CN200950315Y - Experiment platform for simulating visual trace of sub-mini rotorcraft - Google Patents
Experiment platform for simulating visual trace of sub-mini rotorcraft Download PDFInfo
- Publication number
- CN200950315Y CN200950315Y CN 200620046137 CN200620046137U CN200950315Y CN 200950315 Y CN200950315 Y CN 200950315Y CN 200620046137 CN200620046137 CN 200620046137 CN 200620046137 U CN200620046137 U CN 200620046137U CN 200950315 Y CN200950315 Y CN 200950315Y
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- CN
- China
- Prior art keywords
- dolly
- fixed
- wire rope
- trolley
- guide rail
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- Expired - Fee Related
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Abstract
The utility model relates to an experimental platform for simulate microminiature rotorcraft visual tracking. The utility model contains a horizontal mounting guide rail, and the two ends of the rail are separately fixed on two bracket; a trolley with fixed rolling pulley. The rolling pulley matches with the rolling of guide rail. In the trolley is installed a fixed camera. On one of the brackets is installed a fixed driving motor. The output axis end of the driving motor communicates with a tighten sheave with fixed connection. On the other bracket is installed with another tighten sheave. The two ends of a wire rope are fixed on the trolley, and the wire rope bypasses the two tighten sheaves in ringwise. Through the vibration frequency of the visual tracking system to determine the structure diameter of the platform, at the same time, the wire rope communicates with the trolley with offset connection. The nearly real simulation is based on the actual movement of the microminiature rotorcraft tracking system. The utility model provides the convenient for study and experiment, which has good economical efficiency.
Description
Technical field
The utility model relates to a kind of experiment porch of simulating microminiature rotor craft vision track.
Background technology
Mobile surface targets low-altitude follow-up system based on the microminiature rotor craft has strengthened monitoring and the maneuverability of following the tracks of, and reliability has enlarged the scope of monitoring, and is particularly suitable for long distance, follows the tracks of suspicious object on a large scale.
At present based on the experiment of the mobile surface targets low-altitude follow-up system of microminiature rotor craft difficulty carry out, mainly be because experiment needs the support of microminiature rotor craft, factor is more and the flight of microminiature rotor craft is affected by the external environment, usually need open experiment place, weather preferably, aircraft needs special messenger's manipulation simultaneously, the aircraft hang time is limited or the like, all multifactor securities that causes based on the experiment of the vision track of microminiature rotor craft, reliability, economy is relatively poor.
Summary of the invention
The purpose of this utility model is to provide a kind of experiment porch of simulating microminiature rotor craft vision track, simulation is based on the actual motion of the mobile surface targets low-altitude follow-up system of microminiature rotor craft, mainly comprise the vibration of system, swinging, advance, retreat, quickening and motion such as deceleration when hovering.
For achieving the above object, the utility model by the following technical solutions:
A kind of experiment porch of simulating microminiature rotor craft vision track, comprise a guide rail horizontal setting and two ends are separately fixed on two supports, it is characterized in that having a dolly to roll and mate, camera of fixed installation on the dolly with its fixedly connected rolling pulley and described guide rail; Drive motor of fixed installation on the described support, the fixedly connected tightener sheave of the output axle head of drive motor, another tightener sheave is installed on another support, and the two ends of a wire rope are fixedly connected on the dolly and walk around two tightener sheaves ringwise.
Above-mentioned wire rope is connected with the dolly biasing, and promptly its line is without the centre of gyration of dolly.
Distance between two supports is to determine according to the actual vibration frequency of tracker and the selected section bar of guide rail, wire rope and dolly be connected the centre of gyration without dolly.
Determining of concrete structure:
Guide rail is selected existing section bar for use, two ends are fixed on the support, therefore guide rail can be reduced to free beam, determine two distances between the support according to free beam flexural vibrations Calculation of Natural Frequencies method, between the vibration frequency range of the natural frequency that makes guide rail as far as possible tracker in the smooth flight of microminiature rotor craft and when hovering.
Wire rope is connected with the dolly biasing, and its line is without the centre of gyration of dolly, and this will produce a moment of torsion, and dolly is rotated within the specific limits.Rotating angular dimension depends on the distance of biasing.
The sense of current by changing drive motor and the size of electric current realize that dolly advances, retreats, quickens and slows down with the advancing of simulated flight device, retreats, acceleration and retarded motion, also will produce certain vibration when dolly moves simultaneously on guide rail, with the vibration of simulation rotor craft.Because wire rope adopts biasing to be connected with dolly, and wire rope has certain elasticity, pull of steel wire will produce a moment of torsion to dolly, make dolly deflect, therefore can be by continuously changing the drive motor sense of current, make the continuous rotating of drive motor switch, thereby make swinging when deflection is hovered with the simulation rotor craft back and forth about dolly.
The utility model compared with prior art, be that mainly experiment porch not only simulated the flare maneuver of aircraft, also taken into full account the vibration of system, be close to real simulated based on the actual motion of the mobile surface targets low-altitude follow-up system of microminiature rotor craft.For research and experiment is provided convenience, overcome the security of open-air vision track experiment simultaneously again, integrity problem has good and economic.
Description of drawings
Fig. 1 is the structural representation of an embodiment of the utility model
Embodiment
A preferred embodiment of the present utility model is: referring to Fig. 1, the guide rail 1 of the experiment porch of simulation microminiature rotor craft vision track is horizontally fixed on support 3, on 9, dolly 2 is suspended on the guide rail 1, drive motor 4 is fixed on the support 3, the fixedly connected tightener sheave 5 of the output shaft of drive motor 4, tightener sheave 8 is installed on the support 9, the two ends of wire rope 7 are fixedly connected on and walk around two tightener sheaves 5 on the dolly 2 ringwise, 8, wire rope 7 is connected with dolly 2 biasings, the centre of gyration without dolly 2, drive motor 4 is just changeing, counter-rotating, wire rope 7 pulling dollies 2 seesaw, drive motor 4 continuous rotatings, wire rope 7 pulling dollies 2 produce left and right sides yaw motion.Monitoring camera 6 is fixed on the dolly 2 of this experiment porch, this platform simulation aircraft smooth flight and the state that hovers, produce certain vibration simultaneously, at this moment the image that collects of monitoring camera 6 and monitoring camera 6 image that is fixed on the rotor craft to be gathered has the phenomenon of similar shake, and the actual motion of the vision track system on the microminiature rotor craft that has been close to real simulated of this experiment porch has been described.
Claims (2)
1. experiment porch of simulating microminiature rotor craft vision track, comprise guide rail (a 1) horizontal setting and two ends are separately fixed on two supports (3,9), it is characterized in that having a dolly (2) to roll with its fixedly connected rolling pulley and described guide rail (1) and mate, dolly (2) is gone up a fixed installation camera (6); A described support (3) is gone up a fixed installation drive motor (4), the fixedly connected tightener sheave of the output axle head of drive motor (4) (5), another support (9) is gone up another tightener sheave (8) is installed, and the two ends of a wire rope (7) are fixedly connected on dolly (2) and upward walk around two tightener sheaves (5,8) ringwise.
2. the experiment porch of simulation microminiature rotor craft vision track according to claim 1 is characterized in that described wire rope (7) is connected with dolly (2) biasing, and promptly its line is without the centre of gyration of dolly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620046137 CN200950315Y (en) | 2006-09-21 | 2006-09-21 | Experiment platform for simulating visual trace of sub-mini rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620046137 CN200950315Y (en) | 2006-09-21 | 2006-09-21 | Experiment platform for simulating visual trace of sub-mini rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200950315Y true CN200950315Y (en) | 2007-09-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620046137 Expired - Fee Related CN200950315Y (en) | 2006-09-21 | 2006-09-21 | Experiment platform for simulating visual trace of sub-mini rotorcraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200950315Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102169328A (en) * | 2011-01-31 | 2011-08-31 | 上海大学 | Active control test platform and method for vibration of near space aircraft model |
| CN102650851A (en) * | 2011-02-25 | 2012-08-29 | 中国科学院沈阳自动化研究所 | Indoor multi-rotor flying robot test platform |
| CN103531072A (en) * | 2013-09-29 | 2014-01-22 | 天津航天机电设备研究所 | X-ray pulsar ground acquisition and tracking demonstration system |
| CN103954314A (en) * | 2014-04-16 | 2014-07-30 | 浙江大学 | Unmanned aerial vehicle low-altitude remote sensing simulating device |
| CN104200715A (en) * | 2014-09-23 | 2014-12-10 | 北京控制工程研究所 | Spacecraft flying-around approach motion simulator |
| CN106768565A (en) * | 2017-03-09 | 2017-05-31 | 北京尖翼科技有限公司 | A kind of test device of small-sized unmanned aircraft motor |
| CN111102976A (en) * | 2018-10-25 | 2020-05-05 | 哈尔滨工业大学 | Simulation experiment table for landing buffering process of asteroid probe |
-
2006
- 2006-09-21 CN CN 200620046137 patent/CN200950315Y/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102169328A (en) * | 2011-01-31 | 2011-08-31 | 上海大学 | Active control test platform and method for vibration of near space aircraft model |
| CN102169328B (en) * | 2011-01-31 | 2012-11-14 | 上海大学 | Active control test platform and method for vibration of near space aircraft model |
| CN102650851A (en) * | 2011-02-25 | 2012-08-29 | 中国科学院沈阳自动化研究所 | Indoor multi-rotor flying robot test platform |
| CN102650851B (en) * | 2011-02-25 | 2013-10-09 | 中国科学院沈阳自动化研究所 | Indoor multi-rotor flying robot test platform |
| CN103531072A (en) * | 2013-09-29 | 2014-01-22 | 天津航天机电设备研究所 | X-ray pulsar ground acquisition and tracking demonstration system |
| CN103954314A (en) * | 2014-04-16 | 2014-07-30 | 浙江大学 | Unmanned aerial vehicle low-altitude remote sensing simulating device |
| CN104200715A (en) * | 2014-09-23 | 2014-12-10 | 北京控制工程研究所 | Spacecraft flying-around approach motion simulator |
| CN104200715B (en) * | 2014-09-23 | 2016-05-04 | 北京控制工程研究所 | A kind of spacecraft is diversion and approaches motion simulator |
| CN106768565A (en) * | 2017-03-09 | 2017-05-31 | 北京尖翼科技有限公司 | A kind of test device of small-sized unmanned aircraft motor |
| CN111102976A (en) * | 2018-10-25 | 2020-05-05 | 哈尔滨工业大学 | Simulation experiment table for landing buffering process of asteroid probe |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |