CN107985629A - Mars exploration method and Mars probes - Google Patents
Mars exploration method and Mars probes Download PDFInfo
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- CN107985629A CN107985629A CN201710962920.5A CN201710962920A CN107985629A CN 107985629 A CN107985629 A CN 107985629A CN 201710962920 A CN201710962920 A CN 201710962920A CN 107985629 A CN107985629 A CN 107985629A
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- 239000000523 sample Substances 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 24
- 239000000428 dust Substances 0.000 claims abstract description 64
- 238000012546 transfer Methods 0.000 claims abstract description 20
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 238000005070 sampling Methods 0.000 claims description 12
- 230000015572 biosynthetic process Effects 0.000 claims description 9
- 238000012544 monitoring process Methods 0.000 claims description 5
- 239000000446 fuel Substances 0.000 description 10
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000010419 fine particle Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000005416 organic matter Substances 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/105—Space science
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/105—Space science
- B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Geophysics And Detection Of Objects (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
An embodiment of the present invention provides one kind to transport mars exploration method and Mars probes, the described method includes：Enter earth Mars transfer orbit from earth transmission lift-off, and carry out orbital exponent and enter Mars atmosphere；Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；When be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored；When definite martian dust storm is formed, martian dust storm is sampled into Mars atmosphere.Above-mentioned scheme, can reduce cost when carrying out mars exploration.
Description
Technical field
The present invention relates to space technology field, more particularly to a kind of mars exploration method and Mars probes.
Background technology
Mars dust is that martian surface soil passes through the molecule for developing up to some hundred million years and being formed, in martian atmosphere ring
Take aerial, the meteorological astronomy of this unique Mars of formation Mars sandstorm under the effect of the factors such as stream, martian surface electrostatic environment to
Phenomenon.
The areographic large area martian dust storm of ring can be formed according to current scientific exploration result Mars.Wherein, it is fiery
The principal element of stardust deflagration hair takes Mars molecule dust in the air to for martian atmosphere, and dust absorbs sunlight in the air
Afterwards, cause atmospheric temperature to rise, be further exacerbated by martian atmosphere movement, and further speed up the development degree of sandstorm.
Every 2 or 3 years, several regionality dust storms were accidentally joined together, can a large amount of dirt sand augers are aerial to 30km, are developed into
Global big dust storm, covers martian surface, sustainable some months.In the prior art,
Since Mars dust is the effect such as Mars topsoil, weathering, wind erosion by hundreds of millions of years, just formed micron-sized
Fine particle, takes to aerial under atmospheric circulation effect.Contain abundant Mars earth's surface information in institute's Mars dust.To Mars table
The Sample acquisition of dusty complexion angstrom, can obtain a large amount of Mars information, for example, trace, the water on Mars with the presence or absence of vital movement are deposited
Trace, whether there is organic matter, and whether there is the information such as the existence form of the element such as hydrocarbon.But existing mars exploration side
Method, it is higher there is cost when carrying out mars exploration the problem of.
The content of the invention
The technical problem that the embodiment of the present invention solves is how when carrying out mars exploration to reduce cost.
To solve the above problems, an embodiment of the present invention provides one kind to transport mars exploration method, including：
Enter earth Mars transfer orbit from earth transmission lift-off, and carry out orbital exponent and enter Mars atmosphere；
Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；
When be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored；
When definite martian dust storm is formed, martian dust storm is sampled into Mars atmosphere.
Alternatively, the method further includes：
At the end of being sampled to martian dust storm, return to and berth to described around Mars highly elliptic orbit；
When reaching the opportunity for returning to the earth, the Mars earth transfer is accelerated back to around Mars highly elliptic orbit from described
Track；
Into earth atmosphere, and aerobraking is carried out using earth atmosphere and is entered around earth highly elliptic orbit；
When entering around earth highly elliptic orbit, aerobraking deceleration is carried out using earth atmosphere and enters low land ball rail
Road；
The earth is back to from the Low Earth Orbit and is landed to the predetermined position of earth surface.
Alternatively, the opportunity for reaching the return earth, including：Reach default time of return window.
Alternatively, the definite martian dust storm is formed, including：
When the message for receiving martian dust storm formation, or when the definite load of itself reaches default load threshold value,
Determine that martian dust storm is formed.
Alternatively, it is described to be back to the earth from the Low Earth Orbit and land to the predetermined position of earth surface, bag
Include：
When being determined for compliance with default ground landing conditions, it is described from the Low Earth Orbit be back to the earth and land to
The predetermined position of earth surface.
The embodiment of the present invention additionally provides a kind of Mars probes, including：
Brake unit, suitable for entering earth Mars transfer orbit from earth transmission lift-off, and carries out orbital exponent and enters fire
Star atmosphere；Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；
Mars monitoring unit, suitable for when be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored；
Mars sampling unit, suitable for when definite martian dust storm is formed, being adopted into Mars atmosphere to martian dust storm
Sample.
Alternatively, the brake unit, is further adapted at the end of martian dust storm is sampled, returning to and berthing to described
Around Mars highly elliptic orbit；When reaching the opportunity for returning to the earth, the fire is accelerated back to around Mars highly elliptic orbit from described
Star earth transfer orbit；Into earth atmosphere, and aerobraking is carried out using earth atmosphere and is entered around the big oval rail of the earth
Road；When entering around earth highly elliptic orbit, aerobraking deceleration is carried out using earth atmosphere and enters Low Earth Orbit；From institute
Low Earth Orbit is stated to be back to the earth and land to the predetermined position of earth surface.
Alternatively, the opportunity for reaching the return earth, including：Reach default time of return window.
Alternatively, the definite martian dust storm is formed, including：
When the message for receiving martian dust storm formation, or when the definite load of itself reaches default load threshold value,
Determine that martian dust storm is formed.
Alternatively, it is described to be back to the earth from the Low Earth Orbit and land to the predetermined position of earth surface, bag
Include：
When being determined for compliance with default ground landing conditions, it is described from the Low Earth Orbit be back to the earth and land to
The predetermined position of earth surface.
Compared with prior art, technical scheme has the following advantages that：
Above-mentioned scheme, when carrying out Mars sampling, enters Mars atmosphere, and Mars only with a Mars probes
Detector utilizes aero-braking, completes Mars capture, and itself non-used fuel is braked, and can be saved detector fuel and be disappeared
Consumption, therefore can effectively save the cost of mars exploration.
Brief description of the drawings
Fig. 1 is a kind of flow chart of mars exploration method in the embodiment of the present invention；
Position view when Fig. 2 is the Mars probes progress mars exploration in the embodiment of the present invention；
Fig. 3 is a kind of structure diagram of carrier rocket Reliability Assessment device in the embodiment of the present invention.
Embodiment
To solve the above-mentioned problems in the prior art, the technical solution that the embodiment of the present invention uses is by carrying out fire
When star samples, enter Mars atmosphere only with a Mars probes, and Mars probes utilize aero-braking, complete Mars
Capture, and itself non-used fuel is braked, and can save detector fuel consumption, therefore can effectively save mars exploration
Cost.
It is understandable to enable the above objects, features and advantages of the present invention to become apparent, below in conjunction with the accompanying drawings to the present invention
Specific embodiment be described in detail.
Fig. 1 shows a kind of flow chart of mars exploration method in the embodiment of the present invention；Fig. 2 is in the embodiment of the present invention
Mars probes carry out mars exploration when position view.With reference to Fig. 2, mars exploration method as shown in Figure 1, specifically may be used
With including following operation：
Step S101：Enter earth Mars transfer orbit from earth transmission lift-off, and it is big into Mars to carry out orbital exponent
Gas-bearing formation.
In specific implementation, the Mars probes D in the embodiment of the present invention uses aircraft-type configuration, using carrier rocket C
Go up to the air from earth transmission, into earth Mars transfer orbit R1 (or to fiery track).Entering earth Mars transfer orbit R1
When, Mars probes D deploying solar wings simultaneously remain unfolded state in the earth Mars transfer orbit R1 during operation, to obtain
Solar energy, and then be converted into electric energy and provide electric energy for the equipment in Mars probes.Transported when in earth Mars transfer orbit R1
Capable process, Mars probes can carry out one or many orbital exponents, until entering Mars atmosphere R21.
Step S102：Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit.
In specific implementation, when entering Mars atmosphere R21, Mars probes D can use Mars atmosphere to carry out
Aerobraking, into and be docked in around Mars highly elliptic orbit R22 so that complete Mars capture, wait martian dust storm formed.
Above-mentioned process, aerobraking is carried out when Mars probes D carries out Mars capture using Mars atmosphere R21, rather than is utilized
The fuel of itself is braked, therefore can save the fuel consumption of Mars probes D.
Step S103：When be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored.
In specific implementation, when being docked in around Mars highly elliptic orbit R22, namely in Mars highly elliptic orbit R22
During operation, Mars probes D can form martian dust storm by being monitored to Mars atmosphere R21 to determine whether.
In specific implementation, the mode that Mars probes D is monitored martian dust storm can according to the actual needs into
Row is set.
In an embodiment of the present invention, Mars probes D can be according to default cycle or captured in real-time martian atmosphere
The image of layer R21, and the martian atmosphere tomographic image to photographing carries out image recognition, with from taken Mars atmosphere
The image that martian dust storm is formed is identified in the image of R21.
In an alternative embodiment of the invention, the other equipment outside Mars probes D can be used to carry out martian dust storm
Monitoring, and when definite martian dust storm is formed, to the corresponding martian dust storm formation of Mars probes D transmissions message when, can be with
Determine that martian dust storm has been formed.
In still another embodiment of the process, Mars probes D can be in real time or according to the default sampling period to itself
Load be detected, and when the definite load of itself reaches default load threshold value, determine that martian dust storm has been formed.
Step S104：When definite martian dust storm is formed, martian dust storm is sampled into Mars atmosphere.
In specific implementation, berth in the Mars probes around Mars highly elliptic orbit R22, formed in definite martian dust storm
When, appropriate opportunity can be selected to become rail into Mars atmosphere R21 to martian dust storm progress from around Mars highly elliptic orbit R22
Sampling, namely Mars dust is sampled.Wherein, Mars probes D is becoming rail into fire from around Mars highly elliptic orbit R22
During star air R21, the solar wing that itself is in unfolded state is packed up.
Above-mentioned scheme, when carrying out Mars sampling, enters Mars atmosphere, and Mars only with a Mars probes
Detector utilizes aero-braking, completes Mars capture, and itself non-used fuel is braked, and can be saved detector fuel and be disappeared
Consumption, therefore can effectively save the cost of mars exploration.
In specific implementation, the mars exploration method in the embodiment of the present invention can also include：
Step S105：At the end of being sampled to martian dust storm, return to and berth to described around Mars highly elliptic orbit.
In specific implementation, at the end of being sampled every time to martian dust storm, Mars probes D can carry out orbit maneuver,
Lifting periareon, and deploying solar wing, return from Mars atmosphere R21 and are back to around Mars highly elliptic orbit R22, are returned with waiting
Return the arrival on earth opportunity.
In specific implementation, the needs sampled according to martian dust storm, Mars probes D can once or repeatedly enter fire
Star atmosphere R21 samples martian dust storm, is not limited herein.Wherein, the sample track of Mars probes D is around Mars
Highly elliptic orbit R22, because the cycle of detouring around Mars highly elliptic orbit R22 is longer, in order to keep the lasting supply of the energy, it is ensured that
The normal operation of Mars probes D, can return to around Mars highly elliptic orbit R22 in adjacent Mars sampling gap twice
When, the solar wing that packed up can be unfolded again by Mars probes D, to charge to Mars probes D.
Step S106：When reaching the opportunity for returning to the earth, the fire is accelerated back to around Mars highly elliptic orbit from described
Star earth transfer orbit.
In specific implementation, at the end of being sampled to martian dust storm, Mars probes D is docked in around Mars highly elliptic orbit
During R22, and when determining that the opportunity for returning to the earth arrives, open engine and accelerated, from described around Mars highly elliptic orbit
R22 is accelerated back to the Mars earth transfer orbit R1.The Mars earth is being accelerated back to from around Mars highly elliptic orbit R22
During transfer orbit R1, Mars probes D can carry out one or many orbital exponents, and the solar wing of itself is kept
In unfolded state.
In specific implementation, Mars probes D returns to the opportunity of the earth, can be configured according to the actual needs.Example
Such as, when reaching default time of return window, Mars probes D can be accelerated back to the fire from around Mars highly elliptic orbit
Star earth transfer orbit.
Step S107：Into earth atmosphere, and aerobraking is carried out using earth atmosphere and is entered around the big ellipse of the earth
Track.
In specific implementation, when Mars probes D is reached near the earth by orbital exponent, earth atmosphere can be entered
Layer, and aerobraking is carried out using earth atmosphere, Earth's orbit capture is completed, into around earth highly elliptic orbit R0.
Step S108：When entering around earth highly elliptic orbit, aerobraking deceleration is carried out using earth atmosphere and is entered
Low Earth Orbit；
In specific implementation, during R0 is run around earth highly elliptic orbit, Mars probes D is by the sun of itself
The span is opened, and to obtain the energy, and repeatedly constantly passes in and out earth atmosphere, carries out aerobraking using earth atmosphere, decay is remote
Location higher, i.e., become rail to R01 from track R0, then becomes rail to R02 and R03.Treat that Mars probes D reaches planned orbit and (do not show
Go out) when, Mars probes D's packs up solar wing, and carries out orbit maneuver, the planned orbit is reentered into return, into ground
Ball atmosphere, by aero-braking, reduces flying speed, and adjusts itself attitude of flight vehicle, course line and course, in ground machine
Field sliding horizontal lands.
In specific implementation, Mars probes D land to before ground, it is necessary to first determine whether to meet default
During the landing conditions of face, and when being determined for compliance with default ground landing conditions, from the Low Earth Orbit be back to the earth and
Land to earth surface predetermined position.Wherein, default ground landing conditions include Earth orbital parameters, meteorological condition etc..
Earth orbital parameters are obtained by ground observing and controlling, meteorological condition is determined for surface Weather forecast, airport condition by blank pipe department, the above
Condition is ground safeguard condition.
The above-mentioned mars exploration method in the embodiment of the present invention is described in detail, below by above-mentioned method
Corresponding device is introduced.
Referring to Fig. 3, the embodiment of the present invention, which additionally provides a kind of Mars probes 30, can include brake unit 301, Mars
Monitoring unit 302 and Mars sampling unit 303, wherein：
Brake unit 301, suitable for entering earth Mars transfer orbit from earth transmission lift-off, and carries out orbital exponent entrance
Mars atmosphere；Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；
Mars monitoring unit 302, suitable for when be docked in it is described around Mars highly elliptic orbit when, martian dust storm is supervised
Survey；
Mars sampling unit 303, suitable for when definite martian dust storm is formed, being carried out into Mars atmosphere to martian dust storm
Sampling.
In an embodiment of the present invention, the brake unit 301, is further adapted at the end of being sampled to martian dust storm, again
Return and berth to described around Mars highly elliptic orbit；When reaching the opportunity for returning to the earth, from described around the big oval rail of Mars
Road is accelerated back to the Mars earth transfer orbit；Into earth atmosphere, and using earth atmosphere carry out aerobraking into
Enter around earth highly elliptic orbit；When enter around the earth highly elliptic orbit when, using earth atmosphere carry out aerobraking slow down into
Enter Low Earth Orbit；The earth is back to from the Low Earth Orbit and is landed to the predetermined position of earth surface.
In an embodiment of the present invention, the brake unit 301, suitable for when reaching default time of return window, really
Surely the opportunity for returning to the earth is reached.
In an embodiment of the present invention, the brake unit 301, when the message for receiving martian dust storm formation, or works as
When determining that the load of itself reaches default load threshold value, determine that martian dust storm is formed.
In an embodiment of the present invention, the brake unit 301, default ground landing conditions are determined for compliance with suitable for working as
When, it is described to be back to the earth from the Low Earth Orbit and land to the predetermined position of earth surface.
Using the such scheme in the embodiment of the present invention, when carrying out Mars sampling, only with a Mars probes into
Enter Mars atmosphere, and Mars probes utilize aero-braking, complete Mars capture, and itself non-used fuel is braked,
Detector fuel consumption can be saved, therefore can effectively save the cost of mars exploration.
One of ordinary skill in the art will appreciate that all or part of step in the various methods of above-described embodiment is can
To instruct relevant hardware to complete by program, which can be stored in computer-readable recording medium, and storage is situated between
Matter can include：ROM, RAM, disk or CD etc..
The method and system of the embodiment of the present invention are had been described in detail above, the present invention is not limited thereto.Any
Field technology personnel, without departing from the spirit and scope of the present invention, can make various changes or modifications, therefore the guarantor of the present invention
Shield scope should be subject to claim limited range.
Claims (10)
- A kind of 1. mars exploration method, it is characterised in that including：Enter earth Mars transfer orbit from earth transmission lift-off, and carry out orbital exponent and enter Mars atmosphere；Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；When be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored；When definite martian dust storm is formed, martian dust storm is sampled into Mars atmosphere.
- 2. mars exploration method according to claim 1, it is characterised in that further include：At the end of being sampled to martian dust storm, return to and berth to described around Mars highly elliptic orbit；When reaching the opportunity for returning to the earth, the Mars earth transfer rail is accelerated back to around Mars highly elliptic orbit from described Road；Into earth atmosphere, and aerobraking is carried out using earth atmosphere and is entered around earth highly elliptic orbit；When entering around earth highly elliptic orbit, aerobraking deceleration is carried out using earth atmosphere and enters Low Earth Orbit；The earth is back to from the Low Earth Orbit and is landed to the predetermined position of earth surface.
- 3. mars exploration method according to claim 2, it is characterised in that the opportunity for reaching the return earth, including： Reach default time of return window.
- 4. mars exploration method according to claim 1 or 2, it is characterised in that the definite martian dust storm is formed, bag Include：When the message for receiving martian dust storm formation, or when the definite load of itself reaches default load threshold value, determine Martian dust storm is formed.
- 5. mars exploration method according to claim 2, it is characterised in that described to be back to ground from the Low Earth Orbit Ball simultaneously lands to the predetermined position of earth surface, including：It is described to be back to the earth from the Low Earth Orbit and land to the earth when being determined for compliance with default ground landing conditions The predetermined position on surface.
- A kind of 6. Mars probes, it is characterised in that including：Brake unit, suitable for entering earth Mars transfer orbit from earth transmission lift-off, and it is big into Mars to carry out orbital exponent Gas-bearing formation；Using Mars atmosphere carry out aerobraking, into and be docked in around Mars highly elliptic orbit；Mars monitoring unit, suitable for when be docked in it is described around Mars highly elliptic orbit when, martian dust storm is monitored；Mars sampling unit, suitable for when definite martian dust storm is formed, being sampled into Mars atmosphere to martian dust storm.
- 7. Mars probes according to claim 6, it is characterised in that the brake unit, is further adapted for when to Mars dirt At the end of sudden and violent sampling, return to and berth to described around Mars highly elliptic orbit；When reaching the opportunity for returning to the earth, the Mars earth transfer rail is accelerated back to around Mars highly elliptic orbit from described Road；Into earth atmosphere, and aerobraking is carried out using earth atmosphere and is entered around earth highly elliptic orbit；When into around ground During ball highly elliptic orbit, aerobraking deceleration is carried out using earth atmosphere and enters Low Earth Orbit；From the Low Earth Orbit It is back to the earth and lands to the predetermined position of earth surface.
- 8. Mars probes according to claim 7, it is characterised in that the opportunity for reaching the return earth, including：Reach To default time of return window.
- 9. the Mars probes according to claim 6 or 7, it is characterised in that the definite martian dust storm is formed, including：When the message for receiving martian dust storm formation, or when the definite load of itself reaches default load threshold value, determine Martian dust storm is formed.
- 10. Mars probes according to claim 7, it is characterised in that described to be back to ground from the Low Earth Orbit Ball simultaneously lands to the predetermined position of earth surface, including：It is described to be back to the earth from the Low Earth Orbit and land to the earth when being determined for compliance with default ground landing conditions The predetermined position on surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710962920.5A CN107985629B (en) | 2017-10-17 | 2017-10-17 | Mars detection method and Mars detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710962920.5A CN107985629B (en) | 2017-10-17 | 2017-10-17 | Mars detection method and Mars detector |
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| Publication Number | Publication Date |
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| CN107985629A true CN107985629A (en) | 2018-05-04 |
| CN107985629B CN107985629B (en) | 2020-11-03 |
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| CN201710962920.5A Active CN107985629B (en) | 2017-10-17 | 2017-10-17 | Mars detection method and Mars detector |
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| CN109460049A (en) * | 2018-11-14 | 2019-03-12 | 北京控制工程研究所 | Geo-synchronous orbit satellite apogee orbit changing method based on inertia directing mode |
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| CN115367145A (en) * | 2022-08-26 | 2022-11-22 | 哈尔滨工业大学 | Electromagnetic drive attitude-adjusting coaxial Mars aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107985629B (en) | 2020-11-03 |
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