CN101450714A

CN101450714A - Jet type helicopters

Info

Publication number: CN101450714A
Application number: CNA200710050694XA
Authority: CN
Inventors: 陈昌志
Original assignee: Individual
Current assignee: Individual
Priority date: 2007-12-05
Filing date: 2007-12-05
Publication date: 2009-06-10

Abstract

The invention relates to manufacture of airplanes and flying use, taking off and landing modes of the airplanes. Excellent performance of a modern jet plane capable of flying supersonically and convenient taking off and landing of a helicopter are perfectly integrated on a jet helicopter. Wings and a motor of the jet helicopter are movably arranged and can be rotatably adjusted, a hydraulic control unit rotates the wings (3) and the motor (2) simultaneously when the airplane takes off or lands; and the change of the jet direction of the motor can change the taking off and landing mode of the airplane. Another mode is to arrange the motor on an airplane body and operate, control and rotate the motor by a hydraulic unit. Both modes can make the airplane take off and land vertically. The technique applied can design and produce various jet helicopters to serve national defense and human society.

Description

Jet type helicopters

Technical field:

The manufacturing of the present invention and aircraft and the flight of aircraft are used, the landing modes of taking off is relevant.

Background technology:

Modern jet plane is taking off, is all be unableing to do without special-purpose airport and runway when landing, and makes the range of use of aircraft, function greatly limited, can't give full play to the effect of jet plane.And long wing has taken very wide space, causes aircraft flight and parks extremely inconvenient.The airport floor area is big in addition, and construction cost is very high.In case outbreak of war, for capturing " mastery of the air ", airport and runway are the strategic demolition targets of standing in the breach.This class aircraft has been arranged, and it is just extremely difficult that the enemy will capture " mastery of the air ".Though the military type helicopter floor area is few, landing is convenient, and flying speed is slower, is shot down easily, so two class aircrafts cut both ways.The present invention has overcome two class aircraft drawbacks, and the advantage of jet plane and autogyro is rolled into one, and can produce comparatively ideal dual-use aircraft according to different purposes, has great market development application prospect.

Summary of the invention:

The present invention seeks to change the traditional maneuverability pattern of existing jet plane when landing, flight, overcome existing jet plane all be unable to do without special-purpose airport and runway when landing present situation, with the supersonic flight speed of modern jet plane and the convenient landing perfect adaptation of autogyro, produce more advanced, safe than existing type, aircraft is Defence business and human society service easily.

The present invention is achieved in that

The principle of jet type helicopters is with on the wing or the jet engine of directly installing on body, control to adjust through hydraulic control unit, make its can clockwise direction level 90 degree (or more wide-angle) rotation, allow the jet engine air nozzle vertically downward, as among Fig. 12, among Fig. 55, among Fig. 8 shown in 2.Because changed jet direction behind about 90 degree of engine rotation, according to aerodynamic principle, the lift vertically upward that produces when driving engine is jet is greater than aircraft gravity vertically downward, aircraft just can parked standing start.After aircraft rises to suitable flying height, to handle the modulated pressure device and make driving engine rotate about 90 degree to anticlockwise direction, air nozzle slightly can normally fly forward backward in horizontal direction.When need land in flight arrival destination, at this moment the preceding and ground-surface height of the aircraft landing of need controlling well, the size of flying speed and engine throttle, operating hydraulically operated control setup when reducing height, the state of rotary engine direction when taking off slowly, the air resistance that utilizes wing to revolve to turn 90 degrees the back to produce is controlled the inertia that aircraft moves ahead, when closing on the correct position in the landing target sky, the throttle of control driving engine, reduce the jet amount of driving engine, make the gravity of the lift of the jet generation of driving engine less than aircraft, the mode of controlling aircraft gravity by the size of regulating the jet generation lift of driving engine makes slowly safe falling of aircraft.

Device driving engine aircraft VTOL function principle is on the wing:

On wing, install driving engine, the straight lifting of aircraft must be joined with wing together rotate about about 90 degree, make the driving engine air nozzle vertically downward, change the landing mode of aircraft by the jet direction that changes jet engine.Many engine rotation principle assumption diagrams being arranged on the wing shown in Fig. 3,4, is example explanation rotational structure figure and principle with Fig. 3.1 is the wing main truss among the figure, driving engine 6 is housed above, the 2nd, body main piece and draw-in groove, the 3rd, be equiped with a disk that can rotate, draw-in groove blocks disk, but certain appropriate clearance is arranged, make disk come back rotation about becoming in the draw-in groove, 7 and 8 is bearings, the 10th, and live spindle, gear 9 is housed above, being fitted to each other of gear ratch 5 by hydraulic actuator, operating hydraulically operated driving device during use, the flow increase and decrease of operation control presssure oil, change the piston motion direction of hydraulic efficiency gear, gear ratch 5 is moved forwards, backwards, and driven gear 9 rotates forward or backward, thereby wing and driving engine are rotated simultaneously, reach and make driving engine and the jet direction of driving engine utilize such rotation can also regulate the flying height of aircraft by driving the arbitrarily purpose of control and regulation of requirement.The power of wing and engine rotation all comes from hydraulic actuator, and the principle of hydraulic actuator is shown in Figure 14,15.

Driving engine directly is installed in the body VTOL function principle of boarding a plane:

Groundwork is identical with the above, as shown in Figure 9, driving engine 1 is housed on body, the 2nd, draw-in groove, rotary disk 3 is blocked, 6 and 7 is bearings, gear 8 is housed on the main shaft 9, by with the gear ratch 10 of hydraulic actuator, 11 with being fitted to each other of gear 8 at one, gear ratch 10 when hydraulic actuator, 11 processes are handled the pressure oil flow makes the piston of hydraulic actuator move as fore-and-aft direction, the mobile forward or backward gear 9 that drives on the main shaft of gear ratch of hydraulic actuator is moved forward or backward, and (hydraulic efficiency pressure system is handled principle and is seen Figure 14,15) thus the direction that driving engine is wished by the operator do rotation and control takeoff and landing mode and flying height.

Install driving engine on the wing, make the principle that the control and regulation driving engine is done the left and right directions rotation with hydraulic efficiency gear:

As shown in figure 13.Among the figure the 1, the 2nd, the gear 4 on hydraulic efficiency gear gear ratch and the main shaft 3 is assembled together, the 6th, axle journal, axle journal have the semi-circular snap ring 7 of two builds, and whole gravity of driving engine are all passed to snap ring by axle journal, by snap ring gravity is passed to wing main truss 8,9th, bearing again.When operating hydraulically operated device makes

gear ratch

1,2 works mobile forward or backward, can do to move forward or backward by driven gear 4, reach the control and regulation driving engine 10 works purpose of rotation to the left or to the right.Utilize aerodynamic principle, the rotation to the left or to the right of driving engine do can fast be adjusted aircraft and turn to, and makes aircraft turn to more fast and flexible.This mode is applicable to military fight bombing aircraft, multi-role fighters, military transportation airplane, electronics early warning plane etc. very much.

The present invention is a creationary change to flight regulative mode, the landing mode of aircraft industry and aircraft, has very big commonality, practicality.The distinguishing feature and the advantage of this type aircraft are: flying speed is fast, the energy vertical takeoff and landing, and also available rotor blade or driving engine are regulated flying method.This class aircraft range is far away, refuels to ground, weapons and ammunitions are easy to, can both this military aircraft of landing on relatively large warship such as the guided missile armed destroyer deck.The control and regulation of takeoff and landing, flying method all very flexibly, safety, convenience, it is easy to manufacture simultaneously, cost is lower.Wing is very short, and it is little to account for parking space, and a blimp only needs just can park with the level land of 100 to 200 square meters, and can greatly save airport space and construction cost parking standing start or landing.

This technological invention can apply to military, the civilian jet type helicopters of large, medium and small type of all kinds of different purposes of Development and Production.Large, medium and small type jet type helicopters can be widely used in public affair or tourism, so Applicable scope of the present invention is extremely wide, has the great prospect of marketing and economic value.

Description of drawings:

Fig. 1 is that the large and medium-sized dipping structure of taking off is arranged scheme drawing.1 operator's compartment, 2 driving engines, 3 wings, 4 S. A.s, 5 bodies, 6 tail vanes, 7 empennages, 8 alighting gears among the figure

Fig. 2 is that wing and driving engine are provided with figure (facing).1 wing, 2 tail vanes, 3 empennages, 4 driving engines, 5 bodies, 6 operator'ies compartment among the figure.

Fig. 3 is rotor blade (containing a driving engine) structural plan.。1 cell 2 disk draw-in grooves, 3 rotating circular disk 4 body frameworks, 5 hydraulic actuator axles and rack 6

driving engines

7,8 bearings 9 live spindle gears 10 main shafts among the figure.

Fig. 4 is rotor blade (containing a driving engine) structural arrangement enlarged drawing (part).1 wing main truss 2 wing rotating circular disks, 3 bearing 4 body main trusss, 5,6 hydraulic actuator axles and rack 7 bearings 8 reaction gears 9 main shafts among the figure.

Fig. 5 is that microminiature is taken off landing morphosis arrangement plan.1 operator's compartment, 2 bodies, 3 tail vanes, 4 empennages, 5 driving engines, 6 wings, 7 alighting gears among the figure.

Fig. 6 is microminiature flight status figure.1 operator's compartment, 2 bodies, 3 tail vanes, 4 empennages, 5 wings, 6 driving engines among the figure.

Fig. 7 is microminiature aircraft rotor blade (comprising a driving engine) structural plan (part).1 wing main truss, 2 disk draw-in grooves, 3 disks, 4 body main trusss, 5 body main truss reinforcements, 6,7 bearings, 8 reaction gear 9 main shafts, 10,11 hydraulic actuator axles and rack 12 support slippers among the figure.

Fig. 8 is that the microminiature aircraft directly rotates the dipping structure arrangement plan that starts to take off separately.1 operator's compartment, 2 driving engines, 3 bodies, 4 tail vanes, 5 empennages, 6 alighting gears, 7 wings among the figure.

Fig. 9 is directly independent rotary engine structural plan.1 driving engine, 2 disk draw-in grooves, 3 disks, 4 body main trusss, 5 body main truss reinforcements, 6,7 bearings, 8 reaction gear 9 main shafts, 10,11 hydraulic actuator axles and rack 12 support slippers among the figure.

Figure 10 is draw-in groove and round tray cloth interposed structure figure.1 body main truss, 2 disk draw-in grooves, 3 disk spacer block, 4 disks, 5 main shaft 6 bearings, 7 wings or engine mountings bracket among the figure.

Figure 11 is body main truss and reinforcement structure figure.1 body main truss, 2 main body framework reinforcements among the figure

Figure 12 is that wing main truss and disk are arranged cross-sectional view.1 wing main truss, 2 bearings, 3 main shaft fabricated sections, 4 main shafts, 5 disks, 6 disk liner spares among the figure.

Figure 13 is the two-way rotary regulating structure arrangement plan of wing installation driving engine.1,2 hydraulic actuator axles and rack 3 main shafts 4 gears 5 support slippers 6 axle journals 7 semicircular ring cards 8 wing main trusss 9 bearings 10 driving engines among the figure.

Figure 14 is hydraulic actuated control system figure.1,2 live spindles and gear 3 hydraulic actuator racks 4 hydraulic actuator axles 5 hydraulic actuator pistons 6 hydraulic actuator housings 7 support slippers 8 boiler check valve 9 hydraulic control pumps 10 oil pipes 11 safety valves 12 oil pumps 13 fuel tanks among the figure.

Figure 15 is a hydraulic actuated control system enlarged drawing.1,2 live spindles and gear 3 hydraulic actuator racks 4 hydraulic actuator axles 5 hydraulic actuator pistons 6 hydraulic actuator housings 7 support slippers 8 boiler check valve 9 hydraulic control pumps 10 oil pipes 11 safety valves 12 oil pumps 13 fuel tanks among the figure.

The specific embodiment:

Embodiment 1:

Shown in Fig. 1,2,3,4, be applicable on the Development and Production wing and install driving engine, the big-and-middle-sized aircraft of various uses.

Embodiment 2:

Shown in Fig. 5,6,7, be applicable on the Development and Production wing and install driving engine, the blimp of various uses.

Embodiment 3:

Shown in Fig. 8,9, be applicable on the Development and Production body and install driving engine, the middle-size and small-size aircraft of various uses.

Embodiment 4:

Shown in Figure 13, be applicable on the Development and Production wing and install driving engine, the large, medium and small aircraft of various uses.Design and installation requires:

Embodiment

1,2 requires: 1, wing employing light material, and design is high and short as far as possible, and driving engine is disembarked body closely as far as possible, reduces the weight of wing to greatest extent.2, the position member of main shaft, wing and body set requires to possess high-intensity material and structure, shown in Fig. 4,11.

Embodiment 3 requires: the setting position of driving engine and wing will rationally be arranged.

Embodiment 4 requires: requiring has high strength material and structure, as shown in figure 13.

Claims

1, topmost wing and the driving engine of being characterised in that of jet type helicopters is movable the installation or the wing fixed installation, and driving engine is movable to be installed.Can with wing and driving engine rotates simultaneously or separately rotor blade, rotary engine separately.

2, according to claim 1, aircraft can use any type of driving engine by device, and main design apparatus uses present state-of-the-art jet engine.Maximum feature is an aircraft energy hypersonic flight, the energy vertical takeoff and landing, and landing does not need airfield runway.

3, according to claim 1, the aircraft principal character that driving engine is installed on the wing of head is wing and driving engine rotation simultaneously simultaneously can be can be used for controlling to adjust the landing mode and the flying height of aircraft.

4, according to claim 1, the aircraft of driving engine is installed on the wing of head, principal character be can be when rotor blade not rotary engine separately only, can be used for controlling to adjust turning to of aircraft.

5, according to claim 1, in the wing fixed installation, the movable aircraft of installing of driving engine, principal character is that driving engine can rotate, and is used to control to adjust the landing mode and the flying height of aircraft.

6, by manipulation and the control of hydraulic oil pump on the machine and hydraulic oil maneuver control device system to wing and engine rotation.