CN104249818A - Atmospheric braking method based on magnetofluid control - Google Patents
Atmospheric braking method based on magnetofluid control Download PDFInfo
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- CN104249818A CN104249818A CN201310259305.XA CN201310259305A CN104249818A CN 104249818 A CN104249818 A CN 104249818A CN 201310259305 A CN201310259305 A CN 201310259305A CN 104249818 A CN104249818 A CN 104249818A
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Abstract
The invention discloses an atmospheric braking method based on magnetofluid control. The method comprises the steps of: building a mars atmospheric density approximation model; estimating the resistance met by a detector under a rare gas effect; making an atmospheric braking strategy; and combining an atmospheric braking kinetic model and determining a magnetic field strength. Compared with the prior art, the method solves the problem of too long atmospheric braking flight time, reduces the heat flux received by the detector in the atmospheric braking process, and guarantees the operation safety of the detector.
Description
Technical field
The present invention relates to detector martian atmosphere braking technology, especially based on a kind of detector martian atmosphere braking method of magnetic fluid control technology.
Background technology
The detached shock wave that detector produces when entering atmospheric envelope is very strong, and the air-flow in the spatial domain (silting deposit) between detector and shock wave is plasmoid.Magnetic fluid control technology, when using the magnet of internal stowage to this plasma flow externally-applied magnetic field, from faraday electromagnetic induction rule and Hall effect, can produce inducing current in silting deposit.This technology is widely used, as anti-heat control, oblique shock wave control, flowing plus/minus speed control system and the control of flight vehicle aerodynamic power etc.
The object of martian atmosphere braking is fuel saving, with only rely on rocket engine to adjust compared with track, atmospheric deceleration can reduce nearly half by from the fuel that must carry during earth transmission, this is a considerable quantity, particularly for the high-speed aircraft of several hundred million km that needs to fly for long-distance, fuel saving just means can carry larger load.Atmospheric deceleration technology is tested first at the end of the main task of " No. Mai Zhelun " spacecraft on Venus of the U.S. in 1994, this technology is successfully employed afterwards, as " Mars whole world cruiser " detector, " Mars weather " detector, " Mars Odyssey " detector and " Mars scouting " detector etc. on multiple Mars probes.Traditional atmospheric deceleration technical flying is chronic, and the atmospheric deceleration method based on magnetic fluid control technology can improve the efficiency of atmospheric deceleration, greatly reduces atmospheric deceleration time of run.
Summary of the invention
The present invention aims to provide a kind of atmospheric deceleration method controlled based on magnetic fluid, can greatly reduce atmospheric deceleration time of run, meet the demand of following survey of deep space.
For reaching above-mentioned purpose, the atmospheric deceleration method controlled based on magnetic fluid provided by the invention, its step comprises: 1) set up martian atmosphere density approximate model; 2) resistance under detector rarefied gas effect is estimated; 3) atmospheric deceleration strategy is formulated; 4) in conjunction with atmospheric deceleration kinetic model, magnetic-field intensity is determined.
In some embodiments, described step 1) comprising: 1-1) based on the atmospheric density inverting of take off data; 1-2) least square fitting obtains atmospheric density approximate model.
In some embodiments, described step 2) comprising: 2-1) drag coefficient is estimated; 2-2) in conjunction with Atmospheric Density Models and drag coefficient estimation formulas, set up resistance and estimate approximate model.
In some embodiments, in described step 3), meeting the height determining initial periareon under constraint condition, constraint condition is: can not clash into martian surface in order to ensure detector, requires that perigee altitude is not less than critical value; The overload started in acquisition procedure must ensure the scope can born at detector; Meet the demand of thermal control, the density of heat flow rate of moderating process and add the scope that heat can must bear at detector; If detector can produce lift, then must ensure that perigean velocity can not be too large, cause detector to jump out air.
The present invention adopts the atmospheric deceleration method controlled based on magnetic fluid, compared with prior art, its advantage and beneficial effect are: solve atmospheric deceleration flight time long problem, and reduce the thermal flow suffered by atmospheric deceleration process detector, ensure that the safe operation of detector.
Accompanying drawing explanation
By reading the detailed description done non-limiting example done with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the atmospheric deceleration method flow diagram controlled based on magnetic fluid according to the embodiment of the present invention;
Fig. 2 is detector internal magnet schematic diagram;
Fig. 3 is for implementing atmospheric deceleration method schematic diagram;
Fig. 4 adopts the atmospheric deceleration procedure figure controlled based on magnetic fluid.
Detailed description of the invention
See the accompanying drawing that the embodiment of the present invention is shown, hereafter in more detail the present invention will be described.But the present invention can realize in many different forms, and should not be construed as by the restriction in the embodiment of this proposition.On the contrary, it is abundant and complete open in order to reach for proposing these embodiments, and makes those skilled in the art understand scope of the present invention completely.In these accompanying drawings, for clarity sake, may be exaggerated size and the relative size in layer and region.
Description describes the atmospheric deceleration method controlled based on magnetic fluid according to the embodiment of the present invention in detail.As shown in Figure 1, according to the atmospheric deceleration method controlled based on magnetic fluid of the present invention, plasma jet around the Magnetic control aircraft produced by the magnet loaded in detector, thus induction generation current and Lorentz force, the resistance that the reaction force acts of Lorentz force causes to the electromagnetic force of detector and aeromechanics resistance will make detector significantly slow down (see Fig. 2).The method comprises the steps:
1) martian atmosphere density approximate model is set up
1-1) based on the atmospheric density inverting of take off data:
Pneumatic data bank iterative manner is adopted to solve atmospheric density
1-2) least square fitting obtains atmospheric density approximate model
Least square fitting is adopted to obtain periapsis density
and density scale height
.The atmospheric density estimation formulas of next track is:
2) resistance under detector rarefied gas effect is estimated
2-1) drag coefficient is estimated
During without magnetic field, the drag coefficient estimation formulas based on bridge funcation method is:
Wherein,
,
,
knudsen number respectively, drag coefficient, drag coefficient in free molecule incoming flow in continuous incoming flow.Knudsen number is calculated by following formula
Wherein,
,
,
be respectively the ratio of specific heat of detector, Mach number and Lei Luo number
Drag coefficient estimation formulas in externally-applied magnetic field situation is:
Wherein,
for magnetic interaction parameter, calculated by following formula:
Wherein σ, B, L, ρ, V are conductivity, magnetic-field intensity, detector reference length, atmospheric density and relative flight speed respectively.
2-2) in conjunction with Atmospheric Density Models and drag coefficient estimation formulas, resistance estimates that approximate model is:
Wherein,
drag coefficient,
it is wind area.
3) formulating method of atmospheric deceleration strategy
According to the feature of martian atmosphere, at height higher than 200km air and thin, not obvious to the slowing effect of detector.So generally, need periareon to be transferred to relatively enough low height, make full use of the effect of air, by the energy ezpenditure of detector to a certain extent, then periareon is brought up to the height of demand.Therefore need under the condition of satisfied constraint, determine periareon height.
As shown in Figure 3, schematic diagram is moved for implementing air method.In conjunction with constraint condition and actual task demand, determine periareon height.Make full use of the effect of air, by the energy ezpenditure of detector to a certain extent, then periareon is brought up to the height of demand.Constraint condition is:
3-1) can not martian surface be clashed in order to ensure detector, require that perigee altitude is not less than critical value;
Overload 3-2) started in acquisition procedure must ensure the scope can born at detector;
3-3) meet the demand of thermal control, the density of heat flow rate of moderating process and add the scope that heat can must bear at detector;
If 3-4) detector can produce lift, then must ensure that perigean velocity can not be too large, cause detector to jump out air.
4) in conjunction with the magnetic-field intensity defining method of atmospheric deceleration kinetic model
Analysis of magnetic interaction parameter, in conjunction with atmospheric deceleration kinetic model, determines suitable magnetic-field intensity, realizes the atmospheric deceleration method controlled based on magnetic fluid.
Fig. 4 adopts the atmospheric deceleration procedure figure controlled based on magnetic fluid, adopts sensor take off data, eliminates distracter, obtains the acceleration information that atmospherical drag produces, in conjunction with Newton's second law, adopts pneumatic data bank iterative manner to solve atmospheric density
Atmospheric deceleration kinetic model is:
Wherein:
for longitude, east orientation is just;
for track angle, velocity vector and the instantaneous inclination angle when ground level are just above water;
for course angle, the azimuth that velocity vector projects on local level is just northwards;
for latitude, be just above equator;
the speed of spacecraft;
for detector barycenter is to the distance of planetocentric;
for planetary rotation cireular frequency.
To those skilled in the art, obviously the invention is not restricted to the details of above-mentioned one exemplary embodiment, and when not deviating from spirit of the present invention or essential characteristic, the present invention can be realized in other specific forms.Therefore, no matter from which point, all should embodiment be regarded as exemplary, and be nonrestrictive, scope of the present invention is limited by claims instead of above-mentioned explanation, and all changes be therefore intended in the implication of the equivalency by dropping on claim and scope are included in the present invention.Any Reference numeral in claim should be considered as the claim involved by limiting.In addition, obviously " comprising " one word do not get rid of other unit or step, odd number does not get rid of plural number.Multiple unit of stating in system claims or device also can be realized by software or hardware by a unit or device.First, second word such as grade is used for representing title, and does not represent any specific order.
Claims (5)
1., based on the atmospheric deceleration method that magnetic fluid controls, it is characterized in that, the method step comprises:
1) martian atmosphere density approximate model is set up;
2) resistance under detector rarefied gas effect is estimated;
3) atmospheric deceleration strategy is formulated;
4) in conjunction with atmospheric deceleration kinetic model, magnetic-field intensity is determined.
2. the atmospheric deceleration method controlled based on magnetic fluid according to claim 1, is characterized in that, described step 1) comprising:
1-1) based on the atmospheric density inverting of take off data;
1-2) least square fitting obtains atmospheric density approximate model.
3. the atmospheric deceleration method controlled based on magnetic fluid according to claim 1, is characterized in that, described step 2) comprising:
2-1) drag coefficient is estimated;
2-2) in conjunction with Atmospheric Density Models and drag coefficient estimation formulas, set up resistance and estimate approximate model.
4. the atmospheric deceleration method controlled based on magnetic fluid according to claim 1, it is characterized in that, in described step 3), meeting the height determining initial periareon under constraint condition, constraint condition is:
Can not martian surface be clashed in order to ensure detector, require that perigee altitude is not less than critical value; The overload started in acquisition procedure must ensure the scope can born at detector; Meet the demand of thermal control, the density of heat flow rate of moderating process and add the scope that heat can must bear at detector; If detector can produce lift, then must ensure that perigean velocity can not be too large, cause detector to jump out air.
5. the atmospheric deceleration method controlled based on magnetic fluid according to claim 1, it is characterized in that, in described step 4), atmospheric deceleration kinetic model is:
Wherein:
for longitude, east orientation is just;
for track angle, velocity vector and the instantaneous inclination angle when ground level are just above water;
for course angle, the azimuth that velocity vector projects on local level is just northwards;
for latitude, be just above equator;
the speed of spacecraft;
for detector barycenter is to the distance of planetocentric;
for planetary rotation cireular frequency.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985629A (en) * | 2017-10-17 | 2018-05-04 | 上海宇航系统工程研究所 | Mars exploration method and Mars probes |
| CN108349595A (en) * | 2015-02-03 | 2018-07-31 | 阿丽亚娜集团简化股份公司 | The aero-braking system to leave the right or normal track for satellite |
| CN113591265A (en) * | 2021-05-28 | 2021-11-02 | 中国人民解放军63920部队 | Method for calculating atmospheric resistance of Mars detector |
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| EP0158821B1 (en) * | 1984-03-12 | 1987-11-04 | Edward F. Marwick | Apparatus and methods of extraterrestrial transportation |
| CN102765494A (en) * | 2012-08-03 | 2012-11-07 | 北京卫星环境工程研究所 | Detent force umbrella for reentry deceleration of reentry capsule |
Non-Patent Citations (3)
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| HIROTAKA OTSU: "Application of the Magnetic Flow Control System for Aerobraking Flight of the Reentry Vehicle", 《39TH PLASMADYNAMICS AND LASERS CONFERENCE》 * |
| HIROTAKA OTSU: "Rarefied Gas Effects on the Magnetic Flow Control System for Aerobraking Flight of the Reentry Vehicle", 《40TH AIAA PLASMADYNAMICS AND LASERS CONFERENCE》 * |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108349595A (en) * | 2015-02-03 | 2018-07-31 | 阿丽亚娜集团简化股份公司 | The aero-braking system to leave the right or normal track for satellite |
| CN108349595B (en) * | 2015-02-03 | 2021-11-23 | 阿丽亚娜集团简化股份公司 | Atmospheric braking system for satellite derailing |
| CN107985629A (en) * | 2017-10-17 | 2018-05-04 | 上海宇航系统工程研究所 | Mars exploration method and Mars probes |
| CN107985629B (en) * | 2017-10-17 | 2020-11-03 | 上海宇航系统工程研究所 | Mars detection method and Mars detector |
| CN113591265A (en) * | 2021-05-28 | 2021-11-02 | 中国人民解放军63920部队 | Method for calculating atmospheric resistance of Mars detector |
| CN113591265B (en) * | 2021-05-28 | 2024-04-30 | 中国人民解放军63920部队 | Method for calculating atmospheric resistance of Mars detector |
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