CN206704527U

CN206704527U - Manned electronic gyroplane with ejection parachute

Info

Publication number: CN206704527U
Application number: CN201621443906.1U
Authority: CN
Inventors: 许佑正
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-12-27
Filing date: 2016-12-27
Publication date: 2017-12-05
Anticipated expiration: 2026-12-27

Abstract

The utility model provides a kind of manned electronic gyroplane with ejection parachute, including：Electronic gyroplane, ejection controller and parachute catapult-launching gear, parachute catapult-launching gear is arranged on the top of the position of centre of gravity of electronic gyroplane and avoids the position of electronic rotor, parachute catapult-launching gear includes parachute and ejector, ejection controller can automatically or air ejector for starting, ejector are projected parachute by strength caused by compressed gas or blast in a manual fashion by user；When manned electronic gyroplane falls danger, the lapse rate of manned electronic gyroplane can be slowed down by parachute, the chance of survival of passenger is improved and reduce the infringement of electronic gyroplane.

Description

Manned electronic gyroplane with ejection parachute

Technical field

It the utility model is related to a kind of manned electronic gyroplane, particularly a kind of manned electronic rotation with ejection parachute Wing machine, when manned electronic gyroplane falls danger, the lapse rate of manned electronic gyroplane can be slowed down, improve passenger Chance of survival and reduce the infringement of electronic gyroplane.

Background technology

Due to the progress of electronic technology, combining wireless remote control, autobalance, computer control and electronic gyroplane etc. are more The electronic unmanned plane successful commercialization of item function.

Unmanned plane produces the power needed for flight using the rotor (being propeller) of electrical motor driven, because dynamic is steady Fixed and multimotor control technology is highly developed, and unmanned plane common at present uses more shaft designs, in other words, One unmanned plane would generally assemble multiple electro-motors for including rotor, although the electronic unmanned plane of most commercialization is all to make For the instrument taken pictures and photographed in the air, but the exploitation that manned vehicle is carried out based on the technology of unmanned plane turns into future Trend.

It is fixed not using the vehicles of electric energy in order to reduce the air pollution caused by the waste gas of traditional combustion engine discharge Come the trend developed, the commercialization of electric automobile, electric motor car and oily electric power hybrid vehicle, strong proof has been made； In fact, the electronic manned vehicle designed based on the technology of unmanned plane has also been succeeded in developing, electronic manned vehicle The target of commercialization is matter of time, is based only on safe consideration, electronic manned vehicle real commercialization it Before, how to ensure safe to use, be one of target that associated developer is striven for.

For manned electronic gyroplane, main danger generally includes：Two sides of functional fault and manual operation Face, because the maximum difference of manned electronic gyroplane and traditional Fixed Wing AirVehicle is, manned electronic gyroplane is to pass through The rotor (being propeller) of electrical motor driven produces the lift needed for flight, once the danger that will be fallen that runs out of steam Danger, and if because driver is paroxysmal to lose ability to act such as heart disease or syncope, can not continue to operate rotor Machine, the passenger of manned electronic gyroplane can all be produced greatly dangerous.

Utility model content

Technical problem to be solved in the utility model is to provide a kind of manned electronic rotor with ejection parachute Machine, when manned electronic gyroplane falls danger, the lapse rate of manned electronic gyroplane can be slowed down, improve passenger's Chance of survival and the infringement for reducing electronic gyroplane.

The utility model has a kind of embodiment of the manned electronic gyroplane of ejection parachute, including：One electronic rotor Machine, an ejection controller and a parachute catapult-launching gear, wherein parachute catapult-launching gear are arranged on the center of gravity position of electronic gyroplane The top put and the position of electronic rotor is avoided, parachute catapult-launching gear includes parachute and ejector, ejection controller electricity Property connection ejector and electronic gyroplane flight control system, wherein ejector controller can automatically or by user with Manual mode air ejector for starting, the ejector include a container and a gas generator, and the container has an opening upward, The bottom of the container is fixedly installed in the top of the position of centre of gravity of the manned electronic gyroplane and avoids the position of electronic rotor, The container content is provided with the gas generator, and the gas generator is electrically connected with the ejection controller, and the parachute is received after folding It is dissolved among the container and between the gas generator and the opening of the container, one end of the drawstring of the parachute is consolidated Due to a clip of the inside of the container, the gas generator can be started by the ejection controller and quickly produce gas Body, and then the parachute is projected from the opening of the container, first intervention carries the ejection controller before the ejector is started The flight control system positive closing of people's electronic gyroplane electronic rotor；Fallen danger in manned electronic gyroplane When, the lapse rate of manned electronic gyroplane can be slowed down by parachute, the chance of survival of passenger is improved and reduce electronic rotation The infringement of wing machine.

Wherein ejection controller includes an eject button, and after eject button is pressed, ejection controller first intervenes manned electricity The electronic rotor of flight control system positive closing of gyroplane is moved, then air ejector for starting projects parachute.

Wherein ejection controller includes a gyroscope, and gyroscope is to detect the horizontality of manned electronic gyroplane, really Protecting parachute can project towards the direction relatively above of manned electronic gyroplane.

Wherein ejection controller includes an accelerometer, and accelerometer is detecting the lower reduction of speed of manned electronic gyroplane Degree, and when decrease speed exceedes default threshold value, parachute is projected by ejection controller air ejector for starting.

Wherein, the opening of the container of ejector has a protecting cover, and protecting cover is that fragile structures can be when ejector be activated Gas is broken up caused by ejector.

Wherein, gas generator includes：Gunpowder type gas generator, compressed gas build gas generator and mixed gas Generator is therein any.

It will be seen that by above-mentioned technology contents, the utility model has the manned electronic gyroplane of ejection parachute, energy Enough when manned electronic gyroplane falls danger, parachute is projected by automatically or manually mode, subtracted by parachute Delay the lapse rate of manned electronic gyroplane, improve the chance of survival of passenger and reduce the infringement of electronic gyroplane.

On the embodiment that the utility model is related to and it is other the advantages of and effect, schema will be coordinated to be described as follows.

Brief description of the drawings

, below will be to embodiment or existing in order to illustrate more clearly of the embodiment of the present application or technical scheme of the prior art There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this Some embodiments described in application, for those of ordinary skill in the art, on the premise of not paying creative work, Other accompanying drawings can also be obtained according to these accompanying drawings.

Fig. 1, it is the construction front view for the manned electronic gyroplane that the utility model has ejection parachute；

Fig. 2, it is the top view of Fig. 1 embodiment construction；

Fig. 3, it is the functional block diagram for the manned electronic gyroplane that the utility model has ejection parachute；

Fig. 4, it is the local structure figure for the manned electronic gyroplane that the utility model has ejection parachute, illustrates parachute The structure profile diagram of catapult-launching gear；

Fig. 5, it is the use state diagram for the manned electronic gyroplane that the utility model has ejection parachute.

Symbol description

10 manned electronic 11 electronic rotors of gyroplane

The flight control system of 12 cabin 13

The ejection controller of 14 support frame 20

The eject button of 21 gyroscope 22

The 23 automatic ejection accelerometers of starting switch 24

The parachute of 30 parachute catapult-launching gear 31

The ejector of 311 drawstring 32

33 containers 331 are open

The gas generator of 332 clip 34

35 protecting covers

Embodiment

It is before the utility model has the construction of manned electronic gyroplane of ejection parachute referring initially to Fig. 1 and Fig. 2 View and top view.

A kind of embodiment that the utility model has the manned electronic gyroplane of ejection parachute constructs, including：Manned electricity Dynamic gyroplane 10, ejection controller 20 and parachute catapult-launching gear 30.What is illustrated in schema disclosed in the utility model is one The manned electronic gyroplane 10 of kind multiaxis, but be not limited thereto, the manned electronic gyroplane 10 that schema illustrates is used only to A kind of example of embodiment of bright the utility model technology.

Wherein parachute catapult-launching gear 30 is arranged on the top of the position of centre of gravity of manned electronic gyroplane 10 and avoids electricity The position of dynamic rotor 11, it is preferred that parachute catapult-launching gear 30 be fixedly installed to manned electronic gyroplane 10 cabin 12 or It is the overcentre of the support frame 14 of electronic rotor 11, if because the manned electronic not traditional Fixed Wing AirVehicle of gyroplane 10 has The ability of gliding, so will be fallen downwards when manned electronic gyroplane 10 runs out of steam, the utility model is by parachute bullet Injection device 30 is arranged on the top of the position of centre of gravity of manned electronic gyroplane 10 and avoids the position of electronic rotor 11, works as landing Umbrella 31 is by ejection and when opening, it becomes possible to smoothly slows down the lapse rate of manned electronic gyroplane 10, improves the life of passenger The also infringement of chance and the manned electronic gyroplane 10 of reduction.

Referring to Fig. 3, parachute catapult-launching gear 30 includes：Parachute 31 and ejector 32, ejection controller 20 electrically connect The flight control system 13 of ejector 32 and manned electronic gyroplane 10 is connect, wherein ejector controller 20 is substantially a kind of control Circuit processed, ejection controller 20 can automatically or air ejector for starting 32, ejector 32 pass through in a manual fashion by user Strength caused by compressed gas or blast projects parachute 31, and ejection controller 20 is first intervened before air ejector for starting 32 The electronic rotor 11 of the positive closing of flight control system 13 of manned electronic gyroplane 10, parachute can be avoided to penetrate 31 and gone out afterwards not The drawstring 311 of disconnected parachute 31 can be twisted by the electronic rotor 11 still in rotation.

Preferably wherein an embodiment of ejection controller 20 includes a gyroscope 21, gyroscope 21 and ejection controller 20 It is electrically connected with, gyroscope 21 is detecting the horizontality of manned electronic gyroplane 10, it is ensured that parachute 31 can be towards manned Project in the direction relatively above of electronic gyroplane 10；In fact, the manned electronic gyroplane 10 in tenesmus may be because of certain A little factors and have the situation of rolling, if just projecting parachute in the case where manned electronic gyroplane 10 is the posture on head is got a foothold 31, the direction of parachute 31 downward will be projected, so easily causing parachute 31 can not correctly open, so Before parachute 31 is either projected in a manner of automatic or manual, ejection controller 20 first pass through gyroscope 21 detect it is manned electronic The current body posture of gyroplane 10, and when it is determined that the current posture of manned electronic gyroplane 10 is correct, can just start Ejector 32 projects parachute 31, and then ensures that parachute 31 can be towards the side relatively above of manned electronic gyroplane 10 To injection, and successfully open.

On a kind of embodiment of air ejector for starting 32 in a manual fashion, wherein ejection controller 20 includes a bullet Button 22 is penetrated, eject button 22 and ejection controller 20 are electrically connected with, and after eject button 22 is pressed, ejection controller 20 is first situated between Enter the electronic rotor 11 of the positive closing of flight control system 13 of manned electronic gyroplane 10, then in manned electronic gyroplane 10 During correct set, just meeting air ejector for starting 32 projects parachute 31.

On a kind of embodiment of air ejector for starting 32 in an automated way, wherein ejection controller 20 includes one certainly Move and penetrate the accelerometer 24 of starting switch 23 and one, it is automatic to launch starting switch 23 and accelerometer 24 all and ejection controller 20 are electrically connected with, and user can utilize automatic ejection starting switch 23 to be turned on and off automatic ejecting function, launch automatically After function on, accelerometer 24 exceedes to detect the decrease speed of manned electronic gyroplane 10 in decrease speed During default threshold value, just parachute 31 can be projected by the air ejector for starting 32 of ejection controller 20；If the paroxysmal funeral of driver Ability to act such as heart disease or syncope are lost, can not continue to operate manned electronic gyroplane 10, cause manned electronic gyroplane 10 fall downwards, pass through foregoing automatic ejecting function, it is possible to automatically project parachute 31, slow down manned electronic rotor The lapse rate of machine 10, improve the chance of survival of passenger and reduce the infringement of manned electronic gyroplane 10.Similarly, in automatic shooting Go out before parachute 31, the positive closing of flight control system 13 that ejection controller 20 first intervenes manned electronic gyroplane 10 is electronic Rotor 11, then in the correct set of manned electronic gyroplane 10, just meeting air ejector for starting 32 projects parachute 31 (see figure 5)。

Referring to Fig. 4, having an embodiment of the manned electronic gyroplane of ejection parachute in the utility model, it is hit by a bullet Emitter 32 includes a container 33 and a gas generator 34, and container 33 has an opening 331 upward, and the bottom of container 33 is fixed The top of the cabin 12 of manned electronic gyroplane 10 or the support frame 14 of electronic rotor 11 is installed on, gas is equiped with container 33 Body generator 34, gas generator 34 include：Gunpowder type gas generator, compressed gas build gas generator and mixed type gas Body generator is therein any, and gas generator 34 is electrically connected with ejection controller 20, and parachute 31 is contained in appearance after folding In device 33 and between gas generator 34 and the opening 331 of container 33, one end of the drawstring 311 of parachute 31 is fixed Clip 332 in the inside of container 33, gas generator 34 can be started by ejection controller 20 and rapid gas generating, And then parachute 31 is projected from the opening 331 of container 33.

It is preferred that wherein the opening 331 of the container 33 of ejector 32 has a protecting cover 35, protecting cover 35 is a kind of fragile structures It can be broken up the gas caused by ejector 32 when ejector 32 is activated, such as form several on the surface of protecting cover 35 and split Ditch, it can be ruptured when protecting cover 35 is pushed by external force.It is preferred that protecting cover 35 should be able to stop ultraviolet, to avoid parachute 31 It is damaged for a long time by ultraviolet irradiation.

Although the utility model is disclosed as above by the above embodiments, so it is not limited to the utility model, Those skilled in the art, do not departing from spirit and scope of the present utility model, when can make a little change and retouching, therefore this The scope of patent protection of utility model must be defined depending on claims hereof institute defender.

Claims

A kind of 1. manned electronic gyroplane with ejection parachute, it is characterised in that including：One electronic gyroplane, an ejection Controller and a parachute catapult-launching gear, wherein the parachute catapult-launching gear are arranged on the upper of the position of centre of gravity of the electronic gyroplane Side and the position for avoiding electronic rotor, the parachute catapult-launching gear include a parachute and an ejector, the ejection controller Be electrically connected with the flight control system of the ejector and the electronic gyroplane, wherein the ejector controller can automatically or by User starts the ejector in a manual fashion, and the ejector includes a container and a gas generator, and the container has court On an opening, the bottom of the container is fixedly installed in the top of the position of centre of gravity of the manned electronic gyroplane and avoided electronic The position of rotor, the container content are provided with the gas generator, and the gas generator is electrically connected with the ejection controller, the landing Umbrella is contained among the container and between the gas generator and the opening of the container after folding, the drawing of the parachute A clip of the inside of the container is fixed in one end of rope, and the gas generator can be started and soon by the ejection controller Speed produces gas, and then the parachute is projected from the opening of the container, and the ejection controller is before the ejector is started First intervene the flight control system positive closing of the manned electronic gyroplane electronic rotor.
2. there is the manned electronic gyroplane of ejection parachute as claimed in claim 1, it is characterised in that the gas generator Including：Gunpowder type gas generator, compressed gas build gas generator and mixed gas generator are therein any.
3. there is the manned electronic gyroplane of ejection parachute as claimed in claim 1, it is characterised in that the ejector is somebody's turn to do The opening of container has a protecting cover, and the protecting cover is that fragile structures can be when the ejector be activated caused by the ejector Gas is broken up.
4. there is the manned electronic gyroplane of ejection parachute as claimed in claim 1, it is characterised in that include a gyro Instrument, the gyroscope are electrically connected with the ejection controller, gyroscope to detect the horizontality of manned electronic gyroplane, and When determining that the parachute can project towards the direction relatively above of the manned electronic gyroplane, can just start the ejector will The parachute projects.
5. there is the manned electronic gyroplane of ejection parachute as claimed in claim 4, it is characterised in that the ejection controller Comprising an eject button, the eject button is electrically connected with the ejection controller, after the eject button is pressed, the ejection controller The flight control system positive closing of the manned electronic gyroplane electronic rotor is first intervened, and it is determined that the manned electronic rotation After the current posture of wing machine is correct, then starts the ejector and project the parachute.
6. there is the manned electronic gyroplane of ejection parachute as claimed in claim 4, it is characterised in that the ejection controller Comprising an accelerometer, the accelerometer is electrically connected with the ejection controller, and the accelerometer is detecting manned electronic rotor The decrease speed of machine, and when the decrease speed exceedes default threshold value, the ejection controller first intervenes the manned electronic rotation The flight control system positive closing of the wing machine electronic rotor, and it is determined that the current posture of the manned electronic gyroplane is just After really, then start the ejector and project the parachute.