CN104058110A - Remote sensing satellite system - Google Patents
Remote sensing satellite system Download PDFInfo
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- CN104058110A CN104058110A CN201410245065.2A CN201410245065A CN104058110A CN 104058110 A CN104058110 A CN 104058110A CN 201410245065 A CN201410245065 A CN 201410245065A CN 104058110 A CN104058110 A CN 104058110A
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Abstract
The invention discloses a remote sensing satellite system. The remote sensing satellite system comprises a satellite body, an optical remote sensor, a microwave remote sensor and a 6-DOF (Degree-of-Freedom) vibration isolation device, and is characterized in that the microwave remote sensor is mounted at the lower end or the upper end of the satellite body, or extends out of the satellite body via a stretching structure; the 6-DOF vibration isolation device is used for adjusting the orientation of the optical remote sensor; the optical remote sensor of a satellite is connected with the satellite body via the 6-DOF vibration isolation device; the satellite body acquires data via the optical remote sensor and the microwave remote sensor. According to the remote sensing satellite system, disclosed by the embodiment of the invention, the data acquisition range and vibration disturbance resistant performance are boosted owing to the 6-DOF vibration isolation device, and the overall performance of the satellite is improved via the matched microwave remote sensor.
Description
Technical field
The present invention relates to field of aerospace technology, particularly a kind of remote sensing satellite system.
Background technology
Existing remote sensing satellite is divided into optical remote sensing and the large class of microwave remote sensing satellite two according to carried remote sensing load.All there is different defects in existing optical remote sensing and microwave remote sensing satellite, such as the work of Optical remote satellite, be not only subject to the impact of the many factors such as surface Weather, illumination, cloud layer, and be easily subject to " deception " of mulching material, although infrared and high spectrum camera possesses certain counter camouflage ability and the imaging capability under low-light (level), can not meet the requirement of round-the-clock, full-time, fine resolution, anti-camouflage.On the other hand, there is data inversion difficulty in the microwave remote sensing satellite that the synthetic aperture radar of take is representative, often occurs the problem of false target and the true target of loss, and easily by the reflective decoy of surface em, cheated.In addition, existing remote sensing satellite is easily received the impact of vibration on image data process.
Summary of the invention
Object of the present invention is intended at least solve one of above-mentioned technological deficiency.
For this reason, the invention provides a kind of remote sensing satellite system, this remote sensing satellite system can solve anti-interference shake poor performance and the not high problem of satellite overall performance.
In view of this, embodiments of the invention propose a kind of remote sensing satellite system, comprise: satellite main body, optical remote sensing device, microwave remote sensing device and six degree of freedom isolation mounting, it is characterized in that, described microwave remote sensing device is arranged on lower end, the upper end of described satellite main body or by stretched out structure, stretches out external; Described six degree of freedom isolation mounting, for adjusting the orientation of described optical remote sensing device; And described satellite optical remote sensing device is connected with described satellite main body by described six degree of freedom isolation mounting, described satellite main body is by described optical remote sensing device and described microwave remote sensing device image data.
According to the remote sensing satellite system of the embodiment of the present invention, by six degree of freedom isolation mounting, increased data acquisition scope and the anti-interference performance of shaking, and coordinated microwave remote sensing device to improve the overall performance of satellite.
In one embodiment of the invention, also comprise: extending arm, is connected described microwave remote sensing device by described extending arm with described satellite main body.
In one embodiment of the invention, described optical remote sensing device is arranged on side or the lower end of described satellite main body by described six degree of freedom isolation mounting.
In one embodiment of the invention, described six degree of freedom isolation mounting comprises at least three support components, and described satellite main body is controlled the orientation of described optical remote sensing device by described at least three support components.
In one embodiment of the invention, described support component is vibration isolator.
In one embodiment of the invention, described vibration isolator comprises voice coil motor, and described satellite main body changes the length of described vibration isolator by controlling described voice coil motor.
In one embodiment of the invention, described microwave remote sensing device is synthetic aperture radar.
In one embodiment of the invention, described synthetic aperture radar is flat or parabola formula.
In one embodiment of the invention, described optical remote sensing device is high-resolution optical camera.
In one embodiment of the invention, the installation site of described microwave remote sensing device and described optical remote sensing device does not interfere with each other.
The aspect that the present invention is additional and advantage in the following description part provide, and part will become obviously from the following description, or recognize by practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage will become from the following description of the accompanying drawings of embodiments and obviously and easily understand, wherein:
Fig. 1 is the structured flowchart of remote sensing satellite system according to an embodiment of the invention;
Fig. 2 is the structural representation of support component according to an embodiment of the invention;
Fig. 3 is for adopting according to an embodiment of the invention the structural representation of the remote sensing satellite system of flat SAR antenna; And
Fig. 4 is for adopting according to an embodiment of the invention the structural representation of the remote sensing satellite system of parabola SAR antenna.
The specific embodiment
Describe embodiments of the invention below in detail, the example of embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has the element of identical or similar functions from start to finish.Below by the embodiment being described with reference to the drawings, be exemplary, only for explaining the present invention, and can not be interpreted as limitation of the present invention.
In description of the invention, it will be appreciated that, term " " center ", " longitudinally ", " laterally ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of indications such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, rather than device or the element of indication or hint indication must have specific orientation, with specific orientation structure and operation, therefore can not be interpreted as limitation of the present invention.In addition, term " first ", " second " be only for describing object, and can not be interpreted as indication or hint relative importance.
In description of the invention, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and for example, can be to be fixedly connected with, and can be also to removably connect, or connect integratedly; Can be mechanical connection, can be to be also electrically connected to; Can be to be directly connected, also can indirectly be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, can particular case understand above-mentioned term concrete meaning in the present invention.
Fig. 1 is the structured flowchart of remote sensing satellite system according to an embodiment of the invention.As shown in Figure 1, according to the remote sensing satellite system of the embodiment of the present invention, comprise: satellite main body 100, optical remote sensing device 200, microwave remote sensing device 300 and six degree of freedom isolation mounting 400.
Particularly, microwave remote sensing device 300 is arranged on lower end or the upper end of satellite main body 100.Six degree of freedom isolation mounting 400, for adjusting the orientation of optical remote sensing device 200.Satellite optical remote sensing device 200 is connected with satellite main body 100 by six degree of freedom isolation mounting 400, and satellite main body 100 is by optical remote sensing device 200 and microwave remote sensing device 300 image data.
According to the remote sensing satellite system of the embodiment of the present invention, by six degree of freedom isolation mounting, increased data acquisition scope and the anti-interference performance of shaking, and coordinated microwave remote sensing device to improve the overall performance of satellite.
Owing to being subject to the impact of the many factors such as differential rail, load sensing difference, access time difference, target maneuver, adopt the method for Optical remote satellite and microwave remote sensing satellite formation flying or sequence flight can have some problems, this comprises target observation angle difference, coverage goal area differentiation, observed object state difference etc.
That realizes optics and microwave integrated remote sensing satellite also comprises two other Major Difficulties.A difficult point is the difference of field range.The field range of high-resolution optical load will show and is less than microwave remote sensing, for realize specific region time observation, need to adjust the sight line of optics load points to, but the sight line that can not affect microwave remote sensing is simultaneously pointed to, the antenna area of considering microwave remote sensing load is large, conventionally fixing with the setting angle of satellite, this means that the attitude motion of optical remote sensing device can not affect the attitude of satellite.Another one difficult point be high-resolution optical remote sensing device to satellite disturb shake and attitude jitter extremely sensitive, therefore high to the stability requirement of satellite rocking bar system.
In one embodiment of the invention, six degree of freedom isolation mounting 400 is arranged between optical remote sensing device 200 and satellite main body 100, six degree of freedom isolation mounting 400 at least comprises 3 support components, to guarantee the stability of optical remote sensing device 200 and the globality of structure.This optics rocker actuator 200 can be arranged on by six degree of freedom isolation mounting 400 side or the lower end of satellite main body 100.Satellite main body 100 is controlled the orientation of optical remote sensing device 200 by least three support components.This makes parts can be vibration isolator, this vibration isolator comprises voice coil motor, satellite main body 100 changes the length of vibration isolator by controlling voice coil motor, and then length and the orientation of adjusting six degree of freedom isolation mounting 400 adjust optics rocker actuator 200 orientation to reach, do not interfere with each other the object that microwave remote sensing device 300 and optical remote sensing device 200 are controlled simultaneously.Optical remote sensing device 200 can be high-resolution optical camera.
In one embodiment of the invention, by extending arm, microwave remote sensing device 300 is connected with satellite main body 100.Microwave remote sensing device 300 can be for synthetic aperture radar but is not limited to this, and synthetic aperture radar can be flat or parabola formula.
In one embodiment of the invention, make parts and should arrange according to the form of Bipod, arrange in pairs, to form triangular support.For guaranteeing the installation stability of optical remote sensing device 200 and the globality of structure, when adopting Bipod arrangement form, support component should be no less than three pairs, six.Six degree of freedom isolation mounting 400 has attitude and adjusts function, can realize the attitude adjustment in the six-freedom degree attitude direction of optical remote sensing device 200.
Fig. 2 is the structural representation of support component according to an embodiment of the invention.As shown in Figure 2, support component comprises pair of flexible hinge 1, pair of support rods 2, voice coil motor 3, spring 4 and push rod 5.One end of spring 4 is voice coil motor 3 fixedly, and the other end is connected with spring 4 by push rod 5.Support component is connected with optical remote sensing device 200 with satellite by flexible hinge 1.Voice coil motor 3 is by changing the length of the length adjustment support component of spring 4.Spring 4 and voice coil motor 3 parallel connections, spring 4 provides installs rigidity and link, and voice coil motor 3 is controlled attitude, and the permanent magnetic iron in voice coil motor 3 and moving coil provide vibration isolator required damping simultaneously.The isolation frequency of optical remote sensing device 200 should be low as far as possible, gets satellite attitude and control device control the more than three times of bandwidth, can be between 1Hz-10Hz (six direction), and the damping ratio of six degree of freedom isolation mounting 400 can be in 0.05 left and right.
According to the remote sensing satellite system of the embodiment of the present invention, by a plurality of support components, improved the resistance to overturning of satellite, improved the acquisition performance of optics rocker actuator and microwave remote sensing device.
When in one embodiment of the invention, synthetic aperture radar is plate type antenna, be conventionally arranged on a side on 100 pairs of ground of satellite main body.For expanding a day linear content, plate aerial at least comprises three, and three antennas form a plane.Wherein an antenna is arranged in satellite main body 100, and other two are sub-packed in satellite main body 100 both sides, so that transmitter section is folding, launches after entering the orbit.For providing support parts to folding antenna, some satellites can adopt part truss structure, to reduce structural weight.For further reducing structural weight, can adopt thin portion dot matrix truss structure.The another kind of form of SAR antenna is parabolic antenna, is characterized in that antenna reaches the outside of satellite main body 100 by a long extending arm.
When synthetic aperture radar is flat SAR antenna, optical remote sensing device 200 is installed on the outside of satellite main body 100 by six degree of freedom isolation mounting 400, to avoid sight line to be blocked.For guaranteeing structural strength and the shock resistance of transmitter section, can apply supplemental support to optical remote sensing device 200, after entering the orbit, by tripper release, depart from auxiliary support apparatus.For reducing the external envelope size of transmitter section satellite, optical remote sensing device 200 can be taken in satellite main body 100 inside at transmitter section, releases the outside of satellite main body 100 after entering the orbit.At launching phase, parabolic antenna folds and is fixed on celestial body outside, after entering the orbit, launches.
Fig. 3 is for adopting according to an embodiment of the invention the structural representation of the remote sensing satellite system of flat SAR antenna.As shown in Figure 3, according to the remote sensing satellite system of the embodiment of the present invention, comprise: satellite main body 100, optical remote sensing device 200, flat SAR antenna 300, six degree of freedom isolation mounting 400 and a pair of sun wing 500.
As shown in Figure 3, optical remote sensing device 200 is arranged on the side of satellite main body 100, to avoid the visual field of flat SAR antenna (being microwave remote sensing device) 300 and optical remote sensing device 200 to produce phase mutual interference.Optical remote sensing device 200 is connected with satellite main body 100 by six degree of freedom isolation mounting 400, by adjusting the length of the support component of six degree of freedom isolation mounting 400, realizes adjustment and control to optical remote sensing device direction of visual lines.This six degree of freedom isolation mounting 400 comprises six support components, and six support components arrange with bipod form, and minimum isolation frequency is 1Hz.
Fig. 4 is for adopting according to an embodiment of the invention the structural representation of the remote sensing satellite system of parabola SAR antenna.As shown in Figure 4, according to the remote sensing satellite system of the embodiment of the present invention, comprise: satellite main body 100, optical remote sensing device 200, parabola formula SAR antenna 300, six degree of freedom isolation mounting 400, a pair of sun wing 500 and extending arm 600.
Particularly, optical remote sensing device 200 be installed on satellite agent structure 100 under, by six degree of freedom isolation mounting 400, be connected with satellite main body 100, by adjusting the length of the support component of six degree of freedom isolation mounting 400, realize the adjustment in direction of optical remote sensing device 200 and control.Six degree of freedom isolation mounting 400 adopts six support components, and according to bipod form, arranges its minimum isolation frequency 1Hz.Parabola formula SAR antenna 300 is connected with satellite main body 100 by extending arm 600, to be stretched over the outside of satellite main body 100, and then avoids affecting the visual field of optical remote sensing device 200.
According to the remote sensing satellite system of the embodiment of the present invention, by six degree of freedom isolation mounting, increased data acquisition scope and the anti-interference performance of shaking, and coordinated microwave remote sensing device to improve the overall performance of satellite.
Although illustrated and described embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, those of ordinary skill in the art can change above-described embodiment within the scope of the invention in the situation that not departing from principle of the present invention and aim, modification, replacement and modification.
Claims (10)
1. a remote sensing satellite system, is characterized in that, comprising: satellite main body, optical remote sensing device, microwave remote sensing device and six degree of freedom isolation mounting, it is characterized in that,
Described microwave remote sensing device is arranged on lower end or the upper end of described satellite main body;
Described six degree of freedom isolation mounting, for adjusting the orientation of described optical remote sensing device; And
Described satellite optical remote sensing device is connected with described satellite main body by described six degree of freedom isolation mounting, and described satellite main body is by described optical remote sensing device and described microwave remote sensing device image data.
2. remote sensing satellite system as claimed in claim 1, is characterized in that, also comprises:
Extending arm, is connected described microwave remote sensing device by described extending arm with described satellite main body.
3. remote sensing satellite system as claimed in claim 1, is characterized in that, described optical remote sensing device is arranged on side or the lower end of described satellite main body by described six degree of freedom isolation mounting.
4. remote sensing satellite system as claimed in claim 1, is characterized in that, described six degree of freedom isolation mounting comprises at least three support components, and described satellite main body is controlled the orientation of described optical remote sensing device by described at least three support components.
5. remote sensing satellite system as claimed in claim 4, is characterized in that, described support component is vibration isolator.
6. remote sensing satellite system as claimed in claim 5, is characterized in that, described vibration isolator comprises voice coil motor, and described satellite main body changes the length of described vibration isolator by controlling described voice coil motor.
7. remote sensing satellite system as claimed in claim 1, is characterized in that, described microwave remote sensing device is synthetic aperture radar.
8. remote sensing satellite system as claimed in claim 7, is characterized in that, described synthetic aperture radar is flat or parabola formula.
9. remote sensing satellite system as claimed in claim 1, is characterized in that, described optical remote sensing device is high-resolution optical camera.
10. remote sensing satellite system as claimed in claim 1, is characterized in that, the installation site of described microwave remote sensing device and described optical remote sensing device does not interfere with each other.
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| CN201410245065.2A CN104058110B (en) | 2014-06-04 | 2014-06-04 | Remote sensing satellite system |
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| CN201410245065.2A CN104058110B (en) | 2014-06-04 | 2014-06-04 | Remote sensing satellite system |
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| CN105572763A (en) * | 2015-12-15 | 2016-05-11 | 中国科学院遥感与数字地球研究所 | Atmospheric temperature and humidity profile line processing method under cloud cover and system thereof |
| CN110127079A (en) * | 2019-04-11 | 2019-08-16 | 上海卫星工程研究所 | Target flight system for simulating feature under remote sensing visual field based on six degree of freedom platform |
| CN113815909A (en) * | 2021-09-09 | 2021-12-21 | 中国人民解放军63920部队 | Uplink determining method and device for peer-to-peer mode combined configuration spacecraft |
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Cited By (6)
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| CN105572763A (en) * | 2015-12-15 | 2016-05-11 | 中国科学院遥感与数字地球研究所 | Atmospheric temperature and humidity profile line processing method under cloud cover and system thereof |
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| CN110127079A (en) * | 2019-04-11 | 2019-08-16 | 上海卫星工程研究所 | Target flight system for simulating feature under remote sensing visual field based on six degree of freedom platform |
| CN110127079B (en) * | 2019-04-11 | 2020-11-06 | 上海卫星工程研究所 | Target flight characteristic simulation system under remote sensing visual field based on six-degree-of-freedom platform |
| CN113815909A (en) * | 2021-09-09 | 2021-12-21 | 中国人民解放军63920部队 | Uplink determining method and device for peer-to-peer mode combined configuration spacecraft |
| CN113815909B (en) * | 2021-09-09 | 2023-10-27 | 中国人民解放军63920部队 | Uplink determining method and device for peer-to-peer mode combination configuration spacecraft |
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| CN104058110B (en) | 2016-08-10 |
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