CN205707374U - A kind of unmanned plane air crash protection device - Google Patents
A kind of unmanned plane air crash protection device Download PDFInfo
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- CN205707374U CN205707374U CN201620333961.9U CN201620333961U CN205707374U CN 205707374 U CN205707374 U CN 205707374U CN 201620333961 U CN201620333961 U CN 201620333961U CN 205707374 U CN205707374 U CN 205707374U
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- unmanned plane
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Abstract
The utility model discloses a kind of unmanned plane air crash protection device; relate to unmanned air vehicle technique field; solve that existing unmanned plane air crash protection device weight is big, parachute opening ways complicated, air crash judge inaccurate and structure design the unreasonable unmanned plane caused under out of control, stall condition can not low speed tenesmus, the technical problem of minimizing causality loss.It include for detect unmanned plane the acceleration of vertical downward direction and flight angle with judge unmanned plane whether be in fall condition induction trigger device, for reduce unmanned plane fall speed tenesmus protection device, for manually starting the standby remote control trigger device of tenesmus protection device and providing induction trigger device, tenesmus protection device and the supply unit of standby remote control trigger installation's power source.This utility model simple in construction, lightweight, air crash accuracy of judgement, split-type design, production cost is low, can use different release devices according to the unmanned plane of different size, produce difference and bear the protection device of specification.
Description
Technical field
This utility model relates to unmanned air vehicle technique field, is specifically related to a kind of unmanned plane air crash protection.
Background technology
Intelligent hardware high speed development at present, the application of unmanned plane gets more and more, many rotor wing unmanned aerial vehicles popularity rate is more and more higher, but but bring a series of safety problem, the air crash situation that such as unmanned plane causes due to misoperation or program crashing occurs often, and the flying height of current most of unmanned plane is generally more than 100 meters, falls if out of control in high-altitude, not only unmanned plane can be badly damaged, is also easy to cause security incident at city artificial abortion band thick and fast.In flight course, due to objective fortuitous event or fly hands operational error and be easily caused unmanned plane and fall, when unmanned plane falls rapidly from high-altitude, factor due to gravity, one egg all can cause mortal injury from 30th floors freely falling bodies, therefore the unmanned plane of several kilograms of weighing then can cause bigger injury from the pendant of hundreds of meter of high-altitude, and when falling, unmanned plane collides with other objects unavoidably, even if the object near the district that force-lands also can be caused extensive damage even to cause casualties by slight collision.
Existing all kinds of unmanned planes tenesmus protection device there is also a lot of problem, such as, by the way of reinforcing unmanned aerial vehicle body and be crashproof, fuselage is the firmest, but shock still can be brought ground staff or the injury of article；Unmanned plane is mainly based on many rotors type such as at present; but most of six rotors and following many rotors type loading capacity are limited; be usually used in taking photo by plane, the light-duty unmanned plane (below lifting capacity 1KG) of terrain detection etc. is while self usual carry camera, image transmission system; continue to install additional the protection device into the stronger unmanned aerial vehicle design of lifting capacity, it may appear that load-carrying over loading and the most inharmonic problem of moulding；The parachute opening ways of such as unmanned plane protection device is complex, opens fault rate and can increase；By Attitude Calculation, such as unmanned plane protection device only judges that the situation of erroneous judgement easily occurs in unmanned plane fall condition, cause parachute to open by mistake；If such as being buffered by large-scale parachute within 15 meters of height, parachute struts and also results in unmanned plane not in time and landed before not fully opening parachute, and the height of tens of meters still can make unmanned plane crash；It addition, existing unmanned plane protection device designs for integral type, easily affect the gravity balance of unmanned plane.
Utility model content
The technical problems to be solved in the utility model; it is to provide a kind of unmanned plane air crash protection device; overcome that existing unmanned plane air crash protection device weight is big, parachute opening ways complicated, air crash judge inaccurate and structure design the unreasonable unmanned plane caused under out of control, stall condition can not low speed tenesmus, the deficiency of minimizing causality loss.
This utility model solves its technical problem and be the technical scheme is that a kind of unmanned plane air crash protection device, including for detect unmanned plane the acceleration of vertical downward direction and flight angle with judge unmanned plane whether be in fall condition induction trigger device, for reduce unmanned plane fall speed tenesmus protection device, for manually starting standby remote control trigger device and offer induction trigger device, the protection device that drops and the supply unit of standby remote control trigger installation's power source of tenesmus protection device；Induction trigger device is connected with tenesmus protection device；Standby remote control trigger device is connected with tenesmus protection device；Supply unit is connected with induction trigger device, tenesmus protection device and standby remote control trigger device.
Further, described induction trigger device includes acceleration transducer, gyro sensor and single-chip microcomputer.
Further, described tenesmus protection device includes parachute and parachute release device.
Further, described parachute includes main chute and secondary umbrella, first opens secondary umbrella, then pulled open by main chute by secondary umbrella during described parachute release device release parachute.
Further, described parachute uses ultralight fibrous material to make.
Further, described standby remote control trigger device includes ground remote control device and airborne receptor.
Further, described supply unit designs for Split cell box, realizes different model battery by replacing battery case and powers.
Further, described induction trigger device, tenesmus protection device, standby remote control trigger device and supply unit are independent design, can be arranged on separately or in combination on unmanned plane.
The beneficial effects of the utility model are: unmanned plane is detected at acceleration and the flight angle of vertical downward direction by this utility model by acceleration transducer and gyro sensor, and the data that surveyed data are default with single-chip microcomputer are compared, judge whether unmanned plane is in tenesmus state, method simple practical, step simplify, and greatly reduce the probability that in judge process, mistake occurs；First open secondary umbrella, then the mode pulled open by main chute by secondary umbrella during parachute release device release parachute, simplify parachute opening process, be suitable for low latitude unmanned plane air crash protection；The parachute using ultralight fibrous material to make, alleviates the weight of parachute；Induction trigger device, tenesmus protection device, standby remote control trigger device and supply unit are independent design, can be arranged on separately or in combination on unmanned plane, solve unmanned plane and cause the unbalance technical problem of center of gravity owing to increasing integral type air crash protection device.This utility model simple in construction, lightweight, production cost is relatively low; the device of hundreds of units can largely protect the unmanned plane of unit the most up to ten thousand; and different release devices can be used according to the unmanned plane of different size size, produce difference and bear the protection device of specification.
Accompanying drawing explanation
Fig. 1 is the structural representation of this utility model embodiment.
Fig. 2 is this utility model embodiment scheme of installation.
Fig. 3 is this utility model embodiment parachute construction schematic diagram.
Fig. 4 is this utility model embodiment microrocket delivery mode structural representation.
Fig. 5 is this utility model embodiment mechanical ejection delivery mode structural representation.
Detailed description of the invention
Below in conjunction with drawings and Examples, the technical scheme in this utility model is clearly and completely described.
Embodiment:
As depicted in figs. 1 and 2; a kind of unmanned plane air crash protection device, including for detect unmanned plane the acceleration of vertical downward direction and flight angle with judge unmanned plane whether be in fall condition induction trigger device, for reduce unmanned plane fall speed tenesmus protection device, for manually starting standby remote control trigger device and offer induction trigger device, the protection device that drops and the supply unit of standby remote control trigger installation's power source of tenesmus protection device；Induction trigger device is connected with tenesmus protection device；Standby remote control trigger device is connected with tenesmus protection device；Supply unit is connected with induction trigger device, tenesmus protection device and standby remote control trigger device.
Unmanned plane air crash protection device is divided into two parts to install, and one in front and one in back places, and induction trigger device, standby remote control trigger device and supply unit are a part, are placed on head；Tenesmus protection device is a part, is placed on tail, it is ensured that gravity balance before and after unmanned plane.
Induction trigger device includes acceleration transducer, gyro sensor and single-chip microcomputer.Single-chip microcomputer can use stm32,51, PIC, AVR, Freescale, Msp, Raspberry Pi etc..
As it is shown on figure 3, tenesmus protection device includes parachute and parachute release device, parachute uses ultralight fibrous material to make, including main chute and secondary umbrella.
Supply unit uses Split cell box design, can realize using the battery of different model to power by changing battery case.
Acceleration transducer and gyro sensor send the data such as current acceleration, flight angle in real time to single-chip microcomputer, when acceleration information is more than the maximum set, single-chip microcomputer is judged as that unmanned plane is out of control, release signal is sent immediately to parachute release device, parachute release device discharges parachute after receiving release signal immediately, it is first turned on secondary umbrella during release, then by secondary umbrella, main chute is pulled open.
Parachute can be discharged by multiple triggering mode, depending on the unmanned plane of different size, the parachute release device of different triggering mode correspondence different structures, specifically there is following two structure: a, such as Fig. 4, microrocket delivery mode structural representation, after parachute release device receives release signal, the rocket launcher equipped with a small amount of safety black powder is lighted by ignition, quickly release a parachute when rocket launcher is launched in the way of reversely traction parachute secondary umbrella, parachute main chute is pulled open again, it is achieved parachute discharges by parachute pair umbrella；B is as it is shown in figure 5, mechanical ejection delivery mode structural representation, after parachute release device receives release signal, electronic trigger is triggered, being disconnected by the sway chain of fixing spring top, spring is released, by spring rapidly parachute is ejected release by the way of reversely launching.
Standby remote control goes out transmitting apparatus and includes ground remote control device and airborne receptor, and the most airborne receptor includes a reception antenna, and antenna band uses 2.4GHz or 5GHz to reach best anti-interference and laser propagation effect.When needs artificial forced-triggered tenesmus protection device, can launch signal by ground remote control device to airborne receptor, airborne receptor is connected with parachute release device, will ignore the release signal of induction trigger device, and discharge parachute by force.
Embodiments described above is merely to illustrate technological thought of the present utility model and feature, its object is to make those skilled in the art will appreciate that content of the present utility model and implement according to this, only can not limit the scope of the claims of the present utility model with present embodiment, the most all equal changes made according to the spirit disclosed in this utility model or modification, still fall in the scope of the claims of the present utility model.
Claims (8)
1. a unmanned plane air crash protection device, including for detect unmanned plane the acceleration of vertical downward direction and flight angle with judge unmanned plane whether be in fall condition induction trigger device, for reduce unmanned plane fall speed tenesmus protection device, for manually starting the standby remote control trigger device of tenesmus protection device and providing induction trigger device, tenesmus protection device and the supply unit of standby remote control trigger installation's power source；Induction trigger device is connected with tenesmus protection device；Standby remote control trigger device is connected with tenesmus protection device；Supply unit is connected with induction trigger device, tenesmus protection device and standby remote control trigger device.
Unmanned plane air crash protection device the most according to claim 1, it is characterised in that described induction trigger device includes acceleration transducer, gyro sensor and single-chip microcomputer.
Unmanned plane air crash protection device the most according to claim 1, it is characterised in that described tenesmus protection device includes parachute and parachute release device.
Unmanned plane air crash protection device the most according to claim 3, it is characterised in that described parachute includes main chute and secondary umbrella, first opens secondary umbrella, then pulled open by main chute by secondary umbrella during described parachute release device release parachute.
5. according to the unmanned plane air crash protection device according to any one of claim 3 or 4, it is characterised in that described parachute uses ultralight fibrous material to make.
Unmanned plane air crash protection device the most according to claim 1, it is characterised in that described standby remote control goes out transmitting apparatus and includes ground remote control device and airborne receptor.
Unmanned plane air crash protection device the most according to claim 1, it is characterised in that described supply unit designs for Split cell box, the battery that can realize different model by changing battery case is powered.
8. according to claim 1-4, unmanned plane air crash protection device according to any one of 6,7; it is characterized in that; described induction trigger device, tenesmus protection device, standby remote control trigger device and supply unit are independent design, can be arranged on separately or in combination on unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201620333961.9U CN205707374U (en) | 2016-04-20 | 2016-04-20 | A kind of unmanned plane air crash protection device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620333961.9U CN205707374U (en) | 2016-04-20 | 2016-04-20 | A kind of unmanned plane air crash protection device |
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| CN205707374U true CN205707374U (en) | 2016-11-23 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106598038A (en) * | 2017-02-14 | 2017-04-26 | 广西师范大学 | Fixed-wing unmanned aerial vehicle disaster minimization control device and method thereof |
| CN106681338A (en) * | 2017-01-04 | 2017-05-17 | 四川克瑞斯航空科技有限公司 | Unmanned plane landing protection system |
| CN107244420A (en) * | 2017-06-26 | 2017-10-13 | 深圳市雷凌广通技术研发有限公司 | It is a kind of that there is the resistance to of self-protection to fall type Intelligent unattended machine |
| CN107804467A (en) * | 2017-11-22 | 2018-03-16 | 广西电网有限责任公司贺州供电局 | UAV flight's parachute assembly |
| TWI621566B (en) * | 2017-01-24 | 2018-04-21 | Drone anti-drop protection device, drone device and remote monitoring device for drone | |
| WO2019139073A1 (en) * | 2018-01-11 | 2019-07-18 | ミネベアミツミ株式会社 | Flying device |
| CN110979647A (en) * | 2019-12-24 | 2020-04-10 | 广东电网有限责任公司 | Air fault protection device and method suitable for multi-rotor unmanned aerial vehicle |
| CN111164014A (en) * | 2017-10-16 | 2020-05-15 | 日本化药株式会社 | Fall detection device, method for detecting aircraft fall, parachute or paraglider deployment device, and airbag device |
| CN113911371A (en) * | 2021-10-14 | 2022-01-11 | 贵州电网有限责任公司 | Unmanned aerial vehicle battery increase-volume anti-falling system |
| CN116280230A (en) * | 2023-03-17 | 2023-06-23 | 昆山亿飞航空智能科技有限公司 | Continuous energy protection device for power output interruption of unmanned aerial vehicle |
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2016
- 2016-04-20 CN CN201620333961.9U patent/CN205707374U/en not_active Expired - Fee Related
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106681338A (en) * | 2017-01-04 | 2017-05-17 | 四川克瑞斯航空科技有限公司 | Unmanned plane landing protection system |
| TWI621566B (en) * | 2017-01-24 | 2018-04-21 | Drone anti-drop protection device, drone device and remote monitoring device for drone | |
| CN106598038B (en) * | 2017-02-14 | 2023-08-29 | 广西师范大学 | Disaster minimization control device and method for fixed wing unmanned aerial vehicle |
| CN106598038A (en) * | 2017-02-14 | 2017-04-26 | 广西师范大学 | Fixed-wing unmanned aerial vehicle disaster minimization control device and method thereof |
| CN107244420B (en) * | 2017-06-26 | 2019-09-06 | 深圳市雷凌广通技术研发有限公司 | A kind of resistance to self-protection falls type Intelligent unattended machine |
| CN107244420A (en) * | 2017-06-26 | 2017-10-13 | 深圳市雷凌广通技术研发有限公司 | It is a kind of that there is the resistance to of self-protection to fall type Intelligent unattended machine |
| CN111164014A (en) * | 2017-10-16 | 2020-05-15 | 日本化药株式会社 | Fall detection device, method for detecting aircraft fall, parachute or paraglider deployment device, and airbag device |
| CN111164014B (en) * | 2017-10-16 | 2023-10-31 | 日本化药株式会社 | Fall detection device, method for detecting a fall of an aircraft, deployment device for a parachute or paraglider, and airbag device |
| CN107804467A (en) * | 2017-11-22 | 2018-03-16 | 广西电网有限责任公司贺州供电局 | UAV flight's parachute assembly |
| WO2019139073A1 (en) * | 2018-01-11 | 2019-07-18 | ミネベアミツミ株式会社 | Flying device |
| CN111587209A (en) * | 2018-01-11 | 2020-08-25 | 美蓓亚三美株式会社 | Flying device |
| JPWO2019139073A1 (en) * | 2018-01-11 | 2020-12-24 | ミネベアミツミ株式会社 | Flight equipment |
| JP7159219B2 (en) | 2018-01-11 | 2022-10-24 | ミネベアミツミ株式会社 | flight device |
| US11745873B2 (en) | 2018-01-11 | 2023-09-05 | Minebea Mitsumi Inc. | Flying apparatus |
| CN111587209B (en) * | 2018-01-11 | 2024-04-05 | 美蓓亚三美株式会社 | Flying device |
| CN110979647A (en) * | 2019-12-24 | 2020-04-10 | 广东电网有限责任公司 | Air fault protection device and method suitable for multi-rotor unmanned aerial vehicle |
| CN113911371A (en) * | 2021-10-14 | 2022-01-11 | 贵州电网有限责任公司 | Unmanned aerial vehicle battery increase-volume anti-falling system |
| CN116280230A (en) * | 2023-03-17 | 2023-06-23 | 昆山亿飞航空智能科技有限公司 | Continuous energy protection device for power output interruption of unmanned aerial vehicle |
| CN116280230B (en) * | 2023-03-17 | 2024-02-23 | 昆山亿飞航空智能科技有限公司 | Continuous energy protection device for power output interruption of unmanned aerial vehicle |
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Legal Events
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| 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: 20161123 Termination date: 20170420 |