CN106542119A - On star, autonomous Orbit maintains control method - Google Patents
On star, autonomous Orbit maintains control method Download PDFInfo
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- CN106542119A CN106542119A CN201610898405.0A CN201610898405A CN106542119A CN 106542119 A CN106542119 A CN 106542119A CN 201610898405 A CN201610898405 A CN 201610898405A CN 106542119 A CN106542119 A CN 106542119A
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- satellite
- average
- major axis
- orbit
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Classifications
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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
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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
Abstract
On a kind of star, autonomous Orbit maintains control method, including：Determine satellite orbital position and satellite velocity information；By the satellite orbital position and satellite velocity information, calculate and obtain satellite mean orbit parameter, including average semi-major axis；The average semi-major axis for obtaining then opens thruster less than the average semi-major axis lower limit of design, improves average semi-major axis；When the average semi-major axis for obtaining brings up to the average semi-major axis upper limit of design, then thruster is closed.Said method can realize the Autonomous maintenance of the orbit altitude under different atmospheric environments.
Description
Technical field
The present invention relates to autonomous Orbit maintains control method on space technology field, more particularly to a kind of star.
Background technology
Ultralow track refers to flight in exoatmosphere, but less than the track of common spacecraft orbit height, is often referred to track
Height is in more than 120km, the flight track of below 300km.Ultralow track has larger military and scientific meaning, but due to rail
Road is highly low, and in ultralow orbital flight, atmospheric drag affects notable to track, if not carrying out track maintenance, satellite orbit meeting
It is rapid to decay, how to realize that ultralow track autonomous Orbit remains significant.
Traditional non-resistance satellite technology is built-in one or more masses in the satel-lite, by controlling satellite and mass
Maintain isolation from each other state and eliminate atmospheric interference.The technology needs high-precision attitude measurement and stability contorting, Er Qieyou
In the inhomogeneities of atmospheric drag, continuously adjustable thrust is needed, and existing ripe its thrust size of propulsion product is non-adjustable, its
Using by a definite limitation.
It is therefore desirable to propose that autonomous Orbit maintains control method on a kind of star, it is high to adapt to different atmospheric environment lower railway
The Autonomous maintenance of degree.
The content of the invention
The technical problem to be solved is to provide autonomous Orbit on a kind of star and maintains control method, realizes different
The Autonomous maintenance of the orbit altitude under atmospheric environment.
In order to solve the above problems, the invention provides autonomous Orbit maintains control method on a kind of star, including：It is determined that defending
Star orbital position and satellite velocity；Calculate and obtain satellite mean orbit parameter, including average semi-major axis；It is average when what is obtained
Semi-major axis then opens thruster less than the average semi-major axis lower limit of design, improves average semi-major axis；When the average semi-major axis for obtaining
When bringing up to the average semi-major axis upper limit of design, then thruster is closed.
Optionally, the acquisition frequency of satellite mean orbit parameter is 1Hz.
Optionally, the satellite mean orbit parameter also includes average eccentric rate.
Optionally, if current average eccentric rate opens thrust in average apogee more than the design average eccentric rate upper limit
Gas carries out jet, and the jet time is to be pre-designed duration.
Optionally, the design average eccentric rate upper limit is 0.001.
Optionally, the satellite includes：GPS module, for outside data processing module transmission satellite orbital position and
Satellite velocity information；External data processing module, for processing the satellite orbital position and satellite velocity that receive
Information, calculates and obtains satellite mean orbit parameter, and send to orbits controlling module；Orbits controlling module receives the average rail of satellite
Road parameter, sends order parameter to thruster, controls being turned on and off for thruster.
It is an advantage of the current invention that the maintenance strategy of the thruster switch fed back based on mean orbit semi-major axis, to satellite
Carry out track and maintain control, the control method is simple and reliable, robustness is high, it is possible to achieve given orbit altitude is maintained, and fuel disappears
Consumption is reasonable, can meet the ultralow orbital flight of long-time.
Further, technical scheme is also adjusted to the average eccentric rate of satellite flight, so as to defending
The maintenance of star orbit altitude is more stable and accurate.
Description of the drawings
Fig. 1 maintains schematic diagram for autonomous Orbit on the star of the embodiment of the present invention；
Fig. 2 maintains schematic diagram for autonomous Orbit on the star of the embodiment of the present invention.
Specific embodiment
The specific embodiment of control method is maintained to do specifically the autonomous Orbit that the present invention is provided below in conjunction with the accompanying drawings
It is bright.
As orbit altitude h and the earth's core are differed only by as an earth radius R away from re, so maintenance for orbit altitude h etc.
Valency, is realized to rail so the present invention selects the earth's core away from r as control parameter by controlling the earth's core away from r in maintaining away from r to the earth's core
The maintenance control in road.
Consider compression of the Earth first order perturbation, expression formula of the earth's core away from r is：
The earth's core is away from r changes containing average semi-major axis amWith average eccentric ratio emRelated secular change, and the nearly angle of Average True
fmWith mean latitude argument umRelated cyclically-varying, above formula can be rewritten as
r≈am+δrc+δrsp
Wherein：δrcIt is the secular term caused due to the compression of the Earth, its expression formula is
For the nearly polar orbits of 120km, δ rcValue be about 4.8km, orbit altitude changes to δ rcChange very little.
δrspFor average true anomaly fmWith mean latitude argument umRelated periodic term, its size is mainly and average eccentric
Rate emCorrelation, its expression formula is：
For the nearly polar orbits of 120km, if average eccentric rate emLess than 0.001, δ rspMaximum be about 8.2km.
The δ rcWith δ rspIn the track of differing heights, and the change under different atmospheric environments is less, so, Ke Yitong
Cross to average semi-major axis amMaintenance, realize maintenance for the earth's core away from r.
As the thrust of atmospheric drag and satellite propulsion unit is dissipative force, average semi-major axis a can be causedmApproximately linear becomes
Change.If by mean orbit semi-major axis amWithin the specific limits, then the earth's core will be also maintained in corresponding scope away from r, institute for control
With can be by mean orbit semi-major axis amControl, realize control to the earth's core away from r, and then realize to satellite orbit
Maintain control.
For average semi-major axis amControl, it is only necessary to adjust tangential thrust, and utilize mean orbit semi-major axis amAs
The foundation of thruster switch, does not have special demand to thrust size, and the little then adjustment time of thrust is longer, when thrust is then adjusted greatly
Between it is shorter, control system can be simplified.
Specifically, on the star of the embodiment of the present invention, Autonomous maintenance control method includes：Satellite orbit is determined by GPS module
Position and satellite velocity；Calculate and obtain satellite mean orbit parameter, including average semi-major axis；When the average semi-major axis for obtaining
Less than average semi-major axis lower limit is designed, then thruster is opened, improve average semi-major axis；When the average semi-major axis for obtaining brings up to
When designing the average semi-major axis upper limit, then thruster is closed.
Fig. 1 is refer to, is that autonomous Orbit maintains schematic diagram on star.
If current average semi-major axis amIt is reduced to the average semi-major axis lower limit a of designmin, then thruster is opened, average half is made
Major axis amGradually rise；If current average semi-major axis amBring up to the average semi-major axis of design and obtain upper limit aref, then close thruster.Push away
After power device cuts out, as atmospheric drag causes dissipation of energy, orbit averaging semi-major axis amThen start to reduce, continue repetition above-mentioned
Set-up procedure, makes current average half-court axle amAll the time maintain upper limit a of average semi-major axisrefWith lower limit aminBetween, so as to
Realize the maintenance to orbit altitude.
Further, since atmospheric drag change is violent in each orbital period, cause thrust switch uneven, to eccentricity shadow
Ring with accumulative effect so that eccentricity is continuously increased so as to have influence on the earth's core away from r.In order to prevent eccentricity from dissipating, the present invention
Embodiment also include being adjusted average eccentric rate.
In one embodiment of the invention, calculating the satellite mean orbit parameter for obtaining also includes average eccentric rate.Tool
Body, if current average eccentric rate emMore than the design average eccentric rate upper limit, then thruster is opened in average apogee and sprayed
Gas, for simplify control difficulty, implements jet time to be pre-designed duration, after jet duration reaches is pre-designed duration,
Stop jet, no matter currently average eccentric rate emWhether the average eccentric rate upper limit is also greater than designed；If current average eccentric rate emAccording to
It is old that more than the design average eccentric rate upper limit, then when satellite arrives again at average apogee, being again turned on thruster carries out jet,
Average eccentric rate is adjusted, is adjusted by one or many, is made current average eccentric rate emIt is average equal to or less than design
The upper limit of eccentricity.
Used as one embodiment of the present of invention, the design average eccentric rate upper limit is 0.001.By to average eccentric rate
Control, more can accurately realize the control to orbit altitude.
Also, above-mentioned control method is simple and reliable, robustness is high, and fuel consumption rationally, can meet the ultralow rail of long-time
Road flight is required.
Further, the track maintains control by independently completing on star.
Fig. 2 is refer to, is that autonomous Orbit maintains schematic diagram on star.
The satellite includes：GPS module 101, for transmitting satellite orbital position to outside data processing module 102 and defending
Star speed of service information；External data processing module 102, for processing the satellite orbital position and satellite velocity that receive
Information, calculates and obtains satellite mean orbit parameter, and send to orbits controlling module 103；Orbits controlling module 103 is according to satellite
Mean orbit parameter, sends to thruster 104 and instructs, and controls being turned on and off for thruster 104, and the external data processes mould
Block 102, orbits controlling module 103 and thruster 104 belong to the control system 105 of satellite.
Satellite orbital position and satellite velocity information of the external data processing module 102 by acquisition, obtain current
The mean orbit parameter of satellite.Used as one embodiment of the present of invention, the acquisition frequency of the mean orbit parameter of the satellite is
1Hz, it is accurate to obtain satellite transit orbit information, so as to realize the precise control to orbit altitude.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
Member, under the premise without departing from the principles of the invention, can also make some improvements and modifications, and these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (6)
1. on a kind of star, autonomous Orbit maintains control method, it is characterised in that include：
Determine satellite orbital position and satellite velocity information；
By the satellite orbital position and satellite velocity information, calculate and obtain satellite mean orbit parameter, including it is average
Semi-major axis；
When the average semi-major axis for obtaining is less than the average semi-major axis lower limit of design, then thruster is opened, improve average semi-major axis；
When the average semi-major axis for obtaining brings up to the average semi-major axis upper limit of design, then thruster is closed.
2. on star according to claim 1, autonomous Orbit maintains control method, it is characterised in that the satellite mean orbit
Parameter also includes average eccentric rate.
3. on star according to claim 2, autonomous Orbit maintains control method, it is characterised in that if current average eccentric rate
More than the design average eccentric rate upper limit, then opening thrust gas in average apogee carries out jet, and the jet time is to set in advance
Timing is long.
4. on star according to claim 3, autonomous Orbit maintains control method, it is characterised in that the design average eccentric
The rate upper limit is 0.001.
5. on star according to claim 1 and 2, autonomous Orbit maintains control method, it is characterised in that satellite mean orbit
The acquisition frequency of parameter is 1Hz.
6. on star according to claim 1 and 2, autonomous Orbit maintains control method, it is characterised in that the satellite includes：
GPS module, for transmitting satellite orbital position and satellite velocity information to outside data processing module；External data process
Module, for processing the satellite orbital position and satellite velocity information that receive, calculates and obtains satellite mean orbit parameter,
And send to orbits controlling module；Orbits controlling module receives satellite mean orbit parameter, sends order parameter, control to thruster
Controlling push-force device is turned on and off.
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| CN201610898405.0A CN106542119B (en) | 2016-10-14 | 2016-10-14 | On-satellite autonomous orbit maintenance control method |
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| CN201610898405.0A CN106542119B (en) | 2016-10-14 | 2016-10-14 | On-satellite autonomous orbit maintenance control method |
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| CN106542119B CN106542119B (en) | 2020-05-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111989265A (en) * | 2019-11-26 | 2020-11-24 | 中国科学院微小卫星创新研究院 | Autonomous maintenance method for ultralow orbit satellite orbit |
| CN113998150A (en) * | 2021-11-29 | 2022-02-01 | 航天东方红卫星有限公司 | Ultra-low orbit satellite full-electric propulsion orbit maintaining system |
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| US6439507B1 (en) * | 2000-05-05 | 2002-08-27 | Space Systems/Loral, Inc. | Closed-loop spacecraft orbit control |
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| CN113998150A (en) * | 2021-11-29 | 2022-02-01 | 航天东方红卫星有限公司 | Ultra-low orbit satellite full-electric propulsion orbit maintaining system |
| CN113998150B (en) * | 2021-11-29 | 2024-02-09 | 航天东方红卫星有限公司 | Ultra-low orbit satellite full-electric propulsion orbit maintaining system |
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