfer working conditions of a low-track long time domain, multi-circle detouring and medium-high eccentricity, obvious phase deviation accumulation and track surface misjudgment can be generated due to neglecting J 2 perturbation or performing excessive rounding reduction, so that systematic underestimation of speed increment or infeasibility of a scheme is caused, and the application range and robustness of the method are severely limited. Therefore, when the current technology system is used for solving the problem of double-pulse multi-turn track transfer in the full eccentricity range under the J2 perturbation, a method for uniformly describing the phase evolution and the Δv fast estimation with closed balancing and efficient searching capability while maintaining high computing efficiency is still lacking, and in addition, development of a new generation estimation strategy is needed to support the actual engineering requirement of large-scale on-orbit task sequence optimization. It should be noted that the information disclosed in the above background section is only for enhancing understanding of the background of the invention and thus may include information that does not form the prior art that is already known to those of ordinary skill in the art. Disclosure of Invention Aiming at the problems of low calculation efficiency or limited applicability and the like when the existing track transfer DeltaV estimation method is used for processing large-eccentricity tracks and multi-circle J 2 perturbation accumulation, the invention provides a multi-circle double-pulse track transfer DeltaV rapid estimation method and system based on six-number J2 perturbation of spring points. Other features and advantages of the invention will be apparent from the following detailed description, or may be learned by the practice of the invention. According to a first aspect of the present invention, there is provided a method for estimating minimum speed increment of multi-turn double pulse orbit transfer under J2 perturbation, the method comprising: S1, initializ