CN103303496A - Method for regulating orbit altitude slightly - Google Patents
Method for regulating orbit altitude slightly Download PDFInfo
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- CN103303496A CN103303496A CN2013102663777A CN201310266377A CN103303496A CN 103303496 A CN103303496 A CN 103303496A CN 2013102663777 A CN2013102663777 A CN 2013102663777A CN 201310266377 A CN201310266377 A CN 201310266377A CN 103303496 A CN103303496 A CN 103303496A
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Abstract
The invention provides a method for regulating an orbit altitude slightly. In a steady-state flywheel control mode, a fixed jet pulse width is sent to a thruster at a fixed time by using a spray thrust in the tangential direction of an orbit, thus achieving a slight regulation of the orbit altitude of a satellite. The method for regulating the orbit altitude slightly comprises the following steps: determining a spray nozzle of the thruster; calculating a constraint on the thruster, which is required by maintaining a steady-state control state of a flywheel; and according to the orbit altitude which is planned to be regulated, calculating the fixed pulse width of the thruster. Compared with the prior art, the method has the advantages as follows: by the method, the control flow of the satellite is simplified, complex switching between satellite modes is avoided, and an aim of maintaining the orbit altitude can be achieved.
Description
Technical field
The present invention relates to satellite attitude and track control technology, especially use the method for jet some spray fine tune satellite orbit on the basis of the steady attitude control of flywheel.
Background technology
The high spectral resolution satellite is equipped with a plurality of capacity weights, in order to satisfy the covering continuity of the narrow visual field of satellite camera, adopts 5 days accurate recursive orbit cycles, and the overlay area between two recursion periods all covers continuously.According to the load need of work, satellite must have attitude side-sway function and just can finish the work; Simultaneously satellite orbital altitude is required very strictly, must remain on about the nominal track ± 300 meters.If frequent injection master mode, pattern switching flow according to design, need excise flywheel and magnetic dumping, open gyroassembly and thruster, a series of complicated dead works of solar array stall maintenance etc. are after the rail control finishes, need to recover stable state flywheel state of a control again and carry out recovery operation, in order to reduce the human element operational risk, be reduced at rail fine tune orbit altitude flow process, be necessary to design the simple method of a cover.
Summary of the invention
At the deficiency that prior art exists, the technical problem to be solved in the present invention provides a kind of method of readjusting by a small margin orbit altitude, makes on the basis that does not change the control of flywheel stable state, to the mode that thruster uses point to spray, realizes orbit altitude is readjusted by a small margin.
Technical scheme of the present invention provides a kind of method of readjusting by a small margin orbit altitude, uses thruster point spray mode to realize that it may further comprise the steps to the satellite orbital altitude fine tune:
1) determining can be along the thruster nozzle of track tangential direction applied thrust;
2) constraint that flywheel stable state state of a control need be exported jet situation to thruster is kept in calculating;
3) orbit altitude of adjusting according to plan is calculated the quantity of thruster fixed pulse width.
Described step 1)-2) in, pulse width and the time gap between the pulse width that thruster is exported have certain constraint, to guarantee attitude and the degree of stability index request of the control of stable state flywheel.
In a specific embodiment, selection can guarantee the symmetry of jet moment and attitude is produced one group of nozzle of disturbance torque minimum, calculate use described nozzle nominal thrust in setting-up time to the variable quantity of orbit altitude
Calculate the disturbance torque that described nozzle produces the satellite yaw axis, be thrust at the increment of setting-up time inner opposite angle momentum and to the influence of Satellite Angle speed, and when can satisfying the rail control, the verifying satellites degree of stability requires under the prerequisite of index, determine the sustainable work-hours of thruster, and the calculating flywheel controlled to for 0 needed time with cireular frequency
The numerical value of raising according to the track needs is divided by variable quantity
After the result obtain needing the jet time
t, again according to the time
tRound divided by the postimpulse result of each jet output and to obtain needing jet number of times
n, obtain finishing the time that the orbit altitude adjustment needs with this
T=
n*
Use ejection thrust along the thruster of track tangential direction among the present invention, under stable state flywheel master mode, send fixing jet pulsewidth in the set time for thruster, make satellite orbital altitude readjust by a small margin according to the method, the said method that the present invention adopts compared with prior art, its advantage and beneficial effect are:
Use the method to carry out the orbit altitude adjustment, simplified the control flow between master mode is switched, avoided the complexity between the satellite mode to switch, reduced the risk of people for maloperation, attitude is more steady in the adjustment process, does not influence the capacity weight normal operation.Also can be used as the backup path of adjusting track in addition, improved whole star reliability.
Description of drawings
Fig. 1 is fine tune orbit altitude workflow diagram.
The specific embodiment
The invention will be further described below with reference to drawings and Examples.
A kind of method of readjusting by a small margin orbit altitude of the present invention can to the mode that thruster uses point to spray, realize that it comprises the steps to the orbit altitude fine tune on the basis that does not change the control of flywheel stable state.
1. determine the thruster nozzle;
The thruster of mounting arrangement on satellite is a kind of actuating unit of control satellite attitude and track.Can exert an influence to satellite orbital altitude at track tangential direction applied thrust, under stable state flywheel master mode, according to the part of thruster, selection can be used for adjusting orbit altitude along the nozzle of track tangential direction applied thrust.The jet generation of the point jet module of spray of instruction shown in the accompanying drawing 1 is exactly by selected nozzle ejection.
2. calculate keep flywheel stable state state of a control need be to the constraint of thruster;
The control of flywheel stable state just as shown in Figure 1, satellite space is in service be subjected to outside the effect of disturbance torque, operation pose deviation targeted attitude must use and measure the attitude that sensor is measured, controller according to design is controlled in real time by flywheel, makes attitude stabilization at targeted attitude.Thruster is along track tangential direction applied thrust, and is influential to orbit altitude, but if thrust then produces as the jet disturbance torque in the accompanying drawing 1 without the satellite barycenter, simultaneously satellite attitude is also exerted an influence.If will meet adjusting under the track situation the index that requires of satellite attitude and degree of stability, consider the performance that flywheel is installed, must determine jet output pulse width.In addition, satellite attitude is recovered steadily to need the regular hour from being disturbed to, and then determines the time gap of the jet pulsewidth of output.
3. the orbit altitude of adjusting is as required calculated the quantity of thruster fixed pulse width;
If satellite is applied application force, the dynamic (dynamical) orbit element of satellite orbit in the accompanying drawing 1 can change, the influence that demarcation is worked under rated thrust, nominal thrust and satellite orbital altitude produced in 1 second, the orbit altitude of Tiao Zhenging as required, extrapolating thruster needs the time of work, divided by time gap, obtain exporting the quantity of jet pulsewidth.
In a specific embodiment of following introduction, according to Satellite Engine mounting arrangement figure, under normal stable state flywheel master mode, the thruster nozzle that can apply the track tangential direction has a lot of, symmetry from jet moment, and attitude is produced the disturbance torque minimum angles set out, select the nozzle of one group of optimum.
1. if use nominal thrust 5N, along track tangential direction effect 1 second, as follows to the influence that orbit altitude produces:
--whole star quality.
Draw 1 second jet to orbit altitude exert an influence into
Rice.
2. if this group nozzle produces disturbance torque to the satellite yaw axis, then as follows to the satellite attitude influence:
Verify and require index when whether the satellite degree of stability satisfies the rail control.Select the thruster can continuous working period according to index, calculate the flywheel handle then
Cireular frequency control to 0 and need the time to be
3. if track need be raised 300 meters, then need jet time to be
, each jet output pulse is if 1 second, and then needing jet quantity is 42 times, and adjusting complete plan orbit altitude needs the time to be
Second.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.After those skilled in the art have read foregoing, for multiple modification of the present invention with to substitute all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (3)
1. a method of readjusting by a small margin orbit altitude uses thruster point spray mode to realize the satellite orbital altitude fine tune be is characterized in that, may further comprise the steps:
1) determining can be along the thruster nozzle of track tangential direction applied thrust;
2) constraint that flywheel stable state state of a control need be exported jet situation to thruster is kept in calculating;
3) orbit altitude of adjusting according to plan is calculated the quantity of thruster fixed pulse width.
2. readjust by a small margin the method for orbit altitude according to claim 1, it is characterized in that:
Described step 1)-2) in, pulse width and the time gap between the pulse width that thruster is exported have certain constraint, to guarantee attitude and the degree of stability index request of the control of stable state flywheel.
3. as the method for fine tune orbit altitude as described in the claim 2, it is characterized in that, comprising:
Selection can guarantee the symmetry of jet moment and attitude is produced one group of nozzle of disturbance torque minimum, calculate use described nozzle nominal thrust in setting-up time to the variation delta of orbit altitude
a
Calculate the disturbance torque that described nozzle produces the satellite yaw axis, be thrust at the increment of setting-up time inner opposite angle momentum and to the influence of Satellite Angle speed, and when can satisfying the rail control, the verifying satellites degree of stability requires under the prerequisite of index, determine the sustainable work-hours of thruster, and the calculating flywheel controls to 0 needed time Δ with cireular frequency
T
The numerical value of raising according to the track needs is divided by variation delta
aAfter the result obtain needing the jet time
t, again according to the time
tRound divided by the postimpulse result of each jet output and to obtain needing jet number of times
n, obtain finishing the time that the orbit altitude adjustment needs with this
T=
n* Δ
T
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310266377.7A CN103303496B (en) | 2013-06-28 | 2013-06-28 | A kind of method readjusting by a small margin orbit altitude |
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| CN201310266377.7A CN103303496B (en) | 2013-06-28 | 2013-06-28 | A kind of method readjusting by a small margin orbit altitude |
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| CN103303496A true CN103303496A (en) | 2013-09-18 |
| CN103303496B CN103303496B (en) | 2015-09-09 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542119A (en) * | 2016-10-14 | 2017-03-29 | 上海微小卫星工程中心 | On star, autonomous Orbit maintains control method |
| CN109739262A (en) * | 2019-01-25 | 2019-05-10 | 上海微小卫星工程中心 | A fast and autonomous transfer orbit control method |
| CN110429974A (en) * | 2019-08-07 | 2019-11-08 | 清华大学 | Rapid alignment method and device based on regression orbit constellation |
| CN110471431A (en) * | 2019-07-30 | 2019-11-19 | 北京天问空间科技有限公司 | A kind of method of earth observation systems spatial resolution control |
| CN112417589A (en) * | 2020-11-05 | 2021-02-26 | 航天东方红卫星有限公司 | A Calculation Method of Satellite Steady-State Availability |
| CN112607065A (en) * | 2020-12-23 | 2021-04-06 | 长春工业大学 | High-precision phase control method based on electric propulsion system |
| CN115743620A (en) * | 2022-12-19 | 2023-03-07 | 上海航天控制技术研究所 | High-dynamic attitude tracking control method for spacecraft angular momentum bias |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0347585A1 (en) * | 1988-05-26 | 1989-12-27 | Space Systems / Loral, Inc. | Transition control system for spacecraft attitude control |
| US4961551A (en) * | 1988-11-18 | 1990-10-09 | Hughes Aircraft Company | Stabilization of a spinning spacecraft of arbitary shape |
| EP1072508A2 (en) * | 1999-07-29 | 2001-01-31 | Space Systems / Loral, Inc. | An adaptive mass expulsion attitude control system |
| US6340138B1 (en) * | 2000-05-08 | 2002-01-22 | Hughes Electronics Corporation | Stationkeeping method utilizing open-loop thruster pulses and closed-loop authority limited momentum storage devices |
| CN102424116A (en) * | 2011-12-08 | 2012-04-25 | 中国空间技术研究院 | Orbital transfer strategy optimization method for geostationary orbit satellite |
| CN103072703A (en) * | 2013-01-30 | 2013-05-01 | 北京控制工程研究所 | Precession control method for under-actuated satellite |
| CN103072702A (en) * | 2013-01-30 | 2013-05-01 | 北京控制工程研究所 | Control method for orbit and attitude of satellite |
-
2013
- 2013-06-28 CN CN201310266377.7A patent/CN103303496B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0347585A1 (en) * | 1988-05-26 | 1989-12-27 | Space Systems / Loral, Inc. | Transition control system for spacecraft attitude control |
| US4961551A (en) * | 1988-11-18 | 1990-10-09 | Hughes Aircraft Company | Stabilization of a spinning spacecraft of arbitary shape |
| EP1072508A2 (en) * | 1999-07-29 | 2001-01-31 | Space Systems / Loral, Inc. | An adaptive mass expulsion attitude control system |
| US6340138B1 (en) * | 2000-05-08 | 2002-01-22 | Hughes Electronics Corporation | Stationkeeping method utilizing open-loop thruster pulses and closed-loop authority limited momentum storage devices |
| CN102424116A (en) * | 2011-12-08 | 2012-04-25 | 中国空间技术研究院 | Orbital transfer strategy optimization method for geostationary orbit satellite |
| CN103072703A (en) * | 2013-01-30 | 2013-05-01 | 北京控制工程研究所 | Precession control method for under-actuated satellite |
| CN103072702A (en) * | 2013-01-30 | 2013-05-01 | 北京控制工程研究所 | Control method for orbit and attitude of satellite |
Non-Patent Citations (1)
| Title |
|---|
| 常建松等: "静止轨道卫星连续式等间隔脉冲推力东西位置保持策略", 《空间控制技术与应用》 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542119A (en) * | 2016-10-14 | 2017-03-29 | 上海微小卫星工程中心 | On star, autonomous Orbit maintains control method |
| CN106542119B (en) * | 2016-10-14 | 2020-05-15 | 上海微小卫星工程中心 | On-satellite autonomous orbit maintenance control method |
| CN109739262A (en) * | 2019-01-25 | 2019-05-10 | 上海微小卫星工程中心 | A fast and autonomous transfer orbit control method |
| CN109739262B (en) * | 2019-01-25 | 2022-04-19 | 上海微小卫星工程中心 | Control method for fast autonomous transfer of track |
| CN110471431A (en) * | 2019-07-30 | 2019-11-19 | 北京天问空间科技有限公司 | A kind of method of earth observation systems spatial resolution control |
| CN110429974A (en) * | 2019-08-07 | 2019-11-08 | 清华大学 | Rapid alignment method and device based on regression orbit constellation |
| CN110429974B (en) * | 2019-08-07 | 2020-05-12 | 清华大学 | Fast Alignment Method and Device Based on Regression Orbit Constellation |
| CN112417589A (en) * | 2020-11-05 | 2021-02-26 | 航天东方红卫星有限公司 | A Calculation Method of Satellite Steady-State Availability |
| CN112417589B (en) * | 2020-11-05 | 2023-11-10 | 航天东方红卫星有限公司 | Satellite steady-state availability computing method |
| CN112607065A (en) * | 2020-12-23 | 2021-04-06 | 长春工业大学 | High-precision phase control method based on electric propulsion system |
| CN115743620A (en) * | 2022-12-19 | 2023-03-07 | 上海航天控制技术研究所 | High-dynamic attitude tracking control method for spacecraft angular momentum bias |
| CN115743620B (en) * | 2022-12-19 | 2024-09-06 | 上海航天控制技术研究所 | High-dynamic attitude tracking control method for angular momentum bias of spacecraft |
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| CN103303496B (en) | 2015-09-09 |
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Effective date of registration: 20170621 Address after: 200233 Xuhui District, Yishan Road, No. 710, Patentee after: SHANGHAI AEROSPACE CONTROL TECHNOLOGY RESEARCH INSTITUTE Address before: 200233 Xuhui District, Yishan Road, No. 710, Patentee before: Shanghai Xinyue Instrument Factory |
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