CN106542119B - On-satellite autonomous orbit maintenance control method - Google Patents

On-satellite autonomous orbit maintenance control method Download PDF

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CN106542119B
CN106542119B CN201610898405.0A CN201610898405A CN106542119B CN 106542119 B CN106542119 B CN 106542119B CN 201610898405 A CN201610898405 A CN 201610898405A CN 106542119 B CN106542119 B CN 106542119B
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satellite
average
orbit
major axis
semi
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CN106542119A (en
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吴宅莲
本立言
朱让剑
吴会英
齐金玲
陈宏宇
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Shanghai Engineering Center for Microsatellites
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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
    • 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

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Abstract

An on-board autonomous orbit maintenance control method, comprising: determining satellite orbit position and satellite operation speed information; calculating and acquiring satellite average orbit parameters including an average semi-major axis according to the satellite orbit position and the satellite running speed information; if the obtained average semi-major axis is lower than the lower limit of the designed average semi-major axis, opening the thruster to improve the average semi-major axis; and when the acquired average semi-major axis is increased to the upper limit of the designed average semi-major axis, closing the thruster. The method can realize the autonomous maintenance of the track height under different atmospheric environments.

Description

On-satellite autonomous orbit maintenance control method
Technical Field
The invention relates to the technical field of spaceflight, in particular to a satellite autonomous orbit maintenance control method.
Background
The ultra-low orbit is an orbit which flies outside the atmosphere and is lower than the orbit height of a common spacecraft, and generally refers to a flying orbit with the orbit height of more than 120km and less than 300 km. The ultra-low orbit has great military and scientific significance, but because the orbit height is low, the atmospheric resistance has obvious influence on the orbit when the ultra-low orbit flies, and if the orbit is not maintained, the satellite orbit can be quickly attenuated, so that the significance of how to realize the autonomous orbit maintenance of the ultra-low orbit is great.
In the traditional non-resistance satellite technology, one or more mass blocks are built in a satellite, and atmospheric interference is eliminated by controlling the satellite and the mass blocks to keep an isolated state. The technology needs high-precision attitude measurement and stable control, continuous adjustable thrust is needed due to non-uniformity of atmospheric resistance, and the thrust of the existing mature propulsion product is not adjustable, so that the application of the existing mature propulsion product is limited to a certain extent.
Therefore, it is necessary to provide a method for maintaining and controlling an autonomous orbit on a satellite to adapt to autonomous maintenance of the orbit height under different atmospheric environments.
Disclosure of Invention
The invention aims to solve the technical problem of providing a satellite autonomous orbit maintaining control method to realize autonomous maintenance of orbit heights in different atmospheric environments.
In order to solve the above problem, the present invention provides a method for maintaining and controlling an autonomous orbit on a satellite, comprising: determining the satellite orbit position and the satellite running speed; calculating to obtain satellite average orbit parameters including an average semi-major axis; when the obtained average semi-major axis is lower than the lower limit of the designed average semi-major axis, opening the thruster to improve the average semi-major axis; and when the acquired average semi-major axis is increased to the upper limit of the designed average semi-major axis, closing the thruster.
Optionally, the acquisition frequency of the satellite average orbit parameter is 1 Hz.
Optionally, the satellite average orbit parameter further includes an average eccentricity.
Optionally, if the current average eccentricity is greater than the designed upper limit of the average eccentricity, the thrust air is opened at an average far place to jet air, and the air jet time is a preset time.
Optionally, the upper design average eccentricity limit is 0.001.
Optionally, the satellite includes: the GPS module is used for transmitting the satellite orbit position and the satellite running speed information to the external data processing module; the external data processing module is used for processing the received satellite orbit position and satellite running speed information, calculating to obtain satellite average orbit parameters and sending the satellite average orbit parameters to the orbit control module; and the orbit control module receives the average orbit parameters of the satellite, sends instruction parameters to the thruster and controls the opening or closing of the thruster.
The method has the advantages that the orbit maintenance control is carried out on the satellite based on the maintenance strategy of the thruster switch fed back by the average orbit semimajor axis, the control method is simple and reliable, the robustness is high, the maintenance of the given orbit height can be realized, the fuel consumption is reasonable, and the requirement of long-time ultralow orbit flight can be met.
Furthermore, the technical scheme of the invention also adjusts the average eccentricity of the satellite flight, thereby ensuring that the maintenance of the satellite orbit height is more stable and accurate.
Drawings
FIG. 1 is a schematic diagram of an on-board autonomous orbit maintenance in accordance with an embodiment of the present invention;
fig. 2 is a schematic diagram of an on-board autonomous orbit maintenance according to an embodiment of the present invention.
Detailed Description
The following describes in detail a specific embodiment of the autonomous trajectory maintenance control method according to the present invention with reference to the accompanying drawings.
The orbit height h and the earth center distance R only differ by one earth radius ReTherefore, since the maintenance of the track height h is equivalent to the maintenance of the center-to-ground distance r, the present invention selects the center-to-ground distance r as a control parameter and controls the center-to-ground distance r to realize the track maintenance control.
Considering first-order perturbation of earth oblateness, the expression of the earth center distance r is as follows:
Figure BDA0001131062470000021
the variation of the center-to-earth distance r contains an average semimajor axis amAnd average eccentricity emAssociated long-term variation, and mean true angle of approach fmAnd mean latitude argument umThe above formula can be rewritten as
r≈am+δrc+δrsp
Wherein: delta rcIs a long term due to the oblateness of the earth and has the expression
Figure BDA0001131062470000022
For 120km near polar earth orbit, δ rcHas a value of about 4.8km, track height variation pair deltarcThe change in (c) is small.
δrspIs the mean true paraxial angle fmAnd mean latitude argument umPeriod term of interest, whose magnitude is primarily related to the average eccentricity emCorrelationThe expression is as follows:
Figure BDA0001131062470000031
for a 120km near polar track, average eccentricity emNot more than 0.001, δ rspIs about 8.2 km.
The delta rcAnd δ rspThe track at different heights and different atmospheric environments have small change, so the average semi-major axis a can be adjustedmThe maintenance of the geocentric distance r is realized.
Because the atmospheric resistance and the thrust of the satellite propeller are dissipative forces, the average semi-major axis a can be causedmApproximately linearly. If the semi-major axis a of the track is to be averagedmIf the control is within a certain range, the earth center distance r will be maintained within the corresponding range, so the average orbit semi-major axis a can be controlledmThe control of (3) realizes the control of the earth center distance r, and further realizes the maintenance control of the satellite orbit.
For the average semi-major axis amControl by adjusting only the tangential thrust and by using the mean orbit semi-major axis amAs the basis of the switch of the thruster, no special requirement is needed for the thrust, the adjustment time is longer when the thrust is small, and the adjustment time is shorter when the thrust is large, so that a track control system can be simplified.
Specifically, the on-satellite autonomous maintenance control method of the embodiment of the present invention includes: determining the satellite orbit position and the satellite running speed through a GPS module; calculating to obtain satellite average orbit parameters including an average semi-major axis; when the obtained average semi-major axis is lower than the lower limit of the designed average semi-major axis, opening the thruster to improve the average semi-major axis; and when the acquired average semi-major axis is increased to the upper limit of the designed average semi-major axis, closing the thruster.
Please refer to fig. 1, which is a schematic diagram of autonomous orbit maintenance on a satellite.
If the current average semi-major axis amIs reduced to the lower limit a of the design average semi-major axisminThen the thruster is opened to make the average semi-major axis amGradually increasing; if the current average semi-major axis amTo the upper limit a of the design average semi-major axisrefAnd closing the thruster. After the thruster is closed, the average semi-major axis a of the track is dissipated due to energy dissipation caused by atmospheric resistancemThen the process starts to decrease and continues to repeat the above adjustment steps to make the current average half-field axis amAlways maintained at the upper limit a of the average semi-major axisrefAnd a lower limit of aminThereby achieving the maintenance of the track height.
In addition, because the atmospheric resistance changes violently in each orbit period, the thrust switch is not uniform, and the influence on the eccentricity has an accumulative effect, so that the eccentricity is increased continuously to influence the ground center distance r. To prevent eccentricity from diverging, embodiments of the present invention further include adjusting the average eccentricity.
In one embodiment of the invention, calculating the acquired satellite average orbit parameters further comprises average eccentricity. In particular, if the current average eccentricity emIf the average eccentricity is greater than the designed average eccentricity upper limit, the thruster is started at the average far place for jetting, in order to simplify the control difficulty, the jet time is the pre-designed time, when the jet time reaches the pre-designed time, the jet is stopped no matter the current average eccentricity emWhether the average eccentricity is still larger than the design average eccentricity upper limit; if the current average eccentricity emIf the average eccentricity is still larger than the designed average eccentricity upper limit, the thruster is opened again to jet air when the satellite arrives at the average far point again, the average eccentricity is adjusted, and the current average eccentricity e is adjusted once or for multiple timesmEqual to or less than the upper limit of the design average eccentricity.
As an embodiment of the present invention, the upper limit of the design average eccentricity is 0.001. The control of the height of the track can be more accurately realized by controlling the average eccentricity.
Moreover, the control method is simple and reliable, high in robustness and reasonable in fuel consumption, and can meet the requirement of long-time ultralow orbit flight.
Further, the orbit maintenance control is autonomously completed by the satellite.
Please refer to fig. 2, which is a schematic diagram of the autonomous orbit maintenance on the satellite.
The satellite includes: a GPS module 101 for transmitting satellite orbit position and satellite operation speed information to an external data processing module 102; the external data processing module 102 is configured to process the received satellite orbit position and satellite operating speed information, calculate and obtain a satellite average orbit parameter, and send the satellite average orbit parameter to the orbit control module 103; the orbit control module 103 sends an instruction to the thruster 104 according to the average orbit parameter of the satellite, and controls the thruster 104 to be turned on or off, and the external data processing module 102, the orbit control module 103 and the thruster 104 all belong to a control system 105 of the satellite.
The external data processing module 102 obtains the average orbit parameter of the current satellite according to the acquired satellite orbit position and the satellite operation speed information. As an embodiment of the invention, the acquisition frequency of the average orbit parameter of the satellite is 1Hz, and the orbit information of the satellite is accurately acquired, thereby realizing the accurate control of the orbit height.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims (6)

1. An on-board autonomous orbit maintenance control method for maintaining an orbital altitude of a satellite in ultra-low orbit flight, comprising:
determining satellite orbit position and satellite operation speed information;
calculating and obtaining satellite average orbit parameters including an average semi-major axis through the satellite orbit position and the satellite running speed information, and taking the average semi-major axis as the basis of a thruster switch;
when the obtained average semimajor axis is lower than the lower limit of the designed average semimajor axis, opening the thruster, and adjusting the tangential thrust to improve the average semimajor axis;
and when the acquired average semi-major axis is increased to the upper limit of the designed average semi-major axis, closing the thruster.
2. The on-board autonomous orbit maintenance control method of claim 1, wherein the satellite average orbit parameters further comprise an average eccentricity.
3. The on-board autonomous orbit maintenance control method according to claim 2, wherein if the current average eccentricity is greater than the design average eccentricity upper limit, the thrust air is opened at the average far point to inject air, and the time for injecting air is a pre-designed time period.
4. The on-board autonomous orbit maintaining control method according to claim 3, wherein the design average eccentricity upper limit is 0.001.
5. The on-satellite autonomous orbit maintenance control method according to claim 1 or 2, characterized in that the acquisition frequency of the satellite average orbit parameter is 1 Hz.
6. The on-satellite autonomous orbit maintenance control method according to claim 1 or 2, wherein the satellite comprises: the GPS module is used for transmitting the satellite orbit position and the satellite running speed information to the external data processing module; the external data processing module is used for processing the received satellite orbit position and satellite running speed information, calculating to obtain satellite average orbit parameters and sending the satellite average orbit parameters to the orbit control module; and the orbit control module receives the average orbit parameters of the satellite, sends instruction parameters to the thruster and controls the opening or closing of the thruster.
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CN111989265B (en) * 2019-11-26 2022-08-12 中国科学院微小卫星创新研究院 Autonomous maintenance method for ultralow orbit satellite orbit
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CN102591343A (en) * 2012-02-09 2012-07-18 航天东方红卫星有限公司 Satellite orbit maintenance and control method based on two lines of radicals
CN102880184A (en) * 2012-10-24 2013-01-16 北京控制工程研究所 Autonomous orbit control method for stationary orbit satellite
CN103303496A (en) * 2013-06-28 2013-09-18 上海新跃仪表厂 Method for regulating orbit altitude slightly
CN103818564A (en) * 2014-03-04 2014-05-28 中国人民解放军国防科学技术大学 Integrated control method adopting low-thrust spacecraft orbit maintaining and to-earth orientation posture keeping
CN104015938A (en) * 2014-05-07 2014-09-03 北京理工大学 Position keeping method of electric propulsion stationary orbit satellite

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US3995801A (en) * 1974-07-05 1976-12-07 Rca Corporation Method of storing spare satellites in orbit
US6439507B1 (en) * 2000-05-05 2002-08-27 Space Systems/Loral, Inc. Closed-loop spacecraft orbit control
CN102591343A (en) * 2012-02-09 2012-07-18 航天东方红卫星有限公司 Satellite orbit maintenance and control method based on two lines of radicals
CN102880184A (en) * 2012-10-24 2013-01-16 北京控制工程研究所 Autonomous orbit control method for stationary orbit satellite
CN103303496A (en) * 2013-06-28 2013-09-18 上海新跃仪表厂 Method for regulating orbit altitude slightly
CN103818564A (en) * 2014-03-04 2014-05-28 中国人民解放军国防科学技术大学 Integrated control method adopting low-thrust spacecraft orbit maintaining and to-earth orientation posture keeping
CN104015938A (en) * 2014-05-07 2014-09-03 北京理工大学 Position keeping method of electric propulsion stationary orbit satellite

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