CN102431645A - Anti-crash one-man helicopter - Google Patents

Abstract

The invention relates to an anti-crash one-man helicopter. A supplementary restraint system (11) is arranged in a cabin (3); a longitudinal shaft (6) is penetrated out of the cabin (3) upwards, and a low-altitude parachute (1) is arranged at the upper end of the longitudinal shaft (6); a seat buffer spring (13) positioned below a seat (12) is arranged in a control cabin; the lower end of a helicopter body (9) is connected with an undercarriage (15); the lower end of the undercarriage (15) is connected with helicopter wheels (17) through a roller bracket (18); and an up-and-down buffer spring (16) is arranged between the undercarriage (15) and the roller bracket (18). As soon as an engine is stopped, the low-latitude parachute is started, namely a parachute matched with the weight of the helicopter is unfolded instantaneously, so that the helicopter can be landed slowly. The impact force of the helicopter during landing is reduced to the maximum extent by a buffer system which is formed by the seat buffer spring, a buffer component and the up-and-down buffer spring jointly.

Description

A kind of anti-crash one-man helicopter

Technical field

The present invention relates to a kind of one-man helicopter.

Background technology

The accident rate of autogyro is the highest.Existing autogyro is in case awing occur can not the on-the-spot accident that solves, the consequence that is inevitable of crashing.This is the deadly defect that pure helicopter is difficult to overcome.

Summary of the invention

Technical matters to be solved by this invention is, a kind of anti-crash one-man helicopter is provided, helicopter is passive when landing can soft landing, crash avoiding, guarantee man-machine safety, mainly be to guarantee personal security.

Technical scheme of the present invention is following:

A kind of anti-crash one-man helicopter; Comprise the body that has driving compartment and the main rotor of helicopter; The upper end of body is provided with the cabin of captiveing joint with body; In said cabin, be equipped with driving engine and with engine-drive bonded assembly change speed gear box, it is characterized in that: in described driving compartment, be provided with the individual seat, in the cabin, the place ahead of said seat is provided with safety air bag; Said change speed gear box has two power take-off shafts, and one of which is a longitudinal axis, and it two is a horizontal shaft; Wherein said longitudinal axis upwards passes said cabin and the upper end is equipped with low-altitude parachute, and said main rotor also is installed on the longitudinal axis and between said low-altitude parachute and cabin; Fan propelling unit as the direction wing also is installed on body, has power wheel on the angle of rake dynamical axis of said fan, this power wheel is in transmission connection through dynamic conveyor belt and described horizontal shaft; In driving compartment, also be provided with the seat recoil spring that is positioned at under-seat; The body lower end is connected with alighting gear, and the lower end of alighting gear is connected with wheel through rolling wheel support, and between said alighting gear and rolling wheel support, the recoil spring that rises and falls is installed.

The device that the body lower end connects alighting gear is a dampening assembly, this dampening assembly comprise that captiveing joint with alighting gear in the lower end, captives joint with body in the upper end the cannula-like orienting sleeve, be installed in the interior hydraulic piston cylinder of said orienting sleeve; The cylinder sleeve upper end of hydraulic piston cylinder is connected with the bottom of said seat, and the lower end of the piston rod of said hydraulic piston cylinder is connected with described alighting gear.

The invention has the beneficial effects as follows:

The present invention is a kind of single micro-miniature helicopter of taking, and by main rotor and fan propelling unit flying power is provided.Since below the alighting gear wheel is arranged, therefore also can be at ground run.

Above main rotor, be provided with low-altitude parachute, driving engine is in case shut down, and this low-altitude parachute starts, parachute that is complementary with aircraft weight just moment open, make helicopter be able to slowly land.

Damping, buffering system by seat recoil spring, dampening assembly and the recoil spring that rises and falls are formed has jointly reduced the impact when helicopter lands to greatest extent.

In addition, safety air bag has been protected the aircrew to greatest extent.

The present invention is also different with prior art aspect helicopter flight power, and it has been substituted the empennage of transmission by vortex fan propelling unit.This has the turbo fan of steering hardware, is not merely the power that helicopter provides front and back to fly, and has the function that the control aircraft turns to flexibly.

Description of drawings

Fig. 1 is a structural representation of the present invention.

The specific embodiment

Further specify the present invention below in conjunction with the accompanying drawing and the specific embodiment.

Like Fig. 1, the present invention includes thebody 9 that has driving compartment and themain rotor 2 of helicopter.In described driving compartment, be provided withindividual seat 12, in the cabin, the place ahead of saidseat 12 is respectively arranged withflight control system 10 andsafety air bag 11.

The upper end ofbody 9 is provided with thecabin 3 of captiveing joint with body 9.The changespeed gear box 5 that driving engine 4 is installed in saidcabin 3 and is in transmission connection with driving engine 4.Said changespeed gear box 5 has two power take-off shafts, and one of which is alongitudinal axis 6, and it two is a horizontal shaft.Wherein saidlongitudinal axis 6 upwards passes saidcabin 3 and the upper end is equipped with low-altitude parachute 1, and saidmain rotor 2 also is installed on thelongitudinal axis 6 and between said low-altitude parachute 1 and cabin 3.The opener of described low-altitude parachute 1 is installed in the saidflight control system 10, through handling this opener, opens low-altitude parachute 1 in the time of can making helicopter be in the low latitude.The actuation means of driving engine 4 is electrically connected with describedflight control system 10.

Fan propelling unit 8 as the turbo fan form of the direction wing also is installed onbody 9, has power wheel on the dynamical axis of saidfan propelling unit 8, this power wheel is in transmission connection throughdynamic conveyor belt 7 and described horizontal shaft.During driving engine 4 work, drivemain rotor 2 rotations through changespeed gear box 5 andlongitudinal axis 6 on the one hand, on the other hand through changespeed gear box 5 and 8 rotations ofdynamic conveyor belt 7 drive fan propelling units.Saidfan propelling unit 8 is electrically connected with describedflight control system 10.

In driving compartment, also be provided with theseat recoil spring 13 that is positioned at below theseat 12.

Body 9 lower ends are connected withalighting gear 15, and the lower end ofalighting gear 15 is connected withwheel 17 through rolling wheel support 18.And between said alightinggear 15 androlling wheel support 18, therecoil spring 16 that rises and falls is installed.

The device thatbody 9 lower ends connect alightinggear 15 is a dampening assembly 14.Thisdampening assembly 14 comprise that captiveing joint withalighting gear 15 in the lower end, captives joint withbody 9 in the upper end the cannula-like orienting sleeve, be installed in the hydraulic piston cylinder in the said orienting sleeve.The cylinder sleeve upper end of hydraulic piston cylinder is connected with the bottom of saidseat 12, and the lower end of the piston rod of said hydraulic piston cylinder is connected with described alightinggear 15.

In describedcabin 3, also be provided with automaticflight control system 19.

Claims (2)

1. anti-crash one-man helicopter; Comprise the body (9) that has driving compartment and the main rotor (2) of helicopter; The upper end of body (9) is provided with the cabin (3) of captiveing joint with body (9); In said cabin (3), be equipped with driving engine (4) and with the change speed gear box (5) that driving engine (4) is in transmission connection, it is characterized in that: in described driving compartment, be provided with individual seat (12), in the cabin, the place ahead of said seat (12) is provided with safety air bag (11); Said change speed gear box (5) has two power take-off shafts, and one of which is longitudinal axis (6), and it two is a horizontal shaft; Wherein said longitudinal axis (6) upwards passes said cabin (3) and the upper end is equipped with low-altitude parachute (1), and said main rotor (2) also is installed on the longitudinal axis (6) and is positioned between said low-altitude parachute (1) and cabin (3); Fan propelling unit (8) as the direction wing also is installed on body (9), has power wheel on the dynamical axis of said fan propelling unit (8), this power wheel is in transmission connection through dynamic conveyor belt (7) and described horizontal shaft; In driving compartment, also be provided with the seat recoil spring (13) that is positioned at seat (12) below; Body (9) lower end is connected with alighting gear (15), and the lower end of alighting gear (15) is connected with wheel (17) through rolling wheel support (18), and between said alighting gear (15) and rolling wheel support (18), the recoil spring that rises and falls (16) is installed.

2. anti-crash one-man helicopter as claimed in claim 1; It is characterized in that: the device that body (9) lower end connects alighting gear (15) is dampening assembly (14); This dampening assembly (14) comprise that captiveing joint with alighting gear (15) in the lower end, captives joint with body (9) in the upper end the cannula-like orienting sleeve, be installed in the hydraulic piston cylinder in the said orienting sleeve; The cylinder sleeve upper end of hydraulic piston cylinder is connected with the bottom of said seat (12), and the lower end of the piston rod of said hydraulic piston cylinder is connected with described alighting gear (15).

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