CN107844462A - A kind of interplanetary continuous thrust transfer orbit appraisal procedure - Google Patents

A kind of interplanetary continuous thrust transfer orbit appraisal procedure Download PDF

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CN107844462A
CN107844462A CN201711012650.8A CN201711012650A CN107844462A CN 107844462 A CN107844462 A CN 107844462A CN 201711012650 A CN201711012650 A CN 201711012650A CN 107844462 A CN107844462 A CN 107844462A
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transfer orbit
group
parameter
optimal
optimal transfer
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尚海滨
许铃健
乔栋
喻志桐
秦啸
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Beijing Institute of Technology BIT
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Abstract

The present invention proposes a kind of interplanetary continuous thrust transfer orbit appraisal procedure, solves existing interplanetary the problems such as continuously thrust transfer orbit performance estimating method computational efficiency is low, poor for applicability.Comprise the following steps：Step 1: establish continuous thrust transfer orbit Optimized model；Step 2: generate optimal transfer orbit sample data；Step 3: build the statistics mapping model of optimal transfer orbit performance parameter；Step 4: transfer orbit performance parameter is assessed.

Description

A kind of interplanetary continuous thrust transfer orbit appraisal procedure
Technical field
The present invention relates to a kind of interplanetary continuous thrust transfer orbit appraisal procedure, shifted suitable for interplanetary continuous thrust The rapid evaluation of track, belongs to field of aerospace technology.
Background technology
The continuous propulsion system such as plasma electric propulsion can effectively improve the service efficiency of propellant, reduce detector and turn The fuel consumption needed for journey is moved past, is widely applied in survey of deep space task.However, because continuous thrust shifts rail Road kinetics mechanism is extremely complex, solves highly difficult.At present, carry out depending on during continuous thrust transfer orbit Performance Evaluation Cumbersome numerical optimization, computationally intensive, assessment time length.In the survey of deep space task initial design stage, it usually needs to a large amount of Transfer orbit carry out Performance Evaluation with analysis, this causes the appraisal procedure for being currently based on numerical value optimizing to be difficult to meet task design The demand of person.The fast evaluation method for seeking interplanetary continuous thrust transfer orbit is the hot issue of current scientific and technical personnel's concern One of.
In the appraisal procedure of the interplanetary continuous thrust transfer orbit developed, prior art [1] (Vasile M, Minisci E,Locatelli M.Analysis of Some Global Optimization Algorithms for Space Trajectory Design[J].Journal of Spacecraft&Rockets,2012,47(2):334-344), For the design and evaluation problem of continuous thrust transfer orbit, several conventional global optimization approaches are analyzed and compared for, including Genetic algorithm, differential evolution algorithm, dull basin jump algorithm etc., on this basis, it is proposed that one kind combines differential evolution and calculated The hybrid optimization algorithm of method and dull basin jump algorithm, solve interplanetary continuous thrust transfer orbit design and asked with assessment Topic.The advantages of this method is the advantage for having merged two kinds of optimized algorithms, improves and continuous thrust transfer orbit optimal solution is searched Suo Nengli；Shortcoming is that differential evolution algorithm and dull basin jump algorithm belong to random population optimization method, causes to shift rail The assessment efficiency in road is low, carries out time length required when continuous thrust orbit is assessed.
Prior art [2] (Kluever C A.Efficient Computation of Optimal Interplanetary Trajectories Using Solar Electric Propulsion[J].Journal of Guidance Control&Dynamics,2015,38:1-10), for the evaluation problem of interplanetary continuous thrust transfer orbit, Propose a kind of analytics evaluation method based on exponential curve fitting.Asked for the transfer between interplanetary coplanar circular orbit Topic, this method carry out exponential curve fitting by the orbital data obtained to optimization design, have obtained transfer orbit performance parameter With the analytical expression of the Parameters variations such as preliminary orbit radius, target track radius, thrust size.The advantages of this method is to utilize Analytical expression can realize the rapid evaluation of transfer orbit performance parameter, and shortcoming is that may be only available between coplanar circular orbit The situation of transfer, can not solution by no means between coplanar non-circular orbit transfer orbit evaluation problem.
The content of the invention
The present invention is low, poor for applicability to solve existing interplanetary continuous thrust transfer orbit performance estimating method computational efficiency The problems such as, it is proposed that a kind of interplanetary continuous thrust transfer orbit appraisal procedure.
A kind of interplanetary continuous thrust transfer orbit appraisal procedure, comprises the following steps：
Step 1: establish continuous thrust transfer orbit Optimized model：The Optimized model includes Optimal Parameters, performance indications Δ m and constraints three parts；
Step 2: generate optimal transfer orbit sample data by solving described Optimized model：
Track characteristic parameter X possible range is set as [Xmin,Xmax], it is random according to rule is uniformly distributed within the range Generate N group track characteristic parameters；For each group of track characteristic parameter, using normal scatter pulse method and SQP Algorithm solves to Optimized model, obtains optimal transfer orbit performance indications Δ m*, preserve N group track characteristic parameters and its corresponding The optimal transfer orbit performance parameter Δ m gone out by seismic responses calculated*, form optimal transfer orbit sample data；
Step 3: build the statistics mapping model of optimal transfer orbit performance parameter：
Optimal transfer orbit performance indications Δ m*Mapping model between characteristic parameter X is
Y=Δs m*=f (X)
The optimal transfer orbit sample data generated according to step 2, therefrom randomly selects NTGroup is used as training data, NRGroup As test data；Wherein NT+NR=N, then choose the N in training dataIGroup is used as initial training collection, by NIGroup training set As known conditions, study is trained using standard gaussian process recursion method, is constructed by track characteristic parameter to performance The mapping model of parameter；
Step 4: transfer orbit performance parameter is assessed：
For the track characteristic parameter of detection mission requirement, using the statistics mapping model of step 3 structure to optimal transfer The performance parameter of track is assessed, and obtains optimal transfer orbit performance parameter corresponding to the track characteristic parameter.
Beneficial effects of the present invention：
Data mining ability of the invention based on machine learning is handled sample data, realizes and continuous thrust is shifted The extraction of mapping relations between orbit parameter, construct the statistics between optimal transfer orbit performance parameter and track characteristic parameter Mapping model, the assessment of continuous thrust transfer orbit is then realized using the mapping model.Compared with traditional appraisal procedure, keep away Exempt from cumbersome time-consuming numerical optimization routines, effectively increase the assessment efficiency of continuous thrust transfer orbit.Meanwhile sample data Middle characteristic parameter includes inclination angle and the eccentricity of target celestial body heliocentric orbit, and it is coplanar non-by no means to show that this method can be used in solution Transfer evaluation problem between circular orbit, the scope of application are wider.
Brief description of the drawings
Fig. 1 is a kind of interplanetary continuous thrust transfer orbit appraisal procedure flow chart of the present invention.
Embodiment
Below so that detector is from the assessment of the interplanetary continuous thrust transfer orbit of the earth as an example, with reference to accompanying drawing to this The embodiment of invention elaborates.
A kind of interplanetary continuous thrust transfer orbit appraisal procedure of the invention, embodiment comprise the following steps that：
Step 1, establish continuous thrust transfer orbit Optimized model
For under continuous thrust detector target celestial body A is transferred to by the earth and is realized and celestial body A friendship Meeting problem, establishes continuous thrust transfer orbit Optimized model.If U (t) is continuous thrust control law, the present embodiment in transfer process In, the Optimal Parameters of transfer orbit Optimized model are
Z=[E0,EA,U(t)]
Wherein：E0The heliocentric orbit eccentric anomaly of the earth, E when being set out for detectorATarget celestial body A when being intersected for detector Heliocentric orbit eccentric anomaly；
The performance indications of transfer orbit Optimized model are
J=Δs V → min
Wherein：Δ V is the speed increment needed for detector transfer process；
The constraints of transfer orbit Optimized model is
Wherein：RSAnd RADetector and celestial body A heliocentric position vector when respectively intersecting, VSAnd VAWhen respectively intersecting The heliocentric velocity vector of detector and celestial body A；
Step 2, generate optimal transfer orbit sample data
For the interplanetary continuous thrust transfer process from the earth, task gives the characteristic parameter of optimal transfer orbit For
X=[a, e, i, Ω, ω, m0,P0,η,Isp,tf]
Wherein：A, e, i, Ω, ω are that heliocentric orbit semi-major axis, eccentricity, inclination angle, the ascending node of target celestial body are red respectively Through, argument of perihelion, m0For detector initial mass, P0For continuous propulsion system input power, η is propulsion system operating efficiency, IspFor propulsion system specific impulse, tfFor inter-orbital transfer time.
In the present embodiment, the span of given track characteristic parameter is
a:1.5~2.5AU, e:0~0.25, i:0~15 °, Ω:0~2 π, ω:0~2 π,
P0:5~20kw, Isp:2000~3500s, η:0.5~0.7, m0:1000~2500kg, tf:300~1500days Wherein：1AU is average solar distance, 1AU=149597870km.
According to being uniformly distributed, rule is random to generate 3000 groups of track characteristic parameters within the range.Using normal scatter pulse Method and sequential quadratic programming algorithm obtain optimal transfer respectively to each group of optimal transfer orbit of track characteristic parametric solution Track performance parameter.In this example, it is the speed increment Δ V needed for detector transfer process to choose performance parameter.Therefore, 3000 groups Track characteristic parameter and its corresponding performance parameter Δ V constitute optimal transfer orbit sample data.
Step 3, build the statistics mapping model of track performance parameter
2000 groups of optimal transfer orbit sample datas for meeting detection mission requirement are chosen, then therefrom randomly select 1900 Group is used as training data, and 100 groups are used as test data.200 in training data groups are taken as initial training collection and is passed with 50 groups Increase, study is constantly trained to mapping model.1300 groups of training datas are chosen in this example, it is high using the standard in machine learning This process recursion method, is constructed by the mapping model of track characteristic parameter to performance parameter.
Step 4, rapid evaluation is carried out to transfer orbit performance parameter
For the track characteristic parameter of mission requirements in this example, the statistics mapping model built using step 3 can be to most The performance parameter of excellent transfer orbit carries out rapid evaluation.The performance parameter of 100 transfer orbits of the test data, which solves, to be used Traditional Nonlinear Programming Algorithm need to take 150min, and time-consuming less than one second, worst error 3.34% is calculated using mapping model, The sample performance parameter that the track characteristic parameter corresponds to optimal transfer orbit is 7.59km/s, the performance parameter that mapping model calculates For 7.84km/s.

Claims (1)

1. a kind of interplanetary continuous thrust transfer orbit appraisal procedure, it is characterised in that comprise the following steps：
Step 1: establish continuous thrust transfer orbit Optimized model：The Optimized model includes Optimal Parameters, performance indications Δ m With constraints three parts；
Step 2: generate optimal transfer orbit sample data by solving described Optimized model：
Track characteristic parameter X possible range is set as [Xmin,Xmax], generate at random according to being uniformly distributed rule within the range N group track characteristic parameters；For each group of track characteristic parameter, using normal scatter pulse method and sequential quadratic programming algorithm Optimized model is solved, obtains optimal transfer orbit performance indications Δ m*, preserve N group track characteristic parameters and its corresponding by excellent Change the optimal transfer orbit performance parameter Δ m that model calculates*, form optimal transfer orbit sample data；
Step 3: build the statistics mapping model of optimal transfer orbit performance parameter：
Optimal transfer orbit performance indications Δ m*Mapping model between characteristic parameter X is
Y=Δs m*=f (X)
The optimal transfer orbit sample data generated according to step 2, therefrom randomly selects NTGroup is used as training data, NRGroup conduct Test data；Wherein NT+NR=N, then choose the N in training dataIGroup is used as initial training collection, by NIGroup training set conduct Known conditions, study is trained using standard gaussian process recursion method, is constructed by track characteristic parameter to performance parameter Mapping model；
Step 4: transfer orbit performance parameter is assessed：
For the track characteristic parameter of detection mission requirement, using the statistics mapping model of step 3 structure to optimal transfer orbit Performance parameter assessed, obtain optimal transfer orbit performance parameter corresponding to the track characteristic parameter.
CN201711012650.8A 2017-10-26 2017-10-26 A kind of interplanetary continuous thrust transfer orbit appraisal procedure Pending CN107844462A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110806212A (en) * 2019-11-12 2020-02-18 北京理工大学 Asteroid detection small thrust transfer trajectory optimization method based on successive convex programming
CN111382876A (en) * 2020-02-28 2020-07-07 上海航天控制技术研究所 Method and system for acquiring initial value of ground fire transfer orbit design based on evolutionary algorithm
CN112231929A (en) * 2020-11-02 2021-01-15 北京空间飞行器总体设计部 Evaluation scene large sample generation method based on orbit parameters

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110806212A (en) * 2019-11-12 2020-02-18 北京理工大学 Asteroid detection small thrust transfer trajectory optimization method based on successive convex programming
CN111382876A (en) * 2020-02-28 2020-07-07 上海航天控制技术研究所 Method and system for acquiring initial value of ground fire transfer orbit design based on evolutionary algorithm
CN111382876B (en) * 2020-02-28 2023-09-29 上海航天控制技术研究所 Ground fire transfer orbit design initial value acquisition method and system based on evolutionary algorithm
CN112231929A (en) * 2020-11-02 2021-01-15 北京空间飞行器总体设计部 Evaluation scene large sample generation method based on orbit parameters
CN112231929B (en) * 2020-11-02 2024-04-02 北京空间飞行器总体设计部 Evaluation scene large sample generation method based on track parameters

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Application publication date: 20180327