CN103885456B - The different rail level of several satellite in a rocket is distributed transfer method - Google Patents
The different rail level of several satellite in a rocket is distributed transfer method Download PDFInfo
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- CN103885456B CN103885456B CN201410126451.XA CN201410126451A CN103885456B CN 103885456 B CN103885456 B CN 103885456B CN 201410126451 A CN201410126451 A CN 201410126451A CN 103885456 B CN103885456 B CN 103885456B
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Abstract
The invention discloses the different rail levels of several satellite in a rocket to be distributed transfer method, it is necessary first to which clearly enter the orbit inclination angle i and object height HfAnd task deployment deadline T and each star needed for orbital plane drift value Δ Ω, the critical altitude difference Δ a that target track face is at the appointed time transferred in T is calculated according to the above input condition.Satellite is provided by delivery separation or Upper Stage change rail mode and plays drift height, or when satellite, which carries fuel quantity, can have mutually strain rail ability, is directly drifted about drift height since being transferred to height of entering the orbit.Height is floated ensuring to be arranged under the premise of arrival corresponding different rise of each star in specified time T, is restored again respectively after reaching target track face to design height.The drift time and existing condition of entering the orbit that give to Process of Piggyback Satellite or the more stars of constellation according to task carry out the selection of track and carrying, when being met the requirements there are carrying condition or constellation task, each star different fuel demand is configured, the drift mode after entering the orbit according to design completes different rail level distribution transfer.
Description
Technical field
The present invention relates to the different rail levels of several satellite in a rocket to be distributed transfer method, belongs to satellite development and deployment techniques field.
Background technique
Several satellite in a rocket emits the cost of entering the orbit that can save satellite, especially for quality and all lesser satellite of volume
Speech, mutual independent satellite can average emitted cost, and functional associated satellite can form the incomparable constellation system of single star
System efficiency.
Identical height of entering the orbit, inclination angle and eccentricity launch mission, launch cost can calculate in due order substantially, in delivery type spectrum
Certain corresponding rocket maximum is entered the orbit in the case that load weight designed and determine, can't be because of the reduction for carrying load weight
And reduce launch cost.Several satellite in a rocket generally applies in all previous launch mission, and moonlet can be maximum by the way of carrying
Efficiency carries load surplus and launching opportunity using delivery, and the more stars of homologous ray, which are once entered the orbit, can quickly form constellation ability, example
Such as remote sensing satellite RapidEye, emitted after entering the orbit by an arrow five-pointed star mode, the 18 minutes same rail level constellations in formation etc. point interval,
It can be achieved once a day to revisit global arbitrary target.Due to compared to the phase adjustment in orbital plane, directly adjustment track
Face orientation generally requires to expend flood tide fuel, therefore more stars that an arrow mode emits often are in same orbital plane, are entered the orbit
Large scale adjustment is not carried out to the orientation of orbital plane afterwards.It is more according to the spatial relationship of track EDS maps and earth rotation
The type and probability of access information needed for the different rail level of star is distributed in space, obtains in time scale in same rail level all than being distributed
Effect is good.For carrying the mode of entering the orbit of form, if can be realized different rail level distribution transfer ability, when can not be entered the orbit by carrying
Orbital plane limitation.
Existing more stars are entered the orbit based on running in same orbital plane, and the indexs such as time, spatial resolution efficiency of constellation have
Limitation；Formed the distribution of more rail levels still in such a way that one satellite in a rocket emits enter the orbit one by one based on, launch cost is higher, for volume weight
Carrying capacity is not fully used for measuring lesser satellite constellation.
Summary of the invention
The technical problems to be solved by the present invention are: overcome in the prior art several satellite in a rocket transmitting after run on same rail level or
Different orbital planes need to emit respectively the deficiency entered the orbit, and provide several satellite in a rocket different rail level distribution transfer method, pass through time dimension
Orbital plane cost of transfer is reduced, forms Process of Piggyback Satellite and the more stars of constellation from entering deployment of the rail level respectively to target track face.
The technical scheme is that the present invention be directed to the transfers of the different rail level distribution of several satellite in a rocket, it is necessary first to clear
Enter the orbit inclination angle i and object height HfAnd task deployment deadline T and each star needed for orbital plane drift value Δ Ω, root
Upper input condition calculates the critical altitude difference Δ a that target track face is transferred at the appointed time T accordingly.By delivery separation or
Upper Stage becomes rail mode and provides satellite drift height, or when satellite carrying fuel quantity can have and mutually strain rail ability, directly
It drifts about drift height since being transferred to height of entering the orbit.It is corresponding ensuring that each star is arranged under the premise of arrival in specified time T
Difference plays drift height, restores again respectively after reaching target track face to design height.To Process of Piggyback Satellite or the more stars of constellation according to task
Given drift time and existing condition of entering the orbit carry out the selection of track and carrying, and there are carrying conditions or constellation task satisfaction to want
When asking, each star different fuel demand is configured, the drift mode after entering the orbit according to design completes different rail level distribution transfer.
As shown in Figure 1, the method specifically includes following steps:
(1) clearly following input condition: inclination angle i and object height H when carrier rocket is entered the orbitf, task deployment require
Deadline T corresponds to the fuel quantity Δ m that required orbital plane drift value Δ Ω and satellite maximum can be carried with when emitting0；
(2) inclination angle i and object height H when being entered the orbit according to the step (1)f, calculated drift orbital plane relative target rail
The transfer rate in road face
Wherein, a=Re+HfΔ a, Δ a are that rising for relative target track floats difference in height, ReFor earth radius,
According to the deadline T that orbital plane drift value Δ Ω and task deployment require, drift difference in height Δ a value model has been calculated
It encloses, the relationship between three is as follows.
(3) can be calculated in the step (2) | Δ a | value range is arranged Process of Piggyback Satellite or the more stars of constellation plays drift difference in height
It is respectively respectively minimum | Δ a |, calculate required fuel Δ m when satellite restores to design height:
Wherein, M is satellite quality, and μ is Gravitational coefficient of the Earth, and I is constant engine vacuum ratio, and g is acceleration of gravity；
If satellite realizes that, from the transfer for height drift height to of entering the orbit, part consumption should be included in combustion by self-ability
Expect among master budget；
(4) the fuel Δ m according to obtained in the step (3) determines Δ m < Δ m0It is whether true, if so, it is transferred to step
Suddenly (5), otherwise return step (1) remodifies deadline T and maximum carrying fuel quantity Δ m0；
(5) according to resulting demand for fuel is calculated in step (3), the fuel configuration of satellite is carried out, when more stars emit simultaneously
After entering the orbit, drift difference in height Δ a is played according to the difference being calculated and carries out deployment or by itself carrying out orbit maneuver, completion drift motion
Each elevation is restored to object height H afterwardsf, it is finally completed the distribution transfer of different rail level.
The advantages of the present invention over the prior art are that: the year-on-year orbital plane of the method for the present invention is directly shifted and can be dropped significantly
Low fuel consumption, by separate mode of suitably entering the orbit, the one way that satellite only needs to complete drift height to object height from turns
It moves.The different rail level transfer of several satellite in a rocket is to improve constellation systems efficiency, low cost completion constellation arrangement and Process of Piggyback Satellite not by primary
The effective means of orbital plane limitation.
Detailed description of the invention
Fig. 1 is the flow chart of the method for the present invention；
Fig. 2 is orbital plane drift speed with inclination angle relationship；
Fig. 3 is that an arrow Samsung orbital plane shifts schematic diagram.
Specific embodiment
Embodiment
By taking the orbital plane of arrow Samsung transmitting uniformly shifts as an example.
(1) enter the orbit inclination angle i=25 °, orbit altitude Hf=700km, it is desirable that the deployment time of constellation is no more than half a year, and fuel disappears
It consumes total amount and is no more than 30kg.
(2) it is uniformly required according to given orbital plane, two star orbital plane drift speeds are respectivelyWithIt is identified, is drifted about with number 01 and 02
03 star orbit altitude of relative datum is Hf.The opposite H of height is floated according to formula (1) and rising for (2) 01 and 02 starfDifference most
Value is respectively -212km and 212km, i.e. the most raised drift height of 01 star is 488km, and minimum drift height of 02 star is 912km.
(3) assume that whole star weight is 500kg, constant engine vacuum ratio is 200s, then is calculated by formula (3) and know two stars
One way readjustment is respectively necessary for fuel about 29.2kg and 26.7kg.
(4) each star pulls back to target track fuel consumption demand and is respectively less than portable greatest amount of fuel 30kg.
(5) playing drift height can be adjusted in place by Upper Stage, then height when Samsung transmitting is entered the orbit may be set to 488km, this
03 star is discharged into 700km by Upper Stage afterwards, and 02 star is discharged into 912km, and 01 and 02 star is respectively by satellite itself energy after six months
Power becomes rail to 700km.
If passing of satelline self-ability has realized the setting of drift height, then can be by delivering three after three star transmittings are entered the orbit
Star is released to 700km, and hereafter 01 star becomes rail to 488km, and 02 star becomes rail to 912km, and 01 star and 02 star are extensive after six months
Again to 700km, two stars, which need to consume in total fuel, respectively may be about 61.7kg and 59.2kg, and engineering cost is acceptable.If satellite is straight
The motor-driven transfer of row orbital plane is tapped into, the relationship of speed impulse and orbital plane orientation knots modification is
Velocity pulse 1.3kms is needed for changing 10 ° of orbital plane angle in 700km height, corresponding fuel consumption is about
243kg。
It should be noted that the selection at inclination angle becomes apparent the contribution of Drift Process compared to Level Change amount, pass through Fig. 2
It knows that the scheme of entering the orbit at low inclination angle should be selected as far as possible to realize being rapidly completed for Drift Process.Point in three satellite orbit faces
The signal of cloth transfer process as shown in figure 3,01 star and 02 star drift bearing are on the contrary, drift value is 120 °, enter the orbit for mark by when 03 star
Claim orbital plane.
The method of the present invention carries out different rail level distribution transfer to several satellite in a rocket, by the drift that drift height and a period of time has been arranged
Move, save fuel in addition can complete orbital plane can not directly shift realization large scale range it is motor-driven, orbit altitude adjustment
Consumed fuel can be received in Project Realization cost.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (1)
1. the different rail level of several satellite in a rocket is distributed transfer method, it is characterised in that include the following steps:
(1) clearly following input condition: inclination angle i and object height H when carrier rocket is entered the orbitf, task deployment require completion when
Between T with transmitting when correspond to the fuel quantity Δ m that required orbital plane drift value Δ Ω and satellite maximum can carry0；
(2) inclination angle i and object height H when being entered the orbit according to the step (1)f, calculated drift orbital plane relative target orbital plane
Transfer rate
Wherein, a=Re+HfΔ a, Δ a are that rising for relative target track floats difference in height, ReFor earth radius,
According to the deadline T that orbital plane drift value Δ Ω and task deployment require, drift difference in height Δ a value range has been calculated,
Relationship between three is as follows,
(3) can be calculated in the step (2) | Δ a | value range is arranged Process of Piggyback Satellite or the more stars of constellation plays drift difference in height as most
It is small | Δ a |, calculate required fuel Δ m when satellite restores to design height:
Wherein, M is satellite quality, and μ is Gravitational coefficient of the Earth, and I is constant engine vacuum ratio, and g is acceleration of gravity；
If satellite realizes that it is total that part consumption should be included in fuel from the transfer for height drift height to of entering the orbit by self-ability
Among budget；
(4) the fuel Δ m according to obtained in the step (3) determines Δ m < Δ m0It is whether true, if so, step (5) are transferred to,
Otherwise return step (1) remodifies deadline T and the maximum fuel quantity Δ m that can be carried0；
(5) according to resulting demand for fuel is calculated in step (3), the fuel configuration of satellite is carried out, is entered the orbit when more stars emit simultaneously
Afterwards, drift difference in height Δ a is played according to the difference being calculated to carry out deployment or carry out orbit maneuver by itself, complete each after drift motion
Elevation is restored to object height Hf, it is finally completed the distribution transfer of different rail level.
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| CN105628416B (en) * | 2014-11-06 | 2017-12-22 | 北京宇航系统工程研究所 | Upper Stage unit sine sweep test condition minute design method |
| CN104965982B (en) * | 2015-06-17 | 2020-07-24 | 中国人民解放军63920部队 | Earth-moon translation point constellation layout method |
| CN106094853B (en) * | 2016-06-29 | 2018-11-09 | 北京航空航天大学 | A kind of control method of Upper Stage Orbit Transformation section vectored thrust |
| CN110109476A (en) * | 2019-05-06 | 2019-08-09 | 中国人民解放军军事科学院国防科技创新研究院 | Isomery unmanned vehicle independent anti-collision warning method based on collision probability |
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Inventor after: Li Zhiwu Inventor after: Bai Zhaoguang Inventor after: Fu Danying Inventor after: Tan Tian Inventor after: Zhang Yan Inventor after: Lv Qiujie Inventor before: Li Zhiwu Inventor before: Fu Danying Inventor before: Tan Tian Inventor before: Zhang Yan Inventor before: Lv Qiujie |
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Free format text: CORRECT: INVENTOR; FROM: LI ZHIWU FU DANYING TAN TIAN ZHANG YAN LV QIUJIE TO: LI ZHIWU BAI ZHAOGUANG FU DANYING TAN TIAN ZHANG YAN LV QIUJIE |
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