CN112373736A - Satellite device for omnidirectional observation - Google Patents
Satellite device for omnidirectional observation Download PDFInfo
- Publication number
- CN112373736A CN112373736A CN202011020222.1A CN202011020222A CN112373736A CN 112373736 A CN112373736 A CN 112373736A CN 202011020222 A CN202011020222 A CN 202011020222A CN 112373736 A CN112373736 A CN 112373736A
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- servo
- payload
- satellite
- satellite platform
- yaw
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Abstract
The embodiment of the invention discloses a satellite device for omnidirectional observation, which comprises: the device comprises a satellite platform, a servo mechanism and payload equipment, wherein the servo mechanism is a two-dimensional turntable which is arranged at the top of the satellite platform and used for receiving command information from the outside of the device and driving the payload to rotate relative to the satellite platform in yaw and pitch directions; the payload equipment is arranged on the top of the servo mechanism, so that the payload equipment has a wider field of view; the small-angle attitude adjustment of the satellite platform is matched with the rotation of the top servo mechanism in two directions of large-angle pitching and yawing, so that the omnidirectional observation of the effective load can be realized.
Description
Technical Field
The invention relates to the technical field of space observation. And more particularly, to a satellite apparatus for omnidirectional observation.
Background
With the increasing and upgrading of the demand of space exploration tasks, the space observation satellite can realize all-around and multi-mode observation and becomes a core function, and under various observation modes, the configuration layout of the satellite, which can realize rapid tracking response observation, aerial all-around observation and strong universality, is a key technology to be solved at present.
Disclosure of Invention
One embodiment of the present invention provides a satellite apparatus for omnidirectional observation, including: satellite platforms, servos and payload equipment, wherein,
the servo mechanism is a two-dimensional turntable, is arranged at the top of the satellite platform and is used for receiving instruction information from the outside of the device and driving the effective load to rotate relative to the satellite platform in yaw and pitch directions;
the payload equipment is arranged on the top of the servo mechanism, so that the payload equipment has a wider field of view;
the small-angle attitude adjustment of the satellite platform is matched with the rotation of the top servo mechanism in two directions of large-angle pitching and yawing, so that the omnidirectional observation of the effective load can be realized.
In one embodiment, multiple payload devices can be installed by modifying the size of the payload mounting surface.
In a particular embodiment, the servo mechanism comprises a servo base, a servo yaw assembly, a servo pitch assembly, a locking bracket, and a locking screw, wherein,
the servo base is arranged at the bottommost end of the servo mechanism, is connected with the satellite platform and is used for supporting the servo mechanism and the payload equipment;
the servo yaw component is arranged at the top end of the servo base and used for realizing rotary motion relative to the satellite platform;
the servo pitching component is arranged on an output shaft of the servo yawing component, can rotate along with the servo yawing component, and can realize pitching motion relative to the servo yawing component.
In a particular embodiment, the payload device is mounted on a flat surface on top of the servo pitch member, moving with the servo pitch member.
In a specific embodiment, the servo mechanism further comprises a locking bracket and a locking screw, wherein a first end of the locking bracket is fixedly connected with the servo yaw component, and a second end of the locking bracket is fixedly connected with the servo base through the locking screw.
In a specific embodiment, the small-angle attitude adjustment of the satellite platform is matched with the large-angle rotation of the servo pitching component, so that the omnibearing rotation in the pitching direction can be realized.
In a particular embodiment, the servo base internally houses a drive device for positioning a servo yaw assembly.
The invention has the following beneficial effects:
the satellite device for omnidirectional observation provided by the invention is suitable for different satellite platforms and effective loads; the expansibility is strong, and various effective loads can be installed in an expanded way; the satellite platform does not need to carry a large amount of propellants and is provided with a plurality of propellers to adjust the posture at a large angle, and the small-angle posture of the satellite platform and the large-angle pitching and yawing of the top servo mechanism are only adjusted, so that the omnidirectional observation of the effective load can be realized, the load is driven to track, position and observe, the response speed is high, the maneuvering speed is high, and the posture adjusting precision is high.
Drawings
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
Fig. 1 shows a satellite device for omnidirectional observation according to one embodiment of the present invention.
Fig. 2 shows a different directional view of a payload, according to one embodiment of the invention.
Detailed Description
In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and is not to be taken as limiting the scope of the invention.
As shown in fig. 1, an embodiment of the present invention provides a satellite device for omnidirectional observation, including: a satellite platform 1, a servo 2 and a payload device 3, wherein,
the servo mechanism 2 is a two-dimensional turntable, is arranged at the top of the satellite platform 1 and is used for receiving instruction information from the outside of the device, returning measurement information such as the working state and the angular position of the servo mechanism and the like, and driving the effective load to rotate relative to the satellite platform in yaw and pitch directions; the payload equipment 3 is arranged on the top of the servo mechanism, so that the payload equipment has a wider field of view; the small-angle attitude adjustment of the satellite platform 1 is matched with the rotation of the top servo mechanism 2 in two directions of large-angle pitching and yawing, so that the omnidirectional observation of the effective load can be realized.
The satellite body 1 is not limited to a specific structure, the installation surface on the top of the satellite body can be provided with a servo mechanism, and the payload equipment is not limited to specific equipment, has universality and can be a space camera, a detector or other observation type load equipment.
Fig. 2 shows three different directional views of the servo mechanism rotating the payload device, view a) at 0 ° yaw, view b) at 0 ° pitch at 60 ° yaw, view c) at 300 ° pitch at 50 °.
The servo mechanism has a structure comprising: servo base 21, servo yaw assembly 22, servo pitch assembly 23, locking bracket 24 and locking screw 25.
The servo base 21 is arranged at the bottommost end of the servo mechanism 2, is connected with the satellite platform 1, mainly plays a role in supporting the servo mechanism 2 and the payload equipment 3, and can also be internally provided with driving equipment of a yaw component;
the servo yaw component 22 is arranged at the top end of the servo base 21 and can realize rotating motion of 1360 degrees relative to the satellite platform;
the servo pitch part 23 is mounted on an output shaft of the servo yaw part 22, and can rotate together with the servo yaw part 22 and can also realize a pitch motion relative to the servo yaw part 22;
a first end of the locking bracket 24 is fixedly connected with the servo yaw component 23, and a second end of the locking bracket is fixedly connected with the servo base 21 through a locking screw 25; when the satellite is launched, the locking support 24 and the locking screw 25 are adopted to lock the payload equipment 3 on the servo mechanism 2, so that the payload equipment 3 is ensured to have good mechanical property in the launching stage, and after the satellite is in orbit, the locking screw 25 is exploded through an initiating explosive device or other modes, so that the payload equipment 3 is unlocked, and a specified observation task is completed;
the payload equipment 3 is mounted on a plane on top of the servo pitch section 23, moving with the servo pitch section 23, while different kinds or more of payload equipment can be arranged by modifying the size of the mounting surface.
The yaw assembly 22 of the servomechanism 2 is capable of yaw rotation 1360 ° relative to the satellite platform; because the servo mechanism 2 and the satellite platform 1 have installation surfaces with certain areas, the pitching component 23 has a certain small-angle blind area, but when an observation task is executed, the attitude can be adjusted through the small angle of the satellite platform 1, and the 360-degree rotation in the pitching direction can be realized by matching with the large-angle rotation of a pitching shaft; in summary, the servomechanism 2 can drive the payload device 3 to achieve omnidirectional observation of the space.
In one example, the servo base internally houses a drive apparatus for positioning a servo yaw assembly.
The satellite device for omnidirectional observation provided by the invention is suitable for different satellite platforms and effective loads; the expansibility is strong, and various effective loads can be installed in an expanded way; the satellite platform does not need to carry a large amount of propellants and is provided with a plurality of propellers to adjust the posture at a large angle, and the small-angle posture of the satellite platform and the large-angle pitching and yawing of the top servo mechanism are only adjusted, so that the omnidirectional observation of the effective load can be realized, the load is driven to track, position and observe, the response speed is high, the maneuvering speed is high, and the posture adjusting precision is high.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (7)
1. A satellite apparatus for omnidirectional observation, comprising: satellite platforms, servos and payload equipment, wherein,
the servo mechanism is a two-dimensional turntable, is arranged at the top of the satellite platform and is used for receiving instruction information from the outside of the device and driving the effective load to rotate relative to the satellite platform in yaw and pitch directions;
the payload equipment is arranged on the top of the servo mechanism, so that the payload equipment has a wider field of view;
the small-angle attitude adjustment of the satellite platform is matched with the rotation of the top servo mechanism in two directions of large-angle pitching and yawing, so that the omnidirectional observation of the effective load is realized.
2. The apparatus of claim 1, wherein a plurality of payload devices can be installed by modifying the size of the payload mounting surface.
3. The apparatus of claim 1, wherein the servo mechanism comprises a servo base, a servo yaw component, and a servo pitch component, wherein,
the servo base is arranged at the bottommost end of the servo mechanism, is connected with the satellite platform and is used for supporting the servo mechanism and the payload equipment;
the servo yaw component is arranged at the top end of the servo base and used for realizing rotary motion relative to the satellite platform;
the servo pitching component is arranged on an output shaft of the servo yawing component, can rotate along with the servo yawing component, and can realize pitching motion relative to the servo yawing component.
4. The apparatus of claim 3, wherein the payload device is mounted on a flat surface on top of the servo pitch member for movement with the servo pitch member.
5. The apparatus of claim 3, wherein the servo mechanism further comprises a locking bracket and a locking screw, wherein a first end of the locking bracket is fixedly connected with the servo yaw assembly, and a second end of the locking bracket is fixedly connected with the servo base through the locking screw.
6. The apparatus of claim 3, wherein the small angular adjustment of the satellite platform in combination with the large angular rotation of the servo-pitch assembly enables omni-directional rotation in the pitch direction.
7. An arrangement according to claim 3, characterized in that the servo base frame is internally provided with drive means for positioning a servo yaw member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011020222.1A CN112373736A (en) | 2020-09-25 | 2020-09-25 | Satellite device for omnidirectional observation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011020222.1A CN112373736A (en) | 2020-09-25 | 2020-09-25 | Satellite device for omnidirectional observation |
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| CN112373736A true CN112373736A (en) | 2021-02-19 |
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| CN202011020222.1A Pending CN112373736A (en) | 2020-09-25 | 2020-09-25 | Satellite device for omnidirectional observation |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374206A (en) * | 2023-04-24 | 2023-07-04 | 中国科学院微小卫星创新研究院 | Multi-turn satellite and spacecraft |
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| US20110155858A1 (en) * | 2008-06-09 | 2011-06-30 | Astrium Sas | Method for controlling satellite attitude, and attitude-controlled satellite |
| CN205352218U (en) * | 2015-12-31 | 2016-06-29 | 北京航天科颐技术有限公司 | Two -dimentional test turntable of guided missile |
| CN110645456A (en) * | 2019-11-08 | 2020-01-03 | 中国科学院长春光学精密机械与物理研究所 | Large-angle and light servo structure of space remote sensing precision instrument |
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2020
- 2020-09-25 CN CN202011020222.1A patent/CN112373736A/en active Pending
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| US20110155858A1 (en) * | 2008-06-09 | 2011-06-30 | Astrium Sas | Method for controlling satellite attitude, and attitude-controlled satellite |
| CN205352218U (en) * | 2015-12-31 | 2016-06-29 | 北京航天科颐技术有限公司 | Two -dimentional test turntable of guided missile |
| CN110645456A (en) * | 2019-11-08 | 2020-01-03 | 中国科学院长春光学精密机械与物理研究所 | Large-angle and light servo structure of space remote sensing precision instrument |
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| CN116374206A (en) * | 2023-04-24 | 2023-07-04 | 中国科学院微小卫星创新研究院 | Multi-turn satellite and spacecraft |
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Application publication date: 20210219 |