CN102501979B - Airborne navigation nacelle - Google Patents
Airborne navigation nacelle Download PDFInfo
- Publication number
- CN102501979B CN102501979B CN 201110355279 CN201110355279A CN102501979B CN 102501979 B CN102501979 B CN 102501979B CN 201110355279 CN201110355279 CN 201110355279 CN 201110355279 A CN201110355279 A CN 201110355279A CN 102501979 B CN102501979 B CN 102501979B
- Authority
- CN
- China
- Prior art keywords
- pedestal
- base
- ring platform
- unmanned plane
- navigation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The invention relates to an airborne navigation nacelle which is used for providing enemy destination parameters to a main control room and comprises an inner ring platform, an outer ring frame and a base, wherein, the inner ring platform is hinged with the outer ring frame through a rotating shaft; the outer ring frame is hinged with the base through a hinge shaft; the base is fixed at the bottom of an airplane; a visible light television imaging system and a laser rangefinder are arranged inside the inner ring platform; the inner ring platform comprises a two-degree-of-freedom gyroscope, accelerometers, an imaging device, the laser rangefinder and a double-channel rotary transforming angle transducer; in addition, the outer ring frame comprises the double-channel rotary transforming angle transducer; a micromachining gyroscope is arranged on the base in the ordinate axis direction of an unmanned plane, measures the three-axis attitude of a carrier, and offsets the correlative navigation errors. Air speedometers are arranged in the ordinate axis direction and the pitch axis direction of the unmanned plane; an altimeter is arranged at the bottom of the base so as to measure the height of the unmanned plane; and the accelerometers are arranged at the two ends of the base so as to achieve levelling when in initial alignment. The airborne navigation nacelle can integrally detect,search and track a target, and has the advantages of high system reliability and low cost.
Description
Technical field
The present invention relates to a kind of airborne navigation nacelle, be used to master control room that the parameter of unfriendly target is provided.
Background technology
The modern times in tech war, along with the development of missilery, missile operations radius in naval vessel increases, marine battlefield is more wide, the over the horizon attack operations becomes the main patterns of warfare of surface craft anti-ship combat.So-called over the horizon is attacked and is referred to utilize special remote object indicating system that the target indication is provided, the missile attack that the target beyond the shipborne radar over the horizon is implemented.Realization is that the anti-warship guided missle weapon platform must at first carry out the over the horizon location to target to the prerequisite of extra large over-the-horizon missile attack.The method that realizes the over the horizon location mainly contains repeater station location, extendable platform navigation coordinate localization method and basic point localization method.Different from mutual locate mode between the repeater station according to the anti-warship guided missle weapon platform, consisted of again different over the horizon target positioning modes, mainly contain unidirectional relay observation localization method, two-way relay observation localization method, take aim at localization method mutually.
In five kinds of over the horizon localization methods above-mentioned, except extendable platform target positioning method with take aim at mutually localization method and need to launch the warship active probe device power-up, all the other all types of target localization method emission warship active probe equipment need not started shooting, so from disguised angle, these two kinds of localization methods are weaker than that other are several.From the accuracy of positioning angle analysis, other are several although extendable platform navigation coordinate localization method precision is higher than, and the GPS navigation information that needs to use utilizes the U.S. to provide, so in the eventuality, its reliability will be restricted.
Summary of the invention
In order to overcome the shortcoming of prior art, the invention provides a kind of airborne navigation nacelle, to scouting, the search of target, follow the tracks of in one, system reliability is high, and cost is low.
The present invention solves the technical scheme that its technical matters takes: comprise interior ring platform, outer shroud framework and pedestal, interior ring platform is hinged by rotating shaft and outer shroud framework, the outer shroud framework is hinged by hinge and pedestal, pedestal is fixed on the bottom of aircraft, in the interior ring platform visual TV imaging system and laser rangefinder is arranged; Described interior ring platform is the stable benchmark of inertia device, comprises that two-degrees-of freedom gyro, accelerometer, imaging device, laser rangefinder and binary channel revolve the varied angle sensor.Described outer shroud framework carries out the rotation of orientation degree, comprises that binary channel revolves the varied angle sensor.Described pedestal carries out the carrier three-axis attitude and measures along micromechanical gyro gyro of unmanned plane y direction configuration, compensation navigation correlated error.Dispose a Pitot meter along unmanned plane Y and pitch axis to each.Carrying out the unmanned plane height at pedestal bottom altimeter of configuration measures.Leveling when disposing accelerometer as initial alignment at the pedestal two ends.
The present invention integrate the carrier Camera calibration and to scouting, the search of target, follow the tracks of, namely not only can finish the function that general gondola has, and can high precision, the navigation information of real-time output carrier.Can be handling thereby improved, increased integrated level, simplified mode of operation, reduced the hardware configuration of system, greatly improve reliability, reduced cost.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is structural representation of the present invention;
Fig. 2 is stable loop block scheme of the present invention;
Fig. 3 is searching loop block scheme of the present invention;
Fig. 4 is video location tracking loop block scheme of the present invention.
The specific embodiment
As shown in Figure 1, the present invention includes interior ring platform 1, outer shroud framework 2 and pedestal 3, interior ring platform 1 is hinged by rotating shaft 5 and outer shroud framework 2, and outer shroud framework 2 is hinged by hinge 4 and pedestal 3, pedestal 3 is fixed on the bottom of aircraft, in the interior ring platform 1 visual TV imaging system and laser rangefinder is arranged; Described interior ring platform 1 is the stable benchmark of inertia device, comprises that two-degrees-of freedom gyro, accelerometer, imaging device, laser rangefinder and binary channel revolve the varied angle sensor.Described outer shroud framework carries out orientation 360 degree rotation, comprises that binary channel revolves the varied angle sensor.Described pedestal carries out the carrier three-axis attitude and measures along micromechanical gyro of unmanned plane y direction configuration, compensation navigation correlated error.Dispose a Pitot meter along unmanned plane Y and pitch axis to each.Carrying out the unmanned plane height at pedestal bottom altimeter of configuration measures.Leveling when disposing accelerometer as initial alignment at the pedestal two ends.
Described imaging device comprises glass window, variable focal length optical system, variable diaphragm mechanism, optical filtering mechanism and high performance video camera.In order to improve details resolution capability, can fix in addition large face battle array, high-definition color digital camera.
Described laser rangefinder comprises transmitter-receiver device, and feedway comprises optical module and laser, and receiving device comprises avalanche photodide, range information treatment circuit.
In order to eliminate the impact of carrier disturbance, system adopts the gyro to measure optical axis with respect to the motion of geodetic coordinates system, when optical axis moves with respect to geodetic coordinate system, the gyro sensitivity goes out the change in location of motion, proofread and correct, amplify the rear drive motor through control system and make the optical axis counter motion, thereby make optical axis stable.
Apply electric current for the gyro torque device, just can make optical axis search.Control system is divided orientation and pitching two dimension, revolves change etc. by gyro, torque motor, binary channel and forms.Comprise stable loop, searching loop and video location tracking loop, stable loop as shown in Figure 2.Searching loop as shown in Figure 3.The video location tracking loop is asked for circuit (video tracker) by telecamera or thermal infrared imager and error and is consisted of closed loop, in order to realize automatically track target.The video location tracking loop as shown in Figure 4.
Claims (3)
1. airborne navigation nacelle, it is characterized in that: comprise interior ring platform (1), outer shroud framework (2) and pedestal (3), interior ring platform (1) is hinged by rotating shaft (5) and outer shroud framework (2), outer shroud framework (2) is hinged by hinge (4) and pedestal (3), pedestal (3) is fixed on the bottom of aircraft, in the interior ring platform (1) visual TV imaging system and laser rangefinder is arranged; Described interior ring platform (1) is the stable benchmark of inertia device, comprises that two-degrees-of freedom gyro, accelerometer, imaging device, laser rangefinder and binary channel revolve the varied angle sensor; Described outer shroud framework carries out orientation 360 degree rotation, comprises that binary channel revolves the varied angle sensor; Described pedestal is along micromechanical gyro of unmanned plane y direction configuration, carrying out the carrier three-axis attitude measures, compensation navigation correlated error, dispose a Pitot meter along unmanned plane Y and pitch axis to each, carry out the unmanned plane height at pedestal bottom altimeter of configuration and measure the leveling when disposing accelerometer as initial alignment at the pedestal two ends.
2. airborne navigation nacelle according to claim 1, it is characterized in that: described imaging device comprises glass window, variable focal length optical system, variable diaphragm mechanism, optical filtering mechanism and high performance video camera.
3. airborne navigation nacelle according to claim 1, it is characterized in that: described laser rangefinder comprises transmitter-receiver device, and feedway comprises optical module and laser, and receiving device comprises avalanche photodide, range information treatment circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110355279 CN102501979B (en) | 2011-11-10 | 2011-11-10 | Airborne navigation nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110355279 CN102501979B (en) | 2011-11-10 | 2011-11-10 | Airborne navigation nacelle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102501979A CN102501979A (en) | 2012-06-20 |
| CN102501979B true CN102501979B (en) | 2013-10-16 |
Family
ID=46214134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110355279 Active CN102501979B (en) | 2011-11-10 | 2011-11-10 | Airborne navigation nacelle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102501979B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104567653B (en) * | 2014-12-26 | 2016-06-29 | 北京航天控制仪器研究所 | A kind of method of electric vortex sensor measuring many frameworks gondola inner frame angle |
| CN105607639A (en) * | 2015-12-21 | 2016-05-25 | 河北汉光重工有限责任公司 | Posture solving and compensating method for triaxial stable servo platform |
| CN106379559B (en) * | 2016-09-29 | 2019-08-20 | 湖北航天技术研究院总体设计所 | A kind of transition air navigation aid suitable for guided missile launched by airplane |
| CN206265327U (en) * | 2016-11-18 | 2017-06-20 | 捷西迪（广州）光学科技有限公司 | A kind of unmanned aerial vehicle for underwater photograph technical |
| CN107933940B (en) * | 2017-10-26 | 2019-07-30 | 北京遥感设备研究所 | A kind of cantilevered support structure suitable for airborne photoelectric servo platform |
| CN108286959A (en) * | 2017-12-14 | 2018-07-17 | 彩虹无人机科技有限公司 | A kind of O-E Payload for UAV is detectd to be calculated and display methods according to region |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2593127B2 (en) * | 1992-12-02 | 1997-03-26 | 新明和工業株式会社 | Elevating device for aircraft aerial photography camera |
| CN101774431A (en) * | 2010-01-22 | 2010-07-14 | 清华大学 | Spherical hanging type two freedom degree holder for unmanned device |
| CN101758929A (en) * | 2010-01-22 | 2010-06-30 | 清华大学 | Unmanned frame style cradle head of two degrees of freedom |
| CN201974620U (en) * | 2011-03-28 | 2011-09-14 | 广州市红鹏直升机遥感科技有限公司 | Triaxial aerial photography holder |
-
2011
- 2011-11-10 CN CN 201110355279 patent/CN102501979B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN102501979A (en) | 2012-06-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102501979B (en) | Airborne navigation nacelle | |
| CN103149948B (en) | Two-freedom-degree heavy-load tracking stabilized platform system | |
| US7239976B2 (en) | Method and system for automatic pointing stabilization and aiming control device | |
| US9074888B2 (en) | Gyro drift cancelation | |
| CN111044994B (en) | Optical axis calibration device and method for airborne laser range finder of airplane | |
| US20140049643A1 (en) | Gimbal systems providing high-precision imaging capabilities in a compact form-factor | |
| US20080136923A1 (en) | System And Method For Stabilizing An Image | |
| KR20160087388A (en) | Interactive weapon targeting system displaying remote sensed image of target area | |
| CN108955722B (en) | Unmanned aerial vehicle target positioning indicating system and indicating method | |
| TW201710815A (en) | A global positioning system ("GPS") independent navigation system for a self-guided aerial vehicle utilizing multiple optical sensors | |
| KR102472938B1 (en) | Attitude determination by pulse beacon and low-cost inertial measurement unit | |
| CN111470055A (en) | Photoelectric navigation nacelle and photoelectric navigation system | |
| CN110220533A (en) | A kind of onboard electro-optical pod misalignment scaling method based on Transfer Alignment | |
| US9243931B2 (en) | AZ/EL gimbal housing characterization | |
| CN110220536B (en) | Vehicle-mounted strapdown inertial combination field rapid calibration device and method | |
| CN104201458B (en) | Spaceborne radar disturbs real-Time Compensation decoupling method and compensated decoupling system to spacecraft platform | |
| RU179821U1 (en) | AUTOMATED GUIDANCE AND FIRE CONTROL SYSTEM OF RUNNING INSTALLATION OF REACTIVE SYSTEM OF VOLUME FIRE (OPTIONS) | |
| CN211375202U (en) | Comprehensive target correcting instrument for multiple axes of armed aircraft | |
| CN112415535A (en) | Navigation system and navigation method | |
| RU2697939C1 (en) | Method of target design automation at aiming at helicopter complex | |
| CN111157021A (en) | Aircraft reconnaissance camera optical axis calibration device and method based on inertial navigation and optical measurement | |
| CN112882498A (en) | Three-axis photoelectric search tracking device and method with image rotation inhibiting function | |
| CN211928165U (en) | Target correcting instrument for optical axis of laser range finder of armed aircraft | |
| CN111380563A (en) | Detection device, photoelectric theodolite detection system and aviation airborne optical platform detection system | |
| RU2498193C2 (en) | Method of inertial auto-tracking of specified object of viewing and system for its implementation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |