CN102991673A

CN102991673A - New type one-man flight vehicle capable of vertically taking off and landing and with fixed wings

Info

Publication number: CN102991673A
Application number: CN2012105442540A
Authority: CN
Inventors: 刘斌
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-12-17
Filing date: 2012-12-17
Publication date: 2013-03-27

Abstract

The invention discloses a new type one-man flight vehicle capable of vertically taking off and landing and with fixed wings. The new type one-man flight vehicle comprises wings, a support frame, engines, a rotating bearing, braces, a flight control unit, a fuselage, batteries, holding arms, a solar cell panel, an escape parachute and a lifesaving air bag. The vertical taking off and landing, low-speed flight and transition towards horizontal flight can be realized by rotating the directions of the two engines, low-speed and flexible flight can be realized without the utilization of fixed wings, and also high-speed and remote flight can be realized by utilizing the fixed wings.

Description

But a kind of new-type vertical takeoff and landing fixed-wing individual lift device

Technical field

The present invention relates to a kind of individual lift device, especially a kind of fixed-wing individual lift device with vertical takeoff and landing and horizontal flight function that changes the driving engine direction.

Background technology

Freely circling in the air as bird is human dream for thousands of years.But the aircraft of existing vertical takeoff and landing has crown coaxial rotor scheme, the single rotor scheme in the crown, jet knapsack, rocket braces etc., the total advantage of these schemes is vertical takeoff and landing, but total major defect is not have fixed-wing, can't realize remote flat flying, during boat and voyage all very short, and speed is slow, flight cost is high, manipulation is complicated, poor stability.Existing light-duty individual lift device such as powered paraglider and dynamic-delta-wing aircraft etc. that can horizontal flight, speed is slow, and voyage is short, can't vertical takeoff and landing.

Be CN1203167A in China Patent No., application number is 97112823.5, name is called in the patent of " manned vertically taking off and landing flyer " and discloses a kind of manned vertically taking off and landing flyer, its shortcoming is that the relative position of chaufeur center of gravity and aircraft center of gravity is unfixing, when utilizing slide rail to slidably reciprocate the two relative center-of-gravity position of adjustment awing, the crank that causes makes whole system top-heavy easily, might cause flying upside down and hitting ground.That is to say that slide rail slip adjustment center-of-gravity position is not one and easily converges on stable control process, have larger danger, and rail structure is complicated, weight is large.

Be 200810070233.3 at application number, publication number is CN101353084A, name is called in the invention of " light aerobat capable of landing or taking-off vertically ", and application number is 200910168948.7, publication number is CN 101927825, name is called in the invention of " individual lift device " has announced two kinds of similar individual lift devices, but also vertical takeoff and landing and horizontal flight, but the state of the two conversion is to utilize the rotation of engine drive ducted fan to produce power, blow at wing and empennage and produce moment, control the conversion of vertical takeoff and landing and horizontal flight with this, this is a kind of passive type state conversion, state conversion underaction.

Be 201210261225.3 at application number, publication number is CN102785776A, name is called in the invention of " but a kind of vertical takeoff and landing fixed-wing individual lift device " and discloses a kind of individual lift device that rear engine is installed, also can be by the direction of rotation rear engine, the generation side force realizes the conversion of vertical takeoff and landing and horizontal flight, this individual lift device is when realizing vertical takeoff and landing and horizontal flight, chaufeur will be controlled the rotating speed of sustainer, main engine simultaneously, turning to of the rotating speed of rear engine and rear engine, operate very complicated, be difficult to grasp, and rear engine turns to slower, very dumb, in the situation of air-flow more complicated near the ground, be difficult to grasp balance, cause easily safety misadventure.

Summary of the invention

Defective for above-mentioned prior art existence, but the invention provides a kind of new-type vertical takeoff and landing fixed-wing individual lift device, can more flexible realization vertical takeoff and landing and the level flight condition conversion, low-latitude flying is easy to operate, adjust flexibly, stronger to complicated air-flow adaptive faculty.

In order to overcome the above problems, the technical solution adopted in the present invention is: utilize two driving engines that can rotate synchronously to realize state switch transition between vertical takeoff and landing and the horizontal flight.But a kind of new-type vertical takeoff and landing fixed-wing individual lift device comprises wing, driving engine, bracing frame, energy-storage box, holds up arm, flight controller, braces, it is characterized in that wing is fixed on the fuselage by bracing frame.Two driving engines are fixed on bracing frame two ends, and middle stationary distribution has two bearings, and the bearing outside is fixed on the fuselage, fix with bracing frame again between two driving engines, and a driving engine forward, an engine inversion is with the moment of torsion of cancelling out each other.Hold up arm to be fixedly connected on two bracing frames between the driving engine for two, hold up arm by pulling, make turn of engine, promote air to the aircraft rear, pulling Vehicle nose rotates forward, and aircraft is changed to level flight condition; When changing from horizontality to plumbness, carry out inverse process.Hold up arm swing flexibly, fast, convenient in time correction, whole stateful switchover process, one hand can operate realization.

Hold up for two two flight controllers are housed respectively on the arm, be similar to motorcycle upper controller, one is used for two engine speeds of synchro control, can adopt without spring design, makes things convenient for controller to rest on any rotational angle; Another flight controller can be designed to control on the original basis the increase of an engine speed wherein or reduce, with this left/right rotation of controlling when flight to, can adopt spring design, make and do not change wherein engine speed under the controller state of nature, also can be designed to control the rotation of vertical empennage, when realizing flying left/right rotation to, need to increase vertical empennage at afterbody this moment.

The upper and lower surface of this aircraft wing all is equipped with solar panel, and flight cost is saved in convenient charging, along with the progress of solar battery technology, and the raising of conversion efficiency, effect will be more and more obvious.Do not use solar panel to belong to equally the protection domain of this patent.

Escape parachute and life saving air bag also are installed on this aircraft, in when, in-flight emergency situation occuring when, chaufeur, escape parachute and life saving air bag can separate with other parts of aircraft, so that open the escape parachute escape, if drop on waterborne, then life saving air bag can be full of the gas ejection immediately, realizes water survival.

The present invention can realize vertical slow speed flight and horizontal high-speed flight, and control is simple, flexible, and is adaptable to complicated air-flow, has a smooth flight.This aircraft is designed to wearable, simple in structure, light for the human body characteristics.This aircraft wing adopts controlled foldover design, and during vertical flight, wing is collapsible, thereby reduces to be subject to the impact of air-flow, makes flight more stable.

Description of drawings

Fig. 1 is schematic perspective view of the present invention.

Fig. 2 is the scheme drawing of the present invention when adopting jet engine.

Indicate explanation among the figure: the 1-wing, the 2-bracing frame, the 3-bearing, the 4-driving engine, the 5-screw propeller, 6-holds up arm, 7-flight controller, 8-braces, 9-energy-storage box, 10-solar panel, 11-fuselage.

The specific embodiment

Embodiment one:

Further specify take driving engine 4 employing electrical motors as embodiment.

In accompanying drawing 1, wing 1 adopts symmetric design, take the aircraft longitudinal axis as symmetrical, after being fixed on fuselage 11 by bracing frame 2, wing 1 adopts controlled foldover design, during vertical flight, wing 1 is collapsible, thereby reduces to be subject to the impact of air-flow, makes flight more stable.Two driving engines 4 are fixed on bracing frame 2 two ends, and middle stationary distribution has two bearings 3, and bearing 3 outsides are fixed on the fuselage 11, and are fixing with bracing frame 2 again between two driving engines 4.Be separately installed with 5, one forwards of two screw propellers on two driving engines 4, a counter-rotating is with the moment of torsion of cancelling out each other.There are escape parachute and life saving air bag to be used for lifesaving on the aircraft.Flight controller 7 is installed in to be held up on the arm 6.Solar panel 10 is installed on the wing 1.Braces 8 is housed on the fuselage, and is used for the energy-storage box 9 of energy supply.

When needs flew, the aviator opened folding aircraft, the back aircraft, and fastening braces 8 will oneself be fixed on the aircraft, at this moment hold the flight controller 7 of holding up on the arm 6, starts two driving engines 4, drives screw propeller 5 rotations, realizes taking off vertically.Can hold up arm 6 and flight controller 7 to make the aircraft smooth flight by adjusting back and forth when taking off.Then chaufeur control aircraft expansion wing 1, and arm 6 is held up in pulling, controls simultaneously flight controller 7 and strengthens engine speed, and aircraft is changed to level flight condition.When changing from horizontality to plumbness, push away forward and hold up arm 6, carry out inverse process.

Embodiment two:

Further specify as an example of driving engine 4 employing jet engines example.

As shown in Figure 2, driving engine 4 is two jet engines, does not need to install screw propeller 3 on the driving engine 4, battery pack and fuel are arranged in the energy-storage box 9, in the energy-storage box 9 feed apparatus is arranged, when guaranteeing which kind of state no matter aircraft be in, fuel all can be fed on the driving engine.Other parts are with embodiment one.

The above only is the description of the preferred embodiment of the invention; should be understood that; because the finiteness of literal expression; and at the concrete structure that objectively has other; for those skilled in the art; under the prerequisite that does not break away from the principle of the invention, can also make as doing improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.

Claims

1. but new-type vertical takeoff and landing fixed-wing individual lift device, comprise wing, bracing frame, driving engine, screw propeller, bearing, braces, hold up arm, flight controller, fuselage, energy-storage box, it is characterized in that, two driving engines that are installed in aircraft top can pass through bearing rotary, affect aircraft to turn to, realization vertical slow speed flight, or transition is horizontal high-speed flight, also can convert back plumbness by turning to.

2. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 is characterized in that, a pair of arm of holding up also is housed on the aircraft, holds up arm can control two driving engines to turn to, hold up engine start control device is installed on the arm by pushing away, drawing.

3. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 and 2, it is characterized in that, a pair of holding up is equipped with respectively flight controller on the arm, one of them is used for the rotating speed of two driving engines of synchro control, the another one flight controller separately control wherein an engine speed increase or reduce, the left/right rotation when controlling flight with this to, also can increase vertical empennage at afterbody, be used for controlling the rotation of vertical empennage, when realizing flying left/right rotation to.

4. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 is characterized in that driving engine is two ones, and symmetry is installed on the bracing frame of aircraft both sides respectively, and bracing frame connects with fuselage by bearing.

5. but according to claims 1 or 4 described new-type vertical takeoff and landing fixed-wing individual lift devices, it is characterized in that driving engine can be electrical motor, jet engine, combustion engine, turbine engine, can also be other forms of driving engine, can also be jet storage tank.

6. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 is characterized in that fuselage is scalable or collapsible.

7. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 is characterized in that screw propeller is the variable-distance screw propeller.

8. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1, it is characterized in that, energy-storage box provides the energy supply of system, it can be the combination of battery pack or battery pack and fuel in the energy-storage box, battery pack can be storage battery, also can fuel cell, can also be the hybrid battery of multiple battery.

9. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1; it is characterized in that; solar panel is installed on the wing, and battery forms the associating electric power system in solar panel and the energy-storage box, does not use solar panel also to belong to this patent protection domain.

10. but new-type vertical takeoff and landing fixed-wing individual lift device according to claim 1 is characterized in that wing adopts controlled foldover design, and during vertical flight, wing is collapsible, thereby reduces to be subject to the impact of air-flow, makes flight more stable.