CN201220750Y

CN201220750Y - Vertically taking off and landing airplane

Info

Publication number: CN201220750Y
Application number: CNU200820081337XU
Authority: CN
Inventors: 张庆柳
Original assignee: Individual
Current assignee: Individual
Priority date: 2008-06-12
Filing date: 2008-06-12
Publication date: 2009-04-15
Anticipated expiration: 2018-06-12

Abstract

The utility model discloses a vertical take-off and landing (VTOL) plane, and aims to provide a VTOL plane which has a simple structure and easy production, and is capable of vertical take-off and landing and level flight at a high speed without additionally and greatly increasing the power of an aeroengine. The VTOL plane includes a cockpit, a plane body, the aeroengine, aerofoils, a stabilizer, a vertical tail and a control system. A rotor is mounted at the upper part of the plane body; a rotor automatic positioning device is mounted on the rotor; the rotor is connected with a rotor shaft; the rotor shaft is connected with a reducer and a rotor shaft retracting device; a rotor shaft automatic positioning device is mounted on the rotor shaft; a rotor cabin capable of being opened and closed is mounted at the top part of the plane body; the aeroengine is connected with the reducer through a transmission shaft and a clutch; and a steering vector tail pipe is mounted at the rear part of the aeroengine. When the plane vertically takes off and lands, the rotor cabin is opened, and the rotor and the rotor shaft extend out of the rotor cabin; when the plane takes a level flight, the rotor and the rotor shaft retract into the rotor cabin, and the rotor cabin is closed; therefore, the utility model mainly aims to provide the vertical take-off and landing (VTOL) plane capable of vertical take-off and landing and level flight.

Description

Vertical take-off and landing aircraft (VTOL aircraft)

Technical field

The utility model belongs to a kind of aircraft, and more particularly, it relates to a kind of vertical take-off and landing aircraft (VTOL aircraft).

Background technology

Up to the present, vertical take-off and landing aircraft (VTOL aircraft) was successively developed five major types: the mixed configuration formula of tailstock formula, the engine installation formula of verting, thrust deflexion formula, special-purpose lift engine installation formula and above-mentioned back three classes, typical case's representative is as the V-22 tiltrotor of Boeing Co., " sparrow hawk " formula deflection jet pipe mode vertical take-off and landing aircraft (VTOL aircraft) of Britain, the F-35 of american lockheed LMT uses lift fan and band to turn to the short takeoff/vertical landing aircraft of the afterburning turbofan engine of vector spray.Above-mentioned several vertical takeoff and landing, short square take off/the equal place in operation of vertical landing aircraft owing to do not need special airport and runway, make rise aspect its manoevreability in increasing war and the alerting ability effect preferably.But many great shortcomings are also arranged simultaneously, tiltrotor is because rotor diameter is big, speed can only be in 400 kilometers/hour during flat flying, " sparrow hawk " formula deflection jet pipe mode vertical take-off and landing aircraft (VTOL aircraft), owing to will realize vertical takeoff and landing, the take-off weight of aircraft can only be the 83%-85% of engine thrust, this just makes the capacity weight of aircraft be restricted greatly, the fuel load and the voyage of aircraft have been influenced, simultaneously, engine operation was at maximum rating when aircraft took off vertically, consumption of fuel is very big, limited the combat radius of aircraft, and the F-35 of american lockheed LMT development adopts lift fan and is with the short takeoff/vertical landing that turns to vector spray, because lift fan and band turn to the lift deficiency of vector spray generation so that aircraft realization vertical takeoff and landing can only very reluctantlyly change short takeoff/vertical takeoff and landing into, the maneuverability of aircraft is had a greatly reduced quality, be difficult under the engineering factor at present and will significantly increase engine power.

Summary of the invention

The utility model has overcome the deficiencies in the prior art, provide a kind of simple in structure, be easy to manufacture, can vertical takeoff and landing also can equal the vertical take-off and landing aircraft (VTOL aircraft) that flies at a high speed, in order to solve the problems of the technologies described above, the utility model is achieved through the following technical solutions, vertical take-off and landing aircraft (VTOL aircraft) of the present utility model comprises driving compartment, fuselage, aero-engine, wing, tailplane, vertical tail and aircraft control system, described vertical take-off and landing aircraft (VTOL aircraft) back is equipped with rotor, the rotor automatic positioning equipment is housed on the rotor, rotor is connected with rotor shaft, rotor shaft and retarder, the rotor shaft retractor device connects, the rotor shaft automatic positioning equipment is housed on the rotor shaft, able to turn on or off rotor cabin is equipped with at the fuselage top, aero-engine is through transmission shaft, power-transfer clutch is connected with retarder, and the aero-engine rear portion is equipped with and is turned to the vector jet pipe.

Described vertical take-off and landing aircraft (VTOL aircraft), the rotor structure of back can be the contrarotation bispin wing, and rotor shaft is the contrarotation rotor shaft.

Described vertical take-off and landing aircraft (VTOL aircraft), retarder can be connected with many aero-engine through corresponding transmission shaft, power-transfer clutch with it, and the auxiliary aviation driving engine is housed on the vertical tail.

Described vertical take-off and landing aircraft (VTOL aircraft) is equipped with propeller before its aero-engine, behind the auxiliary aviation driving engine propeller is housed.

Described vertical take-off and landing aircraft (VTOL aircraft), rotor cabin front and rear portions is equipped with the opposite rotor of hand of rotation and corresponding with it bonded assembly rotor automatic positioning equipment, rotor shaft, retarder, rotor shaft automatic positioning equipment, rotor shaft retractor device, transmission shaft, aero-engine respectively, and vertical tail is installed downwards.

The rotor structure of described vertical take-off and landing aircraft (VTOL aircraft) back is a coaxial double-rotary wing, rotor shaft is the contrarotation rotor shaft, the aero-engine front portion is connected with propeller through power-transfer clutch, transmission shaft, and the rear portion is connected with retarder through power-transfer clutch, transmission shaft, and adjustable rotor fixed link is equipped with at rear portion, fuselage top.

Owing to adopt technique scheme, the vertical take-off and landing aircraft (VTOL aircraft) beneficial effect that the utility model provides is simple and reliable for structure, the aero-engine service efficiency significantly improves, the lift that rotor produces under equal-wattage during vertical takeoff and landing is the several times of existing other form vertical take-off and landing aircraft (VTOL aircraft) even more than ten times, can realize vertical takeoff and landing easily, during revert to level flight, because in the rotor retraction rotor cabin, make it can be with the same speed normal flight of conventional airplane, must the time flying speed can meet or exceed velocity of sound, and needn't additionally significantly increase aeroengine power.

Description of drawings

Fig. 1 is first embodiment theory structure scheme drawing of the present utility model;

Fig. 2 is second embodiment theory structure scheme drawing of the present utility model;

Fig. 3 is the 3rd an embodiment theory structure scheme drawing of the present utility model;

Fig. 4 is the 4th an embodiment theory structure scheme drawing of the present utility model;

Fig. 5 is the 5th an embodiment theory structure scheme drawing of the present utility model;

Fig. 6 is the 6th an embodiment theory structure scheme drawing of the present utility model.

Among the figure: driving compartment 1 rotor cabin 2 rotor shaft, 3 rotor automatic positioning equipments, 4 rotors, 5 vertical tails, 6 tailplanes 7 turn to vector jet pipe 8 wings 9 aero-engine 10 transmission shafts 11 power-transfer clutchs 12 retarders 13 rotor shaft retractor devices 14 rotor shaft automatic positioning equipments 15 fuselages 16 auxiliary aviation driving engines 17 propeller 18 adjustable rotor fixed links 19 can turn to vertical tail 20

The specific embodiment

The utility model will be further described below in conjunction with accompanying drawing.

In Fig. 1, vertical take-off and landing aircraft (VTOL aircraft) is by driving compartment 1, fuselage 16, aero-engine 10, wing 9, tailplane 7, vertical tail 6 and control system constitute, rotor 5 is equipped with on fuselage 16 tops, rotor automatic positioning equipment 4 is housed on the rotor 5, rotor 5 is connected with rotor shaft 3, rotor shaft 3 and retarder 13, rotor shaft retractor device 14 connects, rotor shaft automatic positioning equipment 15 is housed on the rotor shaft 3, able to turn on or off rotor cabin 2 is equipped with at fuselage 16 tops, aero-engine 10 is through transmission shaft 11, power-transfer clutch 12 is connected with retarder 13, and aero-engine 10 rear portions are equipped with and are turned to vector jet pipe 8.The configuration design of aircraft is similar to the conventional airplane design substantially, and be provided with able to turn on or off rotor cabin 2 at the aircraft top, open in rotor cabin 2 during the aircraft vertical takeoff and landing, rotor shaft retractor device 14 stretches out rotor shaft 3 and the rotor 5 that is attached thereto outside the rotor cabin 2, rotor shaft 3 is telescopic spline shaft type drive mechanism among the figure, aero-engine 10 work, through transmission shaft 11, power-transfer clutch 12, retarder 13 drives rotor shaft 3 and rotates with rotor shaft 3 bonded assembly rotors 5, rotor 5 is for to be connected with rotor shaft 3 upper end branch levels symmetric offset spread, the rotary blade of two groups of symmetric offset spread of fork constitutes mutually, between corresponding two rotors rotor automatic positioning equipment 4 is housed, rotor automatic positioning equipment 4 is made of elastomeric element and limiting component, during rotor 5 rotations, because powerful centnifugal force makes 5 one-tenth X-shaped rotations of rotor greater than the convergent force of rotor automatic positioning equipment 4, produce to raising force during rotor 5 rotations, drive the aircraft vertical takeoff and landing, simultaneously aircraft is produced an antagonistic force, this antagonistic force turns to the antagonistic force balance of vector jet pipe 8 to antagonistic force opposite sense and downward jet generation by the control of stone roller spiral shell instrument, aircraft is stablized risen and advance, when aircraft is raised to certain altitude and goes to flat flying, through power-transfer clutch 12 retarder 13 and transmission shaft 11 are disconnected, turn to vector jet pipe 8 back tracks, promote aircraft and quicken flight, after retarder 13 disconnects with transmission shaft 11, rotor 5 stops the rotation, rotor 5 loses centnifugal force, rotor automatic positioning equipment 4 draws rotor 5 in automatically, rotor shaft automatic positioning equipment 15 is made of positioning element and locking member, rotor shaft automatic positioning equipment 15 is fixed on rotor 5 with rotor shaft 3 and draws the parallel position in back and rotor cabin 2 in, open rotor cabin 2 then, rotor shaft retractor device 14 is with rotor shaft 3, rotor 5 shrinks and enters in the rotor cabin 2, rotor cabin 2 is closed, aircraft enters normal putting down and flies state, and rotor shaft retractor device 14 is made of hydraulically extensible member and associated components thereof.

To be loaded on rotor 5 versions on fuselage 16 tops be coaxial double-rotary wing to vertical take-off and landing aircraft (VTOL aircraft) among Fig. 2, rotor shaft 3 is the contrarotation rotor shaft, owing to adopt the contrarotation bispin wing, the antagonistic force that rotor produces is cancelled each other, make steadily vertical takeoff and landing of aircraft, turn to this moment 8 need of vector jet pipe to turn to below and rear to provide auxiliary lifting and forward thrust for aircraft.

Among Fig. 3, retarder 13 can be connected with many aero-engine, aero-engine 10 is connected with power-transfer clutch 12, can turn to auxiliary aviation driving engine 17 is housed on the vertical tail 20, retarder 13 is through cooresponding two pairs of transmission shafts 11, power-transfer clutch 12 connects with two aero-engine 10 of parallel placement, power-transfer clutch 12 is loaded on respectively on two aero-engine 10, its vertical takeoff and landing principle of work is identical with Fig. 1, the antagonistic force that rotor 5 produces is loaded on the direction of the auxiliary aviation driving engine 17 that can turn on the vertical tail 20 with control balance and generation forward thrust by the control of stone roller spiral shell instrument, after aircraft is put down and is flown, adjustment is loaded on auxiliary aviation driving engine 17 spouts that can turn on the vertical tail 20 and produces the thrust second-mission aircraft backward and advance, but handle be loaded on the auxiliary aviation driving engine 17 that can turn on the vertical tail 20 direction also second-mission aircraft turn to.

Among Fig. 4, before 4 aero-engine 10 placed side by side propeller 18 is housed, propeller 18 is housed behind the auxiliary aviation driving engine 17, its vertical takeoff and landing, the flat principle of work that flies are identical with embodiment shown in Figure 3, rotor 5 intersects 6 rotors placing up and down by symmetry and constitutes among the figure, rotor increases rotary blade quantity as need, must increase in pairs, so that can stagger when drawing in mutually.

Among Fig. 5,2 front and back, rotor cabin of vertical take-off and landing aircraft (VTOL aircraft) are equipped with hand of rotation opposite two groups of rotors 5 and cooresponding with it rotor automatic positioning equipment 4 respectively, rotor shaft retractor device 14, retarder 13, transmission shaft 11, power-transfer clutch 12, aero-engine 10, two groups of aero-engine 10 minutes, the front is the aero-engine 10 of two parallel placements for one group, power flies before providing fwd rotor 5 vertical takeoff and landing power to reach, the back is the aero-engine 10 that separate unit is positioned over drive end unit, power flies before providing rotor 5 vertical takeoff and landing power in back to reach, front and back rotor 5 is because hand of rotation is opposite, the antagonistic force that rotor 5 produces before and after making is cancelled each other, thereby can make the steady landing of vertical take-off and landing aircraft (VTOL aircraft), because rotor 5 postposition, vertical tail 6 is installed downwards.

Among Fig. 6, rotor 5 versions that vertical take-off and landing aircraft (VTOL aircraft) is loaded on fuselage 16 tops are coaxial double-rotary wing, and rotor shaft 3 is the contrarotation rotor shaft, owing to adopt the contrarotation bispin wing, the antagonistic force that rotor produces is cancelled each other, and makes steadily vertical takeoff and landing of aircraft.Aero-engine 10 front portions are connected with propeller 18 through power-transfer clutch 12, transmission shaft 11, the rear portion is connected with retarder 13 through power-transfer clutch 12, transmission shaft 11, adjustable rotor fixed link 19 is equipped with at rear portion, fuselage 16 top, adjustable rotor fixed link 19 is packed up when the vertical take-off and landing aircraft (VTOL aircraft) vertical takeoff and landing, aircraft is flat to stretch out fixedly rotor 5 rear portions when flying, make its flat rotor 5 that do not allow when flying produce swing.

Claims

1, a kind of vertical take-off and landing aircraft (VTOL aircraft), comprise driving compartment (1), fuselage (16), aero-engine (10), wing (9), tailplane (7), vertical tail (6) and control system, it is characterized in that fuselage (16) top is equipped with rotor (5), rotor automatic positioning equipment (4) is housed on the rotor (5), rotor (5) is connected with rotor shaft (3), rotor shaft (3) and retarder (13), rotor shaft retractor device (14) connects, rotor shaft automatic positioning equipment (15) is housed on the rotor shaft (3), able to turn on or off rotor cabin (2) is equipped with at fuselage (16) top, aero-engine (10) is through transmission shaft (11), power-transfer clutch (12) is connected with retarder (13), and aero-engine (10) rear portion is equipped with and is turned to vector jet pipe (8).

2, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that rotor (5) structure is the contrarotation bispin wing, and rotor shaft (3) is the contrarotation rotor shaft.

3, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that retarder (13) can be connected with many aero-engine, and aero-engine (10) is connected with power-transfer clutch (12), can turn to auxiliary aviation driving engine (17) is housed on the vertical tail (20).

4, according to claim 1 or 3 described vertical take-off and landing aircraft (VTOL aircraft), it is characterized in that the preceding propeller (18) that is equipped with of aero-engine (10), propeller (18) is housed behind the auxiliary aviation driving engine (17).

5, according to claim 1 or 3 described vertical take-off and landing aircraft (VTOL aircraft), it is characterized in that rotor cabin (2) front and rear portions is equipped with rotor (5) and corresponding with it rotor shaft (3), rotor automatic positioning equipment (4), retarder (13), rotor shaft automatic positioning equipment (15), rotor shaft retractor device (14), transmission shaft (11), aero-engine (10) respectively, vertical tail (6) is installed downwards.

6, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 and 2, rotor (5) structure that it is characterized in that fuselage (16) top is a coaxial double-rotary wing, rotor shaft (3) is the contrarotation rotor shaft, aero-engine (10) is anterior to be connected with propeller (18) through power-transfer clutch (12), transmission shaft (11), the rear portion is connected with retarder (13) through power-transfer clutch (12), transmission shaft (11), and adjustable rotor fixed link (19) is equipped with at rear portion, fuselage (16) top.