CN104375511A - Geosynchronous orbit SAR satellite off-course guide method based on wave beam cooperative control - Google Patents
Geosynchronous orbit SAR satellite off-course guide method based on wave beam cooperative control Download PDFInfo
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- CN104375511A CN104375511A CN201410588779.3A CN201410588779A CN104375511A CN 104375511 A CN104375511 A CN 104375511A CN 201410588779 A CN201410588779 A CN 201410588779A CN 104375511 A CN104375511 A CN 104375511A
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Abstract
The invention provides a geosynchronous orbit SAR satellite off-course guide method based on wave beam cooperative control. The geosynchronous orbit SAR satellite off-course guide method includes the following steps that 1, an orbit of a geosynchronous orbit SAR satellite is designed according to the system task requirements; 2, a strategy suitable for system off-course guide is selected according to scanning capacity, posture control capacity, posture sensor installation and layout of system antennas and the following strategy analysis; 3, a joint control rule is designed according to all the off-course guide strategies, and posture beam cooperative guide is conducted. According to the geosynchronous orbit SAR satellite off-course guide method, the observation position can be changed flexibly within small-range adjustment of wave beams, the requirement of the system for the off-course control angle is lowered, and normal work of the effective load on the satellite is guaranteed.
Description
Technical field
The present invention relates to a kind of guidance method, particularly, relate to a kind of geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control.
Background technology
Due to the impact of earth rotation, satellite-borne SAR (Synthetic Aperture Radar, synthetic-aperture radar) doppler centroid departs from zero-frequency, even may much larger than imaging processor bandwidth, cause doppler centroid about the fuzzy problem of pulse repetition rate, the shorter fuzzy problem of wavelength is more serious, and larger doppler centroid can cause larger range migration amount simultaneously, and this brings difficulty to imaging processing.Particularly for geostationary orbit SAR satellite, the impact of earth rotation speed is more remarkable.Major part SAR imaging algorithm realizes based on to a certain degree approximate, if do not carried out gesture stability, along with the raising of resolution and the increase of imaging mapping band, thisly approximately may become insufficient, thus be constrained to the precision of picture.In addition, when not adopting gesture stability, for the region (as region of the equator) that equivalent squint angle changes greatly, from low coverage to long distance end, the variation range of doppler centroid can reach thousand hertz, may cause signal noise ratio (snr) of image loss, orientation misconvergence Jiao and azimuth ambiguity.In order to compensating for doppler parameter is with the change of distance, usually take distance to the mode of staging treating, but because the unpressed distance signal at different oblique distance place is overlapping at range-Dopler domain, this processing mode effect is not bery perfect, and gesture stability can effectively reduce the variable quantity of this doppler centroid with oblique distance, reduce range migration amount, be convenient to imaging processing.
Adopt attitude guiding can realize zero doppler centroid, but when namely convenient orbit inclination is 70 °, maximum yaw angle is also close to 60 °, and this controls to propose higher requirement for platform stance.On the other hand, the orbit altitude of geostationary orbit SAR satellite is very large, can change observation position flexibly by the adjustment among a small circle of wave beam.Therefore, can consider to adopt the mode of wave beam Collaborative Control to realize Yaw steering, reduce the requirement of system to driftage pilot angle.
Do not find explanation or the report of technology similar to the present invention at present, not yet collect similar data both at home and abroad yet.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control, it changes observation position flexibly by the adjustment among a small circle of wave beam, reduction system, to the requirement of driftage pilot angle, ensures the normal work of useful load on star.
According to an aspect of the present invention, a kind of geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control is provided, it is characterized in that, comprise the following steps: step one, according to the track of system task Demand Design geostationary orbit SAR satellite; Step 2, according to scan capability, gesture stability ability, the attitude sensor mounting arrangement of system antenna, according to analysis of strategies, chooses the strategy being wherein applicable to system Yaw steering; Step 3, the Strategy Design according to above-mentioned each Yaw steering jointly controls rule, carries out the collaborative guiding of attitude wave beam.
Preferably, described track mainly comprises orbit altitude, orbit inclination and work visual angle.
Preferably, the collaborative guiding of described step 3 attitude wave beam adopts attitude wave beam Collaborative Control, utilizes the adjustment among a small circle of wave beam to change observation position flexibly, reduces geostationary orbit SAR satellite system like this to the requirement of driftage pilot angle.
Preferably, the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control uses beam scanning to realize zero doppler centroid, does not namely carry out pose adjustment, obtains the azimuth beam angle under different visual angles and distance field angle.
Preferably, it is 20 ° that the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control gets maximum yaw limit angles, then the maximum position angle of wave beam is less than 6 °, and ultimate range angle is less than 2.5 °, reduces the difficulty that driftage controls.
Preferably, the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control adopts complete wave beam control strategy or maximum yaw pilot angle to be the strategy of 20 ° or the federation policies of consideration beam scanning capabilities.
Compared with prior art, the present invention has following beneficial effect: the present invention limits maximum yaw angle, the design maximum position angle of beam scanning and ultimate range angle; Because beam scanning capabilities is limited, so design associating control law in conjunction with beam scanning capabilities, reduce the requirement to antenna scan angle on the one hand, also reduce the difficulty that driftage controls simultaneously.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the schematic diagram that geostationary orbit SAR satellite jointly controls.
Fig. 2 is the schematic diagram of aiming point relation under antenna coordinate system.
When Fig. 3 is not for adopting crab angle, orientation is to wave beam pilot angle (θ
y max=0 °) schematic diagram.
When Fig. 4 is not for adopting crab angle, distance is to wave beam pilot angle (θ
y max=0 °) schematic diagram.
When Fig. 5 is not for adopting crab angle, orientation is to wave beam pilot angle (θ
y max=20 °) schematic diagram.
When Fig. 6 is not for adopting crab angle, distance is to wave beam pilot angle (θ
y max=20 °) schematic diagram.
Fig. 7 is the schematic diagram of driftage pilot angle.
Fig. 8 is the schematic diagram of maximum field angle.
Fig. 9 (a) is the schematic diagram jointly controlling the driftage pilot angle of rule when maximum scan angle is 3 °.
Fig. 9 (b) is the schematic diagram jointly controlling the beam scanning angle of rule when maximum scan angle is 3 °.
Figure 10 (a) is the schematic diagram jointly controlling the driftage pilot angle of rule when maximum scan angle is 2 °.
Figure 10 (b) is the schematic diagram jointly controlling the beam scanning angle of rule when maximum scan angle is 2 °.
Figure 11 (a) is the schematic diagram jointly controlling the driftage pilot angle of rule when maximum scan angle is 1 °.
Figure 11 (b) is the schematic diagram jointly controlling the beam scanning angle of rule when maximum scan angle is 1 °.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
The geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control of the present invention comprises the following steps:
Step one, according to the track of system task Demand Design geostationary orbit SAR satellite, track mainly comprises orbit altitude, orbit inclination and work visual angle;
Step 2, according to the constraint condition such as scan capability, gesture stability ability, attitude sensor mounting arrangement of system antenna, according to analysis of strategies, chooses the strategy being wherein applicable to system Yaw steering;
Step 3, the Strategy Design according to above-mentioned each Yaw steering jointly controls rule, carries out the collaborative guiding of attitude wave beam.
As shown in Figure 1, S is satellite position to the space geometry relation that wave beam controls, θ
ybe Raney driftage pilot angle, P is the wave beam aiming point of going off course completely when controlling, θ
y' be the driftage pilot angle limited, Q is the wave beam aiming point under restriction crab angle.
Under the antenna coordinate system limiting driftage pilot angle, as shown in Figure 2, APC is antenna phase center to the relativeness of wave beam aiming point P when driftage controls completely and the wave beam aiming point Q under limiting crab angle.
When driftage controls completely, the doppler centroid of wave beam aiming point P when driftage controls completely is 0.When after restriction crab angle, there is deviation in the wave beam aiming point Q under restriction crab angle and completely the wave beam aiming point P gone off course when controlling, needs, by the mode of beam scanning, beam center sensing is adjusted to " APC-P " to realize zero doppler centroid from " APC-Q ".If the coordinate of wave beam aiming point P when driftage controls completely in the antenna coordinate system pointing to the wave beam aiming point Q under restriction crab angle is (P
x, P
y, P
z), beam scanning angle is following formula (1):
Wherein, θ
aazimuth scan angle, θ
rit is range sweep angle.
Attitude-wave beam jointly controls strategy can be divided into following three kinds of strategies:
Strategy one, completely wave beam control strategy, if only use beam scanning to realize zero doppler centroid, namely do not carry out pose adjustment, then the azimuth beam angle under different visual angles and distance field angle are as shown in Figure 3 and Figure 4.Maximum position angle needed for complete wave beam control realization zero doppler centroid is less than 8 °, and ultimate range angle is less than 4.5 °.
Strategy two, maximum yaw pilot angle are the strategy of 20 °, if get maximum yaw limit angles θ
y maxbe 20 °, then emulation obtains azimuth beam angle under different visual angles and distance field angle as shown in Figure 5, Figure 6.Under the prerequisite limiting crab angle 20 °, the maximum position angle of wave beam is less than 6 °, and ultimate range angle is less than 2.5 °, reduces the difficulty that driftage controls, and simultaneously corresponding driftage control law as shown in Figure 7.
The federation policies of strategy three, consideration beam scanning capabilities, geostationary orbit SAR satellite antenna beam scanning capabilities is limited, needs to design associating control strategy in conjunction with beam scanning capabilities.Selected antenna look angle 4 °, then maximum field angle with driftage pilot angle Changing Pattern as shown in Figure 8.
Beam scanning capabilities in system index is ± 3 °, and namely maximum beam scanning angle is no more than 3 °.Position angle is greater than distance angle, therefore the restriction at only demand fulfillment azimuth beam angle.Driftage pilot angle corresponding to 3 ° of azimuth scan angles is 15 °; Driftage pilot angle corresponding to 2 ° of azimuth scan angles is 33.5 °; Driftage pilot angle corresponding to 1 ° of azimuth scan angle is 49 °." attitude-wave beam " jointly controls rule respectively as shown in Fig. 9 (a), 9 (b), 10 (a), 10 (b), 11 (a), 11 (b) accordingly.
Be the geostationary orbit of 53 ° at inclination angle for satellite operation, in the orbital period, crab angle is changed to-63.5 ° ~ 63.5 °.As can be seen here, geostationary orbit SAR satellite Yaw steering angle variation range is comparatively large, and satellite needs the instruction angle of guiding to be also far longer than previous similar model satellite at yaw direction, and this controls to propose higher requirement for platform stance.The present invention can change observation position flexibly by the adjustment among a small circle of wave beam, reduces the requirement of system to driftage pilot angle.The present invention carries out Yaw steering, to ensure the normal work of useful load on star.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (6)
1. a geostationary orbit SAR satellite Yaw steering method for wave beam Collaborative Control, is characterized in that, the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control comprises the following steps:
Step one, according to the track of system task Demand Design geostationary orbit SAR satellite;
Step 2, according to scan capability, gesture stability ability, the attitude sensor mounting arrangement of system antenna, according to analysis of strategies below, chooses the strategy being wherein applicable to system Yaw steering;
Step 3, the Strategy Design according to above-mentioned each Yaw steering jointly controls rule, carries out the collaborative guiding of attitude wave beam.
2. the geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control according to claim 1, it is characterized in that, described track mainly comprises orbit altitude, orbit inclination and work visual angle.
3. the geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control according to claim 1, it is characterized in that, the collaborative guiding of described step 3 attitude wave beam adopts attitude wave beam Collaborative Control, utilizes the adjustment among a small circle of wave beam to change observation position flexibly.
4. the geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control according to claim 1, it is characterized in that, the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control uses beam scanning to realize zero doppler centroid.
5. the geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control according to claim 1, it is characterized in that, it is 20 ° that the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control gets maximum yaw limit angles, then the maximum position angle of wave beam is less than 6 °, and ultimate range angle is less than 2.5 °.
6. the geostationary orbit SAR satellite Yaw steering method of wave beam Collaborative Control according to claim 1, it is characterized in that, the geostationary orbit SAR satellite Yaw steering method of described wave beam Collaborative Control adopts complete wave beam control strategy or maximum yaw pilot angle to be the strategy of 20 ° or the federation policies of consideration beam scanning capabilities.
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| CN104657795A (en) * | 2015-03-16 | 2015-05-27 | 中国人民解放军空军装备研究院雷达与电子对抗研究所 | To-be-observed task determination method and device of multi-satellite earth synergetic observation |
| CN106646473A (en) * | 2017-01-25 | 2017-05-10 | 上海卫星工程研究所 | Geosynchronous orbit SAR satellite burst imaging work method |
| CN108710379A (en) * | 2018-06-14 | 2018-10-26 | 上海卫星工程研究所 | Fixed statellite is imaged Yaw steering angle computational methods |
| CN108958272A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | Yaw steering method is imaged in fixed statellite |
| CN111948650A (en) * | 2020-06-29 | 2020-11-17 | 北京理工大学 | Satellite-borne bistatic SAR (synthetic Aperture Radar) combined Doppler guidance method based on electric scanning |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104657795A (en) * | 2015-03-16 | 2015-05-27 | 中国人民解放军空军装备研究院雷达与电子对抗研究所 | To-be-observed task determination method and device of multi-satellite earth synergetic observation |
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| CN108710379A (en) * | 2018-06-14 | 2018-10-26 | 上海卫星工程研究所 | Fixed statellite is imaged Yaw steering angle computational methods |
| CN108710379B (en) * | 2018-06-14 | 2021-02-02 | 上海卫星工程研究所 | Method for calculating yaw guide angle in imaging of stationary satellite |
| CN108958272A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | Yaw steering method is imaged in fixed statellite |
| CN111948650A (en) * | 2020-06-29 | 2020-11-17 | 北京理工大学 | Satellite-borne bistatic SAR (synthetic Aperture Radar) combined Doppler guidance method based on electric scanning |
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Application publication date: 20150225 |