CN203672381U - Posture stabilizing device based on double gyroscopes - Google Patents
Posture stabilizing device based on double gyroscopes Download PDFInfo
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- CN203672381U CN203672381U CN201320860602.5U CN201320860602U CN203672381U CN 203672381 U CN203672381 U CN 203672381U CN 201320860602 U CN201320860602 U CN 201320860602U CN 203672381 U CN203672381 U CN 203672381U
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Abstract
The utility model discloses a posture stabilizing device based on double gyroscopes. The posture stabilizing device adopts an externally mounted overall annular shelf structure; a camera is mounted on a stabilizing plane of a direction frame; a direction axis is used as a Z-axis; an inner frame can rotate around the X-axis of an outer frame; the outer frame can rotate around a Y-axis; a posture control gyroscope is mounted on a flying platform; a camera gyroscope is mounted on the camera; the two gyroscopes are connected with a servo control device through data lines. The posture stabilizing device adopts a double-gyroscope system, the posture control gyroscope is used for detecting the posture in normal operation so as to control the camera, and the camera gyroscope is used for detecting the posture of the camera so as to obtain a POS value with high precision. The two gyroscopes can be subjected to difference correction for eliminating magnetic shifting influence. When one gyroscope has faults, the faults can be corrected by the other gyroscope according to corresponding algorithms.
Description
Technical field
The utility model belongs to low altitude photogrammetry technical field, relates in particular to a kind of attitude stabilization device based on double tops instrument.
Background technology
Air photo technique has special meaning for the application of the military field such as aerial survey, scouting technology, also plays an important role for taking high-precision cadastre, city map and engineering mapping.But in the time of flight photography, aircraft can be subject to the impact of the machine and air-flow, and it is stable that body cannot keep, and to Airborne Camera, appointed area high precision taken and brought difficulty.Because imageing sensor is arranged on motion carrier, the attitude of carrier will be shaken, take the photograph image blurring, as lack the camera stable platform of certain precision, take aircraft and must extend the flight time, increase flight number, and the post-processed of giving image is brought difficulty by the decline of shooting quality, therefore, air photo technique need to have the camera stable platform of certain precision.
Utility model content
The purpose of this utility model is to provide a kind of attitude stabilization device based on double tops instrument, be intended to solve in air photo technique because imageing sensor is arranged on motion carrier, the attitude of carrier will be shaken, lack camera stable platform and make to take the photograph image blurring problem.
The utility model is achieved in that a kind of attitude stabilization device based on double tops instrument comprises attitude control gyroscope, camera gyroscope, camera loading frame, Servocontrol device, interface cable.
Described camera loading frame is divided into orientation framework, pitching frame, roll framework, and they are installed from inside to outside successively; It is fitted outside integral loop shelf structure that attitude stabilization device based on double tops instrument is taked structure, and photographic camera is arranged in the stability plane of orientation framework, and azimuth axis is Z axis, and inside casing can be around the X-axis rotation of housing, and housing can rotate around Y-axis; Attitude control gyroscope is arranged on flying platform, and camera gyroscope is arranged on camera, and two gyroscopes are connected with Servocontrol device by data line.
Further, described pitching frame, roll framework, orientation framework, each loading frame forms by support frame, bearing, steering wheel.
Further, described Servocontrol device is spent by power supply, two precision 0.5 gyro, GPS, main control computer (ARM) form.
effect gathers
The utility model adopts double tops instrument system, uses two three-axis gyroscopes that precision is 0.5 degree, and one is placed in the attitude value of measuring platform on platform, and one is placed in the attitude value of phase aircraft measurements camera.Attitude control gyroscope is in order to measure attitude to control camera in the time of normal work, and camera gyroscope is in order to measure camera attitude to obtain high-precision POS value.Two gyroscopes can carry out difference correction to eliminate the magnetic impact of wafing.In the time that wherein a certain gyroscope breaks down, can be corrected by another gyroscope according to corresponding algorithm.
Accompanying drawing explanation
Fig. 1 is the vertical view of the attitude stabilization device based on double tops instrument that provides of the utility model embodiment;
Fig. 2 is three axle configuration diagram of the attitude stabilization device based on double tops instrument that provides of the utility model embodiment.
In figure: 1, roll framework; 2, pitching frame; 3, camera gyroscope; 4, orientation framework; 5, Servocontrol device; 6, interface cable; 7, attitude control gyroscope; 8, camera
Embodiment
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein is only in order to explain the utility model, and be not used in restriction the utility model.
Fig. 1 and Fig. 2 show the structure of the attitude stabilization device based on double tops instrument, as shown in the figure, the utility model is achieved in that a kind of attitude stabilization device based on double tops instrument comprises attitude control gyroscope 7, camera gyroscope 3, camera loading frame, Servocontrol device 5, interface cable 6.
Described camera loading frame is divided into orientation framework 4, pitching frame 2, roll framework 1, and they are installed from inside to outside successively; It is fitted outside integral loop shelf structure that attitude stabilization device based on double tops instrument is taked structure, and photographic camera is arranged in the stability plane of orientation framework 4, and azimuth axis is Z axis, and inside casing can be around the X-axis rotation of housing, and housing can rotate around Y-axis; Attitude control gyroscope 7 is arranged on flying platform, and camera gyroscope 3 is arranged on camera, and two gyroscopes are connected with Servocontrol device 5 by data line.
Further, described pitching frame 2, roll framework 1, orientation framework 4, each loading frame forms by support frame, bearing, steering wheel.
Further, described Servocontrol device 5 is spent by power supply, two precision 0.5 gyro, GPS, main control computer (ARM) form.
Below in conjunction with drawings and the specific embodiments, application principle of the present utility model is further described.
The utility model adopts Platform INS Inertial, adopts gyroscope as the sensitive element of measuring platform pitching, roll and orientation three axles, and attitude control gyroscope 7 is arranged on flying platform, and camera gyroscope 3 is arranged on camera.Attitude control gyroscope 7 is in order to measure attitude to control camera in the time of normal work, and camera gyroscope 3 is in order to measure camera attitude to obtain high-precision POS value.Two gyroscopes can carry out difference correction to eliminate the magnetic impact of wafing.In the time that wherein a certain gyroscope breaks down, can be corrected by another gyroscope according to corresponding algorithm.
By reference to the accompanying drawings embodiment of the present utility model is described although above-mentioned; but the not restriction to the utility model protection domain; one of ordinary skill in the art should be understood that; on the basis of the technical solution of the utility model, those skilled in the art do not need to pay various modifications that performing creative labour can make or distortion still within protection domain of the present utility model.
Claims (3)
1. the attitude stabilization device based on double tops instrument, is characterized in that, the described attitude stabilization device based on double tops instrument comprises attitude control gyroscope, camera gyroscope, camera loading frame, Servocontrol device, interface cable; Described camera loading frame is divided into orientation framework, pitching frame, roll framework, and they are installed from inside to outside successively; It is fitted outside integral loop shelf structure that attitude stabilization device based on double tops instrument is taked structure, and photographic camera is arranged in the stability plane of orientation framework, and azimuth axis is Z axis, and inside casing can be around the X-axis rotation of housing, and housing can rotate around Y-axis; Attitude control gyroscope is arranged on flying platform, and camera gyroscope is arranged on camera, and two gyroscopes are connected with Servocontrol device by data line.
2. the attitude stabilization device based on double tops instrument as claimed in claim 1, is characterized in that, described pitching frame, roll framework, orientation framework, and each loading frame forms by support frame, bearing, steering wheel.
3. the attitude stabilization device based on double tops instrument as claimed in claim 1, is characterized in that, gyro, GPS, main control computer that described Servocontrol device is spent by power supply, two precision 0.5 form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320860602.5U CN203672381U (en) | 2013-12-25 | 2013-12-25 | Posture stabilizing device based on double gyroscopes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320860602.5U CN203672381U (en) | 2013-12-25 | 2013-12-25 | Posture stabilizing device based on double gyroscopes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203672381U true CN203672381U (en) | 2014-06-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320860602.5U Expired - Fee Related CN203672381U (en) | 2013-12-25 | 2013-12-25 | Posture stabilizing device based on double gyroscopes |
Country Status (1)
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104168460A (en) * | 2014-08-24 | 2014-11-26 | 武汉华中天经光电系统有限公司 | Light airborne three-axis stabilization image device |
| CN106289207A (en) * | 2015-06-26 | 2017-01-04 | 中国航天科工集团第四研究院指挥自动化技术研发与应用中心 | A kind of high-precision measuring method based on difference MEMS gyroscope |
| CN107941206A (en) * | 2017-11-27 | 2018-04-20 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN108007434A (en) * | 2017-11-27 | 2018-05-08 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN108119731A (en) * | 2017-12-28 | 2018-06-05 | 吉林大学 | The adjustable omnidirectional's vibration-isolating platform of posture |
| CN114384941A (en) * | 2022-01-13 | 2022-04-22 | 中北大学南通智能光机电研究院 | Similar carrier posture cooperation system based on OPENMV |
-
2013
- 2013-12-25 CN CN201320860602.5U patent/CN203672381U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104168460A (en) * | 2014-08-24 | 2014-11-26 | 武汉华中天经光电系统有限公司 | Light airborne three-axis stabilization image device |
| CN104168460B (en) * | 2014-08-24 | 2017-06-23 | 武汉华中天经光电系统有限公司 | A kind of light airborne three-axis stabilization device for image |
| CN106289207A (en) * | 2015-06-26 | 2017-01-04 | 中国航天科工集团第四研究院指挥自动化技术研发与应用中心 | A kind of high-precision measuring method based on difference MEMS gyroscope |
| CN107941206A (en) * | 2017-11-27 | 2018-04-20 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN108007434A (en) * | 2017-11-27 | 2018-05-08 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN108007434B (en) * | 2017-11-27 | 2019-08-06 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN107941206B (en) * | 2017-11-27 | 2019-11-05 | 安徽江淮汽车集团股份有限公司 | Gyroscope assembly |
| CN108119731A (en) * | 2017-12-28 | 2018-06-05 | 吉林大学 | The adjustable omnidirectional's vibration-isolating platform of posture |
| CN114384941A (en) * | 2022-01-13 | 2022-04-22 | 中北大学南通智能光机电研究院 | Similar carrier posture cooperation system based on OPENMV |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20171225 |