CN109094819A - Spacecraft is controlled to reenter design method of settling in an area - Google Patents
Spacecraft is controlled to reenter design method of settling in an area Download PDFInfo
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- CN109094819A CN109094819A CN201810907411.7A CN201810907411A CN109094819A CN 109094819 A CN109094819 A CN 109094819A CN 201810907411 A CN201810907411 A CN 201810907411A CN 109094819 A CN109094819 A CN 109094819A
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- spacecraft
- controlled
- reenter
- drop rail
- reentered
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- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
Abstract
Design method of settling in an area is reentered the present invention relates to a kind of spacecraft is controlled, comprising steps of a. judges Spacecraft Attitude Control propellant waste according to the controlled running track of spacecraft, then corresponding selection Spacecraft reentry embodiment；B. judge spacecraft engine operation duration, then corresponding selection implements drop rail control program；C. the controlled posture for reentering period drop rail control of spacecraft is determined；D. selection spacecraft implements the controlled date reentered；E. selection spacecraft implements the controlled circle time reentered.The controlled design method of settling in an area that reenters of spacecraft according to the present invention controlled to the implementation of the spacecraft after completion task can reenter, and spacecraft is avoided to become space junk.
Description
Technical field
Design method of settling in an area is reentered the present invention relates to a kind of spacecraft is controlled.
Background technique
With the development of Chinese Space Spaceflight device, LEO operation large-scale manned spacecraft (spacelab,
Cargo ship, space station) and large-scale near-earth remote-sensing spacecraft platform etc. face the handling problems that task completes kataphase, to avoid
In-orbit spacecraft becomes space debris, needs to carry out them to implement control and reenters, to show the image of responsible big country of China.
To reenter task using limited propellant resource completion Large Spacecraft, equipped with control-moment gyro or move
The aircraft of the devices such as amount wheel, often utilizes the effect of atmospheric drag, gradually reduces the flying height of spacecraft, then implement again
It is controlled to reenter.Lack the aircraft of control-moment gyro or momentum wheel apparatus, when in-orbit flight, generally requires to pass through engine
Implement gas puff Z-pinch to guarantee the posture of aircraft, causes to consume more propellants, so this kind of spacecraft is often completed
After flight test mission, implement to reenter directly in flying height.
It is limited by engine characteristics and spacecraft weight, in order to improve the accuracy reentered, in conjunction with Spacecraft TT&C,
The demand of the energy needs directly controlled to reenter scheme detailed design to Large Spacecraft.
Summary of the invention
The purpose of the present invention is to solve the above problem, provides that a kind of spacecraft is controlled to reenter design method of settling in an area.
For achieving the above object, the present invention provides that a kind of spacecraft is controlled to reenter design method of settling in an area, including following
Step:
A. according to the controlled running track of spacecraft, judge Spacecraft Attitude Control propellant waste, then corresponding selection
Spacecraft reentry embodiment；
B. judge spacecraft engine operation duration, then corresponding selection implements drop rail control program；
C. the controlled posture for reentering period drop rail control of spacecraft is determined；
D. selection spacecraft implements the controlled date reentered；
E. selection spacecraft implements the controlled circle time reentered.
According to an aspect of the present invention, in a step, spacecraft under atmospheric drag effect in attenuation process,
It promotes dosage to be greater than the corresponding propulsion dosage for dropping rail consumption of orbit altitude of decaying when Spacecraft Attitude Control consumption, passes through
Directly implement drop rail control, makes Spacecraft reentry atmosphere and pass away in ground；
Dosage is promoted to be less than or equal to the corresponding drop rail consumption of the orbit altitude to decay when Spacecraft Attitude Control consumption
, can be under atmospheric drag effect, when orbit altitude being made to decay to certain altitude when promoting dosage, then implement to drop rail control, make to navigate
Its device atmospheric reentry simultaneously passes away in ground.
According to an aspect of the present invention, in the b step, spacecraft engine operating duration is greater than the orbital period
When 10%, the controlled drop rail control reentered of spacecraft is divided into and is executed more than twice, the engine of the drop rail control executed every time
Working time is less than or equal to the 10% of orbital period；
When spacecraft engine operating duration is less than or equal to the 10% of orbital period, implements spacecraft single and drop rail control
System.
According to an aspect of the present invention, in the step c, according to the b step embodiment and the rail used
The controlled posture for reentering period drop rail control of control engine mounting positions adjustment spacecraft, makes precise tracking carry out drop rail control
When the speed increment direction that generates it is opposite with heading.
According to an aspect of the present invention, in the Step d, the spacecraft determined according to the step c is controlled to be reentered
Posture when rail control drops in period reenters the spacecraft energy at period controlled by selecting suitable solar irradiation condition
In equilibrium state, so that it is determined that spacecraft implements the controlled date reentered.
According to an aspect of the present invention, in the step e, implemented according to the spacecraft of Step d selection controlled
The date reentered selects reliable space-based or ground observing and controlling tracking condition by the running track on the day of calculating spacecraft, comes
Determine the circle time for implementing each secondary drop rail control.
A scheme according to the present invention, spacecraft is controlled reenter before, complete spacecraft platform state setting, guarantee
The controlled reentry trajectory control period state of spacecraft operates normally, and completes pose adjustment, guarantees that controlled reentry trajectory control is
Rail control is dropped.It will to drop rail control implementation 1~2 time or more orbits controlling according to the type of the characteristic of engine and spacecraft
The perigee altitude of spacecraft is down to atmosphere hereinafter, spacecraft ablation under the action of atmosphere aerodynamic force and Aerodynamic Heating is made to disintegrate
It passes away in ground presumptive area.
A scheme according to the present invention, if control can the booting duration of the engine according to needed for during controlled reenter by several times
It determines, if the engine available machine time being calculated is longer, illustrates that gravity loss is larger, if engine booting duration is more than rail
The 10% of road period then takes the controlled mode reentered in batches, to reduce rail control error, improves and settles in an area after implementing to reenter control
Precision.
A scheme according to the present invention controlled to the implementation of the spacecraft after completion task can reenter, avoid spacecraft
As space junk.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 schematically shows the controlled flow chart for reentering design method of settling in an area of spacecraft according to the present invention.
Fig. 2 schematically shows a kind of controlled stream for reentering design method of settling in an area of the spacecraft of embodiment according to the present invention
Cheng Tu.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
In the present invention, spacecraft is under the premise of meeting constraint condition, can complete the direct of spacecraft and controlled reenter.
Therefore, implement spacecraft according to the present invention it is controlled reenter settle in an area design method before, it should be ensured that spacecraft meet needed for skill
Art condition and constraint condition.
In the present invention, technical conditions and constraint condition needed for spacecraft include:
1. the Key Platforms functions such as spacecraft energy power supply and distribution, Attitude and orbit control, telemetry communication, thermal control meet minimum
It is controlled to reenter requirement.
2. ground observing and controlling condition meets ground surveillance and emergency disposal requirement during test.
3. the controlled region that reenters meets requirement of settling in an area.
4. the controlled process solar irradiation condition that reenters meets spacecraft energy balance operating condition.
Fig. 1 schematically shows the controlled flow chart for reentering design method of settling in an area of spacecraft according to the present invention.Such as Fig. 1 institute
Show, spacecraft according to the present invention is controlled reenter settle in an area design method the following steps are included:
A. according to the controlled running track of spacecraft, judge Spacecraft Attitude Control propellant waste, then corresponding selection
Spacecraft reentry embodiment；
B. judge spacecraft engine operation duration, then corresponding selection implements drop rail control program；
C. the controlled posture for reentering period drop rail control of spacecraft is determined；
D. selection spacecraft implements the controlled date reentered；
E. selection spacecraft implements the controlled circle time reentered.
Fig. 2 schematically shows a kind of controlled stream for reentering design method of settling in an area of the spacecraft of embodiment according to the present invention
Cheng Tu.As shown in Fig. 2, a kind of embodiment according to the present invention, in above-mentioned a step, spacecraft is under atmospheric drag effect
In attenuation process, when the propulsion dosage of Spacecraft Attitude Control consumption is greater than pushing away for the corresponding drop rail consumption of orbit altitude of decaying
Into dosage, rail control is dropped by directly implementing, makes Spacecraft reentry atmosphere and passes away in ground；
Dosage is promoted to be less than or equal to the corresponding drop rail consumption of the orbit altitude to decay when Spacecraft Attitude Control consumption
, can be under atmospheric drag effect, when orbit altitude being made to decay to certain altitude when promoting dosage, then implement to drop rail control, make to navigate
Its device atmospheric reentry simultaneously passes away in ground.
In the present invention, directly it is controlled reenter as spacecraft task after, implement from current running track height
Rail control is dropped, makes Spacecraft reentry atmosphere and passes away in ground.
Indirectly it is controlled reenter as spacecraft task after, run a period of time after, under the action of atmospheric drag, decaying
When to certain altitude, implements drop rail control, make Spacecraft reentry atmosphere and pass away in ground.
A kind of embodiment according to the present invention when spacecraft engine operating duration is longer, implements spacecraft drop in batches
Rail control；
When spacecraft engine operating duration is shorter, implement the drop rail control of spacecraft single.
A kind of embodiment according to the present invention, in above-mentioned step c, according to the b step embodiment and use
Precise tracking installation site adjustment spacecraft it is controlled reenter during drop rail control posture, so that precise tracking is carried out drop rail
The speed increment direction generated when control is opposite with heading.
A kind of embodiment according to the present invention, in above-mentioned Step d, the spacecraft determined according to the step c is controlled
Posture during reentering when the control of drop rail makes the spacecraft energy reenter the phase controlled by selecting suitable solar irradiation condition
Between be in equilibrium state, so that it is determined that spacecraft implements the controlled date reentered.
A kind of embodiment according to the present invention is implemented in above-mentioned step e according to the spacecraft of Step d selection
The controlled date reentered selects reliable space-based or ground observing and controlling trackbar by the running track on the day of calculating spacecraft
Part, to determine the circle time for implementing each secondary drop rail control.
Design method according to the present invention, when meeting above-mentioned condition, spacecraft is controlled reenter before, it is flat to complete spacecraft
The state of platform is arranged, and guarantees that the controlled reentry trajectory control period state of spacecraft operates normally, and complete pose adjustment, guarantee by
Reentry trajectory control is controlled as drop rail control.According to the type of the characteristic of engine and spacecraft, drop rail control is implemented 1~2 time
The perigee altitude of spacecraft is down to atmosphere hereinafter, making spacecraft in atmosphere aerodynamic force and pneumatic by above orbits controlling
Ablation disintegration is passed away in ground presumptive area under the action of heat.
Design method according to the present invention, if control can the booting duration of the engine according to needed for during controlled reenter by several times
It determines, if the engine available machine time being calculated is longer, illustrates that gravity loss is larger, if engine booting duration is more than rail
The 10% of road period then takes the controlled mode reentered in batches, to reduce rail control error, improves and settles in an area after implementing to reenter control
Precision.
From the foregoing, it will be observed that design method according to the present invention, controlled to the implementation of the spacecraft after completion task can reenter, keep away
Exempt from spacecraft as space junk.
The foregoing is merely an embodiment of the invention, are not intended to restrict the invention, for this field
For technical staff, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (6)
1. a kind of spacecraft is controlled to reenter design method of settling in an area, comprising the following steps:
A. according to the controlled running track of spacecraft, judge Spacecraft Attitude Control propellant waste, then corresponding selection space flight
Device reenters embodiment；
B. judge spacecraft engine operation duration, then corresponding selection implements drop rail control program；
C. the controlled posture for reentering period drop rail control of spacecraft is determined；
D. selection spacecraft implements the controlled date reentered；
E. selection spacecraft implements the controlled circle time reentered.
2. spacecraft according to claim 1 is controlled to reenter design method of settling in an area, which is characterized in that in a step,
Spacecraft in attenuation process, promotes dosage to be greater than the track decayed under atmospheric drag effect when Spacecraft Attitude Control consumption
Highly it is corresponding drop rail consumption propulsion dosage, by directly implement drop rail control, make Spacecraft reentry atmosphere and pass away in
Ground；
Dosage is promoted to be less than or equal to the corresponding propulsion for dropping rail consumption of the orbit altitude to decay when Spacecraft Attitude Control consumption
, can be under atmospheric drag effect, when orbit altitude being made to decay to certain altitude when dosage, then implement to drop rail control, make spacecraft
Atmospheric reentry simultaneously passes away in ground.
3. spacecraft according to claim 1 is controlled to reenter design method of settling in an area, which is characterized in that in the b step,
Spacecraft engine operating duration be greater than the orbital period 10% when, by spacecraft it is controlled reenter drop rail control be divided into twice with
The engine operating duration of upper execution, the drop rail control executed every time is less than or equal to the 10% of the orbital period；
When spacecraft engine operating duration is less than or equal to the 10% of orbital period, implement the drop rail control of spacecraft single.
4. spacecraft according to claim 3 is controlled to reenter design method of settling in an area, which is characterized in that in the step c,
Period drop rail control is reentered according to the b step embodiment and the precise tracking installation site used adjustment spacecraft are controlled
The posture of system, the speed increment direction for generating precise tracking when carrying out drop rail control are opposite with heading.
5. spacecraft according to claim 3 is controlled to reenter design method of settling in an area, which is characterized in that in the Step d,
The controlled posture reentered when period drop rail controls of the spacecraft determined according to the step c, passes through and selects suitable solar irradiation
Condition makes the spacecraft energy during controlled reenter in equilibrium state, so that it is determined that spacecraft implements the controlled date reentered.
6. spacecraft according to claim 3 is controlled to reenter design method of settling in an area, which is characterized in that in the step e,
Implement the controlled date reentered according to the spacecraft that the Step d selects, passes through the running track on the day of calculating spacecraft, selection
Reliable space-based or ground observing and controlling tracking condition, to determine the circle time for implementing each secondary drop rail control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810907411.7A CN109094819B (en) | 2018-08-10 | 2018-08-10 | Spacecraft controlled reentry landing area design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810907411.7A CN109094819B (en) | 2018-08-10 | 2018-08-10 | Spacecraft controlled reentry landing area design method |
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| Publication Number | Publication Date |
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| CN109094819A true CN109094819A (en) | 2018-12-28 |
| CN109094819B CN109094819B (en) | 2020-06-05 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101725A (en) * | 2018-08-10 | 2018-12-28 | 北京空间技术研制试验中心 | Spacecraft is controlled to reenter predicting method of settling in an area |
| CN111241634A (en) * | 2019-11-19 | 2020-06-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Analysis and forecast method for reentry of spacecraft into meteor space |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101725A (en) * | 2018-08-10 | 2018-12-28 | 北京空间技术研制试验中心 | Spacecraft is controlled to reenter predicting method of settling in an area |
| CN109101725B (en) * | 2018-08-10 | 2023-01-20 | 北京空间技术研制试验中心 | Spacecraft controlled reentry landing area prediction method |
| CN111241634A (en) * | 2019-11-19 | 2020-06-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Analysis and forecast method for reentry of spacecraft into meteor space |
| CN111241634B (en) * | 2019-11-19 | 2022-04-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Analysis and forecast method for reentry of spacecraft into meteor space |
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| Publication number | Publication date |
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| CN109094819B (en) | 2020-06-05 |
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