CN106843248A - Unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit - Google Patents
Unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit Download PDFInfo
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- CN106843248A CN106843248A CN201710059935.0A CN201710059935A CN106843248A CN 106843248 A CN106843248 A CN 106843248A CN 201710059935 A CN201710059935 A CN 201710059935A CN 106843248 A CN106843248 A CN 106843248A
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- 238000009434 installation Methods 0.000 title claims abstract description 60
- 238000002715 modification method Methods 0.000 title claims abstract description 10
- 238000012360 testing method Methods 0.000 claims abstract description 10
- 238000002347 injection Methods 0.000 claims abstract description 9
- 239000007924 injection Substances 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 claims abstract description 6
- 238000000205 computational method Methods 0.000 abstract description 2
- 230000005484 gravity Effects 0.000 description 6
- 238000003384 imaging method Methods 0.000 description 5
- 238000005259 measurement Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000036244 malformation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Length Measuring Devices By Optical Means (AREA)
- Control And Safety Of Cranes (AREA)
Abstract
Unit installation deviation is estimated and modification method after entering the orbit the invention discloses a kind of satellite launch, comprising procedure below：By measuring the angular relationship of unit reference mirror and satellite primary standard mirror, satellite is obtained in Light Condition, the first installation deviation Δ θ of unit1；Satellite in full load condition, the second installation deviation Δ θ of unit2；Satellite check and accept level vibration test before, and satellite in a fully loaded state when, the 3rd installation deviation Δ θ of unit3；Satellite check and accept level vibration test after, and satellite in a fully loaded state when, the 4th installation deviation Δ θ of unit4；And before satellite launch, satellite in a fully loaded state when, the 5th installation deviation Δ θ of unit5；The first to the 5th installation deviation Δ θ according to unit1~Δ θ5Estimate the 6th installation deviation Δ θ of the unit after satellier injection6；The 6th installation deviation Δ θ according to unit6, calculate the unit orientation angle value θ ' after amendment satellite launch is entered the orbit.The present invention has computational methods simple, controls flexible advantage.
Description
Technical field
The present invention relates to satellite gravity anomaly field, unit installation deviation is estimated after more particularly to a kind of satellite launch is entered the orbit
And modification method.
Background technology
In order to meet the imaging demand of high-resolution satellite, it is necessary to realize sensing and the attitude control of satellite of satellite imaging devices
The sensing of unit processed is accurately corresponded to.General, satellite can set a primary standard mirror, and imaging device and gesture stability unit are set
Reference mirror, measurement imaging device and gesture stability unit set the deviation of reference mirror and primary standard mirror, (are padded as increased by adjustment
Piece, polishing mounting surface etc.) angular relationship control installation deviation each other.But in satellite development process, due to gravity
Influence, the influence of mechanical structured member timeliness, the influence of vibration environment, the influence of transportation environment and influence of launch environment etc., into
As the deviation that equipment and gesture stability unit set reference mirror and primary standard mirror can all change, it is difficult to accurate to obtain satellite hair
Inject the installation deviation of unit after rail, the attitude pointing accuracy of satellite is difficult to meet and requires, in addition influence satellite imaging requirements.
The content of the invention
Unit installation deviation is estimated and modification method after entering the orbit it is an object of the present invention to provide a kind of satellite launch, by defending
The measurement of unit installation deviation under star different conditions, considers gravity, mechanical structured member timeliness, vibration, transport and transmitting ring
The influence in border, estimate satellier injection after unit installation deviation and be modified, realize ensure the attitude of satellite point to meet require
Purpose.
In order to realize the above object the present invention is achieved through the following technical solutions：
Unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit, comprising procedure below：
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, obtains unit in Light Condition
The first installation deviation Δ θ1；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, obtains unit in full load condition
The second installation deviation Δ θ2；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, is obtained before level vibration test is checked and accepted
To the 3rd installation deviation Δ θ of satellite unit in a fully loaded state3；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, is obtained after level vibration test is checked and accepted
To the 4th installation deviation Δ θ of satellite unit in a fully loaded state4；
Before satellite launch, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, satellite is obtained fully loaded
5th installation deviation Δ θ of the unit under state5；
The first to the 5th installation deviation Δ θ according to unit1~Δ θ5Estimate that the 6th installation of the unit after satellier injection is inclined
Difference Δ θ6；6th installation deviation Δ θ of the unit6Computing formula be：
Δθ6=Δ θ1+(Δθ5-Δθ2)+(Δθ4-Δθ3)
The 6th installation deviation Δ θ according to unit6, calculate the unit orientation angle value θ ' after amendment satellite launch is entered the orbit.
Preferably, if unit orientation angle measured value is θ after satellite launch is entered the orbit, to software remote control injection Δ θ on star6,
By correcting the 6th installation deviation Δ θ6The accurate orientation angle value θ ' of unit is obtained, i.e.,
θ '=θ-Δ θ6。
The present invention has advantages below compared with prior art：
The present invention considers gravity, mechanical structured member by the measurement to unit installation deviation under satellite different conditions
The influence of timeliness, vibration, transport and launch environment, estimate satellier injection after unit installation deviation and be modified, it is ensured that defend
Star attitude is pointed to meet and required.The present invention has computational methods simple, and control is flexible, can be applied to attitude pointing accuracy requirement
It is high, it is necessary to it is accurate obtain launching enter the orbit after advantage in unit installation deviation and the satellite development process that is modified.
Brief description of the drawings
Fig. 1 is the flow chart that unit installation deviation estimates with modification method after a kind of satellite launch of the invention is entered the orbit.
Specific embodiment
Below in conjunction with accompanying drawing, by describing a preferably specific embodiment in detail, the present invention is further elaborated.
Estimate satellier injection by considering gravity, mechanical structured member timeliness, vibration, transport and the influence of launch environment
The installation deviation of unit and it is modified afterwards, it is ensured that the attitude of satellite is pointed to meet and required.
As shown in figure 1, unit installation deviation is estimated and modification method after a kind of satellite launch of the invention is entered the orbit, comprising following
Process：
Unit dress star, other units and the part for the assembling for the first time of satellite main structure is terminated, being required to installation deviation are not
Fill the Light Condition that starlike state is defined as satellite.Satellite in the unloaded state, is wanted due to there was only main structure and having to installation deviation
The unit asked, does not have other units and part, and gravity influences minimum to malformation, therefore, satellite is under the Light Condition
The state being not influenced by gravitation after entering the orbit with satellite launch is closest.Under satellite Light Condition, by measuring unit reference mirror
With the angular relationship of satellite primary standard mirror, the first installation deviation Δ θ of unit is obtained1。
Satellite (including all units and part) assembling for the first time is terminated to be defined as the full load condition of satellite.In this shape
Under state, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, the second installation deviation Δ θ of unit is obtained2。
Before satellite (including all units and part) checks and accepts level vibration test, by measuring satellite list in a fully loaded state
Machine reference mirror and the angular relationship of satellite primary standard mirror, obtain the 3rd installation deviation Δ θ of unit3。
After satellite (including all units and part) checks and accepts level vibration test, by measuring satellite list in a fully loaded state
Machine reference mirror and the angular relationship of satellite primary standard mirror, obtain the 4th installation deviation Δ θ of unit4。
Before satellite (including all units and part) transmitting, and satellite is in a fully loaded state, by measuring unit reference mirror
With the angular relationship of satellite primary standard mirror, the 5th installation deviation Δ θ of unit is obtained5。
The first to the 5th installation deviation Δ θ according to the unit1~Δ θ5It is inclined to estimate the 6th installation after satellier injection
Difference Δ θ6。
The vibration level that carrier rocket brings during due to satellite launch is suitable with satellite examination level vibration test magnitude, so
The the 3rd and the 4th installation deviation data variation value Δ θ that vibration test fore-and-aft survey is obtained4-Δθ3With influenceed by launch environment
Installation deviation data variation value is suitable.
Satellite mechanical structured member timeliness, transportation environment influence can be by Δ θ5-Δθ2Obtain.The transportation environment refers to
General satellite can all experience the transportation environment from satellite factory building to launching site long period relatively long distance；Estimated according to formula 1
Satellite launch enter the orbit after unit the 6th installation deviation Δ θ6,
Δθ6=Δ θ1+(Δθ5-Δθ2)+(Δθ4-Δθ3) (1)
If unit orientation angle measured value is θ after satellite launch is entered the orbit, the of the unit is injected to software remote control on star
Six installation deviation Δ θ6, the 6th installation deviation Δ θ is corrected by formula 26The accurate orientation angle value θ ' of unit is obtained, so
Cause that attitude pointing accuracy meets index request by attitude closed-loop control afterwards.
θ '=θ-Δ θ6 (2)
Although present disclosure is discussed in detail by above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read the above, for of the invention
Various modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (2)
1. unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit, it is characterised in that comprising procedure below：
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, obtains the of unit in Light Condition
One installation deviation Δ θ1；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, obtains the of unit in full load condition
Two installation deviation Δ θ2；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, is defended before level vibration test is checked and accepted
3rd installation deviation Δ θ of star unit in a fully loaded state3；
Satellite, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, is defended after level vibration test is checked and accepted
4th installation deviation Δ θ of star unit in a fully loaded state4；
Before satellite launch, by measuring the angular relationship of unit reference mirror and satellite primary standard mirror, satellite is obtained in full load condition
Under unit the 5th installation deviation Δ θ5；
The first to the 5th installation deviation Δ θ according to unit1~Δ θ5Estimate the 6th installation deviation Δ of the unit after satellier injection
θ6；6th installation deviation Δ θ of the unit6Computing formula be：
Δθ6=Δ θ1+(Δθ5-Δθ2)+(Δθ4-Δθ3)
The 6th installation deviation Δ θ according to unit6, calculate the unit orientation angle value θ ' after amendment satellite launch is entered the orbit.
2. unit installation deviation is estimated and modification method after a kind of satellite launch is entered the orbit as claimed in claim 1, it is characterised in that
If unit orientation angle measured value is θ after satellite launch is entered the orbit, to software remote control injection Δ θ on star6, by correcting the described 6th
Installation deviation Δ θ6The accurate orientation angle value θ ' of unit is obtained, i.e.,
θ '=θ-Δ θ6。
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| CN201710059935.0A CN106843248B (en) | 2017-01-24 | 2017-01-24 | The estimation of single machine installation deviation and modification method after a kind of satellite launch is entered the orbit |
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| CN201710059935.0A CN106843248B (en) | 2017-01-24 | 2017-01-24 | The estimation of single machine installation deviation and modification method after a kind of satellite launch is entered the orbit |
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