CN104176273B - Target asteroid selection method for manned asteroid exploration - Google Patents
Target asteroid selection method for manned asteroid exploration Download PDFInfo
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- CN104176273B CN104176273B CN201410336521.4A CN201410336521A CN104176273B CN 104176273 B CN104176273 B CN 104176273B CN 201410336521 A CN201410336521 A CN 201410336521A CN 104176273 B CN104176273 B CN 104176273B
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Abstract
The invention discloses a target asteroid selection method for manned asteroid exploration. The method comprises four steps as follows: Step 1: determining constraint conditions for target asteroid preliminary selection; Step 2: screening an asteroid data base according to the constraint conditions which are determined in Step 1 and used for target asteroid preliminary selection to obtain primarily-selected targets; Step 3: performing primarily-selected asteroid orbit design and related calculation, including design of task orbits, calculation of velocity increments, search of launch windows and calculation of task periods; Step 4: performing target asteroid optimization, including a target asteroid optimization model and solutions. The method involves a strict target asteroid preliminary selection process and a target asteroid optimization mathematical model, so that a target asteroid which has the project realizability and the exploration value can be provided.
Description
Technical field
The present invention relates to a kind of target satellite choosing method of manned ASTEREX, can filter out engineering based on the method can
The realisation target satellite having both with scientific value, belongs to field of aerospace technology.
Background technology
Asteroidal manned exploration has particularly significant and special meaning.Because spacefarer has subjective initiative, can
To carry out site inspection, the arrangement of scientific instrument, the sample collection and sample tentatively detected event such as identification, therefore can be preferably
Complete asteroidal detection mission.The selection of target satellite is the matter of utmost importance that manned ASTEREX faces and the key that need to be solved
Technology.It is existing to be sieved according to asteroidal orbit parameter with regard to most of the method that manned ASTEREX target satellite is chosen
Choosing, have ignored asteroidal physical characteristics, and the composition of screening process qualitative analyses is more, without clearly general screening bar
Part.Though other some screening techniques consider asteroidal detection value, be also qualitatively analysis and by it is asteroidal can
Consider simultaneously with detection value up to property so that screening process is complex.This in the case where asteroid quantity is very huge, nothing
Doubt the difficulty that increased screening.
The content of the invention
1st, purpose
The invention aims to overcoming, existing choosing method qualitative analyses are more, screening process is complex and science
Property relatively low defect, propose a kind of target satellite choosing method of manned ASTEREX, it is a kind of strict target satellite primary election
Flow process and target satellite optimization of mathematical models, can provide accordingly the target satellite that engineering realizability has both with detection value.
2nd, technical scheme
In order to realize foregoing invention purpose, the present invention is employed the following technical solutions.
A kind of target satellite choosing method of manned ASTEREX of the present invention, mainly including following step：
Step one：Determine the constraints of target satellite primary election
The constraints of the target satellite primary election is by asteroid orbit parameter, asteroidal absolute magnitude and asteroidal
Self-rotary cycle is constituted, and is coordination between each several part.
Semi-major axis a of the asteroid orbit parameter comprising asteroid track, eccentric ratio e and orbit inclination angle i.It is by delivering
The carrying capacity of rocket is determined, is the primary factor of target satellite primary election consideration.
The asteroid absolute magnitude is determined by asteroidal size, it is however generally that, asteroid size is bigger, and its is absolute
Magnitude is less, and the condition can determine according to requirement of the manned exploration to asteroid size.
The asteroid self-rotary cycle includes self-rotary cycle lower limit and self-rotary cycle upper limit two parts.Both are coordinations.
The self-rotary cycle lower limit can be determined that the spin is all by the asteroid relation equal with gravitation to the centrifugal force of its surface object
The phase upper limit can be determined by the correlational study of asteroid thermal model.
Step 2：Preliminary screening
The constraints of the target satellite primary election determined using step one is screened to asteroid data base, draws primary election mesh
Mark.
Step 3：Primary election star orbit Design and correlation computations
The orbit Design and correlation computations include that the design of task track, the calculating of speed increment, launch window are searched
The calculating of rope and duty cycle, there is certain coupled relation between each several part.
Being designed as from earth parking orbit for the task track, escapes along the hyperbola with earth centroid as focus
Gravitational effects ball, reaches asteroid and intersects therewith, in asteroid table along the ellipse with sun barycenter as focus afterwards
Some days are resident in face, afterwards again along the oval edge for reaching gravitational effects ball with sun barycenter as focus, entirely
Task track includes the earth's core escape section and two day heart transfer legs.
The calculating of the speed increment need to be analyzed solution using corresponding Orbit Transformation strategy.
The search of the launch window is obtained using the search of existing optimizing algorithm, such as algorithm, the intelligent algorithm based on gradient
Deng.
The calculating of the duty cycle can be calculated in the lump in the calculating process of launch window and speed increment.
Step 4：Target satellite is preferred
The target satellite preferably comprises target satellite optimization model and solution.
The target satellite optimization model includes optimized variable and optimization aim two parts, is coordination between each several part.
The optimized variable includes the speed increment Δ v needed for detection, duty cycle Δ T, asteroidal spectrum types, little row
Whether the detection experience in advance of star, asteroid is to threaten asteroid over the ground, and whether asteroidal self-rotary cycle is known.Each several part it
Between be coordination.
The optimization aim is maximum for the corresponding score sum of above-mentioned six optimized variables of target satellite, i.e., asteroid possess compared with
Little speed increment and duty cycle, are provided simultaneously with the comprehensive of larger scientific value, engineering realizability and detection value
Divide highest.
The solution is and draws optimal detection target using above-mentioned target satellite optimization model analytical calculation.
3rd, advantage and effect
The selection of manned ASTEREX target satellite is divided into " primary election " and " preferred " two big process by the present invention, by " just
Choosing " can primarily determine that some targets for meeting basic constraint, then primary election star be carried out again preferably, most preferably visit so as to drawing
Survey target.Prior art is contrasted, main advantages of the present invention are：Possess strict screening process and scientific higher screening mould
Type, can provide the target satellite that detection value has both with engineering realizability.
Description of the drawings
Fig. 1 is the primary election flow chart of target satellite
Fig. 2 is the preferred flow charts of target satellite
Fig. 3 is the total design screening process figure of the present invention
Symbol description is as follows in figure：
The semi-major axis of a, asteroid track；The eccentricity of e, asteroid track；The orbit inclination angle of i, asteroid track；
The value range of H, absolute magnitude；T, asteroidal self-rotary cycle.
Specific embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
As seen from Figure 3, the present invention provides a kind of target satellite choosing method of manned ASTEREX, and it includes following
Several steps：
Step one：Determine the constraints of target satellite primary election
The constraints of the target satellite primary election is by asteroid orbit parameter, asteroidal absolute magnitude and asteroidal
Self-rotary cycle is constituted, and is coordination between each several part.
Semi-major axis a of the asteroid orbit parameter comprising asteroid track, eccentric ratio e and orbit inclination angle i.It is by delivering
The carrying capacity of rocket is determined, is the primary factor of target satellite primary election consideration.A in the present embodimentmin<a<amax, e<min{e1,
e2, i<3°.Wherein, amin,amax,e1,e2Computing formula be
In formula, μ is solar gravitation constant, and r is radius when assuming that the track that revolves around the sun of the earth is circle, vETo visit
Survey device from earth parking orbit escape into gravitational effects ball edge when the earth in day heart ecliptic inertial coodinate system
Speed, C3 is the amount of the carrying capacity for characterizing carrier rocket.
The asteroid absolute magnitude indicates requirement of the manned exploration to asteroid size indirectly, can determine that according to following formula
The scope of asteroid absolute magnitude：
In formula, msunFor the apparent magnitude of the sun, A for asteroid surface albedo, R is asteroid radius, d0For a day
Literary unit.(1AU=1.496 × 108km)。
The asteroid self-rotary cycle includes self-rotary cycle lower limit and self-rotary cycle upper limit two parts.Both are coordinations.
The self-rotary cycle lower limit can utilize the asteroid relation equal with gravitation to the centrifugal force of its surface object and consider certain
Safety coefficient determine, i.e.,
In formula, G is universal gravitational constant, and M is asteroidal quality, and m is the quality of asteroid surface object, and T is little row
The self-rotary cycle of star.
The self-rotary cycle upper limit can be by the detection of the correlational study of asteroid thermal model and manned ASTEREX task
Requirement of the device temperature control system to asteroid surface environment determines.
Step 2：Preliminary screening
Such as Fig. 1, the constraints of the target satellite primary election determined using step one is screened to asteroid data base, is drawn
Primary election target.
Step 3：Primary election star orbit Design and correlation computations
The orbit Design and correlation computations include that the design of task track, the calculating of speed increment, launch window are searched
The calculating of rope and duty cycle, there is certain coupled relation between each several part.
In the present embodiment, the task track is designed as：From height for 300km earth parking orbit, along
Hyperbola escape gravitational effects ball with earth centroid as focus, reaches afterwards along the ellipse with sun barycenter as focus
Asteroid is simultaneously intersected therewith.Some days are resident on asteroid surface, are arrived again along the ellipse with sun barycenter as focus afterwards
Up to the edge of gravitational effects ball.Whole task track is comprising the earth's core escape section and two day heart transfer legs.
The calculating of the speed increment need to be analyzed solution using corresponding Orbit Transformation strategy.In the present embodiment, day
Heart transfer leg adopts Lambert Orbit Transformation strategies.Required total speed increment comprising the acceleration pulse of earth parking orbit and
During asteroid rendezvous become rail pulse and leave asteroid into day heart transfer orbit section change rail pulse.
The search of the launch window is obtained using the search of existing optimizing algorithm, such as algorithm, the intelligent algorithm based on gradient
Deng.In the present embodiment, launch window is obtained using the Genetic algorithm searching with ability of searching optimum.
The calculating of the duty cycle can be calculated in the lump in the calculating process of launch window and speed increment.
Step 4：Target satellite is preferred
The target satellite preferably comprises target satellite optimization model and solution.
The target satellite optimization model includes optimized variable and optimization aim two parts, is coordination between each several part.
The optimized variable is：
X=[x1,x2,x3,x4,x5,x6] (4)
In formula,
x1Total speed increment, km/s, x needed for the detection of-target satellite1Value it is less, target satellite detection value is higher；
x2- target satellite detection mission cycle, day, x2Value it is less, the detection of target satellite value is higher；
x3The spectrum types of-target satellite, the asteroid for preferentially choosing C, S, X class is detected；
x4The detection experience in advance of-target satellite, preferential detection has the asteroid for detecting experience in advance；
x5Whether-target satellite is PHAs, and preferential detection is the asteroid of PHAs；
x6Whether-target satellite self-rotary cycle is, it is known that asteroid known to preferential detection self-rotary cycle.
The optimization aim is：
Maxf (x)=c1(x1)+c2(x2)+c3(x3)+c4(x4)+c5(x5)+c6(x6) (5)
In formula, cj(xj) (j=1,2,3,4,5, are 6) the corresponding self-defining function of above-mentioned six optimized variables, and it is actually
" score " of the asteroid in terms of above-mentioned six variables is represented, function f (x) is asteroidal PTS.Score is higher, little
The detection priority of planet is higher.
The solution is, according to above-mentioned target satellite optimization model, with reference to Fig. 2, to each primary election target, it to be calculated respectively
Optimization design variable and respective function value, be finally added and obtain the value of object function f (x), the value of f (x) is bigger,
The detection priority of the target satellite is higher.This to each primary election target satellite by the way of a kind of " scoring " equivalent to " being beaten
Point ", " score " highest is optimal detection target, and " score " is higher, and the priority of detection is higher.
So far the primary election of manned ASTEREX target satellite is completed, whole flow process is as shown in Figure 3.
Claims (1)
1. a kind of target satellite choosing method of manned ASTEREX, it is characterised in that：It includes following step：
Step one：Determine the constraints of target satellite primary election
The constraints of the target satellite primary election is by asteroid orbit parameter, asteroidal absolute magnitude and asteroidal spin
Cycle constitutes, and is coordination between each several part；
Semi-major axis a of the asteroid orbit parameter comprising asteroid track, eccentric ratio e and orbit inclination angle i, the asteroid rail
The semi-major axis a in road, eccentric ratio e and orbit inclination angle i determine by the carrying capacity of carrier rocket, is the head that target satellite primary election considers
Want factor；
The asteroid absolute magnitude is determined that asteroid size is bigger by asteroidal size, and its absolute magnitude is less, the mesh
Requirement of the constraints of mark star primary election according to manned exploration to asteroid size determines；
The asteroid self-rotary cycle includes self-rotary cycle lower limit and self-rotary cycle upper limit two parts, and both are coordinations；Should be certainly
Revolve period limit to be determined by the asteroid relation equal with gravitation to the centrifugal force of its surface object, the self-rotary cycle upper limit
Determined by the correlational study of asteroid thermal model；
Step 2：Preliminary screening
The constraints of the target satellite primary election determined using step one is screened to asteroid data base, draws primary election target；
Step 3：Primary election star orbit Design and correlation computations
The orbit Design and correlation computations include the design of task track, the calculating of speed increment, the search of launch window with
And the calculating of duty cycle, there is certain coupled relation between each several part；
The task track is designed as from earth parking orbit, along the hyperbola escape earth with earth centroid as focus
Gravitation affects ball, reaches asteroid along the ellipse with sun barycenter as focus afterwards and intersects therewith, stays on asteroid surface
Plural day is stayed, afterwards again along the oval edge for reaching gravitational effects ball with sun barycenter as focus, whole task
Track includes the earth's core escape section and two day heart transfer legs；
The calculating of the speed increment need to be analyzed solution using corresponding Orbit Transformation strategy；
The search of the launch window is obtained using the search of existing optimizing algorithm；
The calculating of the duty cycle is calculated in the lump in the calculating process of launch window and speed increment；
Step 4：Target satellite is preferred
The target satellite preferably comprises target satellite optimization model and solution；
The target satellite optimization model includes optimized variable and optimization aim two parts, is coordination between each several part；
The optimized variable includes the speed increment Δ v needed for detection, and duty cycle Δ T, asteroidal spectrum types are asteroidal
Experience is detected in advance, and whether asteroid is to threaten asteroid over the ground, and whether asteroidal self-rotary cycle is, it is known that being between each several part
Coordination；
The optimization aim is maximum for the corresponding score sum of above-mentioned six optimized variables of target satellite, i.e., asteroid possesses less
Speed increment and duty cycle, are provided simultaneously with the comprehensive score of larger scientific value, engineering realizability and detection value most
It is high；
The solution is and draws optimal detection target using above-mentioned target satellite optimization model analytical calculation.
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| CN113553695A (en) * | 2021-06-21 | 2021-10-26 | 中国科学院国家空间科学中心 | Method for giving consideration to asteroid early warning and asteroid cataloguing in sun direction |
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| CN105083596B (en) * | 2015-09-21 | 2017-05-03 | 上海卫星工程研究所 | Method for selecting near-Earth asteroid as detection target |
| CN107883966B (en) * | 2017-09-25 | 2020-12-01 | 上海卫星工程研究所 | Deep space navigation method of asteroid reflectance spectrum |
| CN108100306B (en) * | 2017-12-05 | 2019-02-01 | 北京理工大学 | A kind of with quickly screening day equalization point asteroid detection mesh calibration method |
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| CN100476359C (en) * | 2006-12-27 | 2009-04-08 | 北京航空航天大学 | Deep space probe UPF celestial self-navigation method based on starlight angle |
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