CN204998779U - Descending system for unmanned aerial vehicle - Google Patents
Descending system for unmanned aerial vehicle Download PDFInfo
- Publication number
- CN204998779U CN204998779U CN201520583070.4U CN201520583070U CN204998779U CN 204998779 U CN204998779 U CN 204998779U CN 201520583070 U CN201520583070 U CN 201520583070U CN 204998779 U CN204998779 U CN 204998779U
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- CN
- China
- Prior art keywords
- microcontrol processor
- umbrella
- sensor
- unmanned plane
- microcontrol
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Abstract
The utility model relates to a descending system for unmanned aerial vehicle has descending system and the the control unit of setting at unmanned aerial vehicle's umbrella under -deck, the descending system links to each other with the one end of throwing the umbrella catapult, it fixes in umbrella bottom of a ship's hold portion to throw the other end of umbrella catapult, the control unit includes microcontrol processor, sensor and wireless communication circuit, the output of sensor links to each other with microcontrol processor's input, microcontrol processor's output is connected with the hasp of throwing the umbrella catapult, and microcontrol processor's output is closed down to press the button with the screw and is connected, wireless communication circuit and ground receiving station wireless remote control are connected, it is connected with the microcontrol processor both -way communication to fly to control motor -circuit, the self -lock device that falls to the ground is connected with the microcontrol processor both -way communication. The utility model discloses can close down earlier in reliable realization and launch the descending system under the screw prerequisite to the safe and reliable who has ensured the descending system uses.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly a kind of unmanned plane landing system.
Background technology
Landing system is a kind of equipment utilizing air resistance to slow down rapidly, is one of aircraft, parachutist, the most effective means of dropped object safe falling! Also be the most important component part of aircraft, it is the barrier of last one safety control of aircraft! There is the outstanding advantages such as lightweight, simple and reliable convenience.Landing system uses very extensive at Fixed Wing AirVehicle, little of model plane, unmanned plane, arrives greatly aircraft carrier, space shuttle; But the utilization on rotor craft exists larger technical difficulty, its reason stops propeller aircraft rotating instantaneously if can not solve, and the hawser of that landing system is just very easily cut off by the screw propeller of rotor self, loses the due effect of landing system.Present high most advanced and sophisticated helicopter is that the mode adopting first demolition propeller aircraft then to play umbrella realizes.But this mode can only be protected aviator and can not protect aircraft, shortcoming is fairly obvious.
Summary of the invention
The purpose of this utility model overcomes the defect that prior art exists, and provides a kind of and be widely used, dually to launch, the unmanned plane landing system of Based Intelligent Control.
The technical scheme realizing the utility model object is: a kind of unmanned plane landing system, has and is arranged on landing system in the umbrella cabin of unmanned plane and control unit; Described landing system is connected with the one end of throwing umbrella ejector; The other end of described throwing umbrella ejector is fixed on umbrella bilge portion; Described control unit comprises microcontrol processor, sensor and wireless communication line; The mouth of described sensor is connected with the input end of microcontrol processor; The mouth of described microcontrol processor is connected with the snap close throwing umbrella ejector, and the mouth of microcontrol processor and screw propeller are closed down button and be connected; Described wireless communication line is connected with ground receiving station Wireless remote control; The described control motor circuit that flies is connected with microcontrol processor intercommunication; The described self-locking device that lands is connected with microcontrol processor intercommunication.
Sensor described in technique scheme comprises the geomagnetic sensor, three-axis gyroscope and the weight sensor that are all electrically connected with microcontrol processor; Described geomagnetic sensor is parallel to fuselage bottom and installs setting; The course axle that described three-axis gyroscope is parallel to unmanned plane installs setting; Described weight sensor is arranged on the center of gravity place of unmanned plane.
Throwing umbrella ejector described in technique scheme is rocket type booster.
After adopting technique scheme, the utility model has following positive effect:
(1) the utility model detects the state of unmanned plane by sensor, judge whether to need to open landing system function, mouth and the screw propeller of microcontrol processor are closed down button and are connected, when sensor detects exception, send shutoff instruction immediately and close down button to screw propeller, open landing system umbrella cabin simultaneously, trigger and throw umbrella ejector, landing system can be launched under screw propeller prerequisite is first closed down in reliable realization, thus ensure the safe and reliable use of landing system.
(2) the utility model is by reading instantaneous acceleration, cireular frequency, after filtering, Attitude Calculation and data fusion, judge whether unmanned plane is in dangerous fall condition, automatically open landing system, avoid to greatest extent because artificial manipulation error or airborne power system fault cause aircraft to crash.
(3) simple, with low cost, lightweight, the compact of the utility model structure, there is higher response sensitivity, be adapted at using in small aircraft, and the safety of existing many rotor wing unmanned aerial vehicles can be improved.
Accompanying drawing explanation
In order to make content of the present utility model more easily be clearly understood, below according to specific embodiment also by reference to the accompanying drawings, the utility model is described in further detail, wherein
Fig. 1 is structural representation of the present utility model;
Attached number in the figure is: parachute 1, control unit 2, throw umbrella ejector 3, microcontrol processor 4, sensor 5, wireless communication line 6, fly control motor circuit 7, land self-locking device 8, weight sensor 9, snap close 10, screw propeller and close down button 11, ground receiving station 12, geomagnetic sensor 13, three-axis gyroscope 14.
Detailed description of the invention
(embodiment 1)
See Fig. 1, the utility model has and is arranged on parachute 1 in the umbrella cabin of unmanned plane and control unit 2; Parachute 1 is connected with the one end of throwing umbrella ejector 3; The other end throwing umbrella ejector 3 is fixed on umbrella bilge portion control unit 2 and comprises microcontrol processor 4, sensor 5, wireless communication line 6, flies control motor circuit 7 and the self-locking device 8 that lands; The mouth of sensor 5 is connected with the input end of microcontrol processor 4; The mouth of microcontrol processor 4 is connected with the snap close 10 throwing umbrella ejector 3, and the mouth of microcontrol processor 4 and screw propeller are closed down button 11 and be connected; Wireless communication line 6 is connected with ground receiving station 12 Wireless remote control; Fly control motor circuit 7 to be connected with microcontrol processor 4 intercommunication; The self-locking device 8 that lands is connected with microcontrol processor 4 intercommunication.Throwing umbrella ejector 3 is rocket type booster, throws in umbrella ejector 3 and has cartridge.
Wherein, sensor 5 comprises the geomagnetic sensor 13, three-axis gyroscope 14 and the weight sensor 9 that are all electrically connected with microcontrol processor 4; Geomagnetic sensor 13 is parallel to fuselage bottom and installs setting; The course axle that three-axis gyroscope 14 is parallel to unmanned plane installs setting; Weight sensor 9 is arranged on the center of gravity place of unmanned plane.
Above-described specific embodiment; the purpose of this utility model, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any amendment made, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (3)
1. a unmanned plane landing system, has and is arranged on parachute (1) in the umbrella cabin of unmanned plane and control unit (2); Described parachute (1) is connected with the one end of throwing umbrella ejector (3); The other end of described throwing umbrella ejector (3) is fixed on umbrella bilge portion; It is characterized in that: described control unit (2) comprises microcontrol processor (4), sensor (5), wireless communication line (6), flies control motor circuit (7) and the self-locking device (8) that lands; The mouth of described sensor (5) is connected with the input end of microcontrol processor (4); The mouth of described microcontrol processor (4) is connected with the snap close (10) throwing umbrella ejector (3), and the mouth of microcontrol processor (4) and screw propeller are closed down button (11) and be connected; Described wireless communication line (6) is connected with ground receiving station (12) Wireless remote control; Described fly control motor circuit (7) be connected with microcontrol processor (4) intercommunication; The described self-locking device (8) that lands is connected with microcontrol processor (4) intercommunication.
2. unmanned plane landing system according to claim 1, is characterized in that: described sensor (5) comprises the geomagnetic sensor (13), three-axis gyroscope (14) and the weight sensor (9) that are all electrically connected with microcontrol processor (4); Described geomagnetic sensor (13) is parallel to fuselage bottom and installs setting; The course axle that described three-axis gyroscope (14) is parallel to unmanned plane installs setting; Described weight sensor (9) is arranged on the center of gravity place of unmanned plane.
3. unmanned plane landing system according to claim 2, is characterized in that: described throwing umbrella ejector (3) is rocket type booster.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520583070.4U CN204998779U (en) | 2015-08-06 | 2015-08-06 | Descending system for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520583070.4U CN204998779U (en) | 2015-08-06 | 2015-08-06 | Descending system for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204998779U true CN204998779U (en) | 2016-01-27 |
Family
ID=55155680
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520583070.4U Expired - Fee Related CN204998779U (en) | 2015-08-06 | 2015-08-06 | Descending system for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204998779U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108502161A (en) * | 2018-06-19 | 2018-09-07 | 南京森林警察学院 | A kind of anti-air crash unmanned plane of more rotors of energy autonomous intelligence pop-up parachute |
| WO2022261864A1 (en) * | 2021-06-16 | 2022-12-22 | 深圳市大疆创新科技有限公司 | Control method and apparatus for unmanned aerial vehicle system, and unmanned aerial vehicle system and storage medium |
-
2015
- 2015-08-06 CN CN201520583070.4U patent/CN204998779U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108502161A (en) * | 2018-06-19 | 2018-09-07 | 南京森林警察学院 | A kind of anti-air crash unmanned plane of more rotors of energy autonomous intelligence pop-up parachute |
| WO2022261864A1 (en) * | 2021-06-16 | 2022-12-22 | 深圳市大疆创新科技有限公司 | Control method and apparatus for unmanned aerial vehicle system, and unmanned aerial vehicle system and storage medium |
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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: 20160127 Termination date: 20180806 |