CN102310944A

CN102310944A - Disc type aircraft

Info

Publication number: CN102310944A
Application number: CN201110172168A
Authority: CN
Inventors: 林文强; 李清良
Original assignee: Northeastern University China
Current assignee: Northeastern University China
Priority date: 2011-06-24
Filing date: 2011-06-24
Publication date: 2012-01-11

Abstract

The invention provides a disc type aircraft, which has the advantages of small volume, simple structure, high safety and strong applicability. The aircraft comprises a control cabin, an aircraft body, a variable torque system, a rotor wing system, a transmission device, a power system and an undercarriage. The aircraft body is of a fixed frame body of the aircraft integral structure. The control cabin is arranged above the aircraft body. The variable torque system is driven by a servo motor. The servo motor is connected to a gear transmission mechanism and a variable torque hinge. The rotor wing system is connected at one side of the variable torque system. The rotor wing system is arranged on the outer edge of the aircraft body and comprises an upper paddle, a lower paddle and a propelling paddle. The outer ends of the upper paddle and the lower paddle are respectively fixed through a fixed ring. The propelling paddle is arranged at the bottom of the aircraft body and connected to a motor for driving the propelling paddle. A gear ring is arranged at the other side of the variable torque system. The gear ring is matched with the transmission device in the form of a gear. The power input shaft of the transmission device is connected with the power system. The power system is composed of a gearbox, a clutch and an engine and arranged in an aircraft body cabin. The undercarriage is fixed at the bottom of the aircraft body.

Description

Disc aircraft

Technical field

The invention belongs to the aviation aircraft technical field, particularly a kind of disc aircraft.

Background technology

Existing helicopter kind is a lot; Can be applicable to travel that view, aviation are taken pictures, geologic survey, ultra-high-tension power transmission line tour, oil field pipeline inspection, freeway management, forest fire protection cruising, poison gas are reconnoitred, drug law enforcement, accident illumination, build many aspects such as interim communication platform, emergency management and rescue, rescue; Every kind of helicopter basically all is made up of thousands of parts; Structure and complicacy thereof, processing and manufacturing are felt bad greatly, and price reaches millions of even more than one hundred million units; Relatively more expensive, popularize very difficulty; Parts are various, and the accumulation of part self and transmission device reliability will variation, causes the higher accident rate of helicopter, threatens crew's safety of life and property; Because the complexity of its structure, detection and maintenance are also very difficult when helicopter breaks down.In addition, helicopter commonly used is because numerous factors such as fuselage weight skewness must keep balance through empennage is set, and diameter of propeller is very big again, causes the helicopter activity space restricted, all can't play a role in a lot of occasions.

Summary of the invention

To the shortcomings and deficiencies of existing helicopter, the present invention provides the disc aircraft that a kind of volume is little, simple in structure, safe and applicability is strong.

For realizing above-mentioned purpose, the technical scheme that the present invention adopts is: disc aircraft comprises driving compartment, fuselage, bending moment system, rotor system, driving device, power system and alighting gear, and fuselage is as the integrally-built fixing bracket body of aircraft; Driving compartment is arranged on body upper, and the bending moment system is by driven by servomotor, and servomotor connection gear transmission device and bending moment cut with scissors; Bending moment system one side connects rotor system, and rotor system is arranged on the fuselage outer rim, comprises blade, following blade and advances oar; Last blade, following blade outer end are fixed by mounting ring respectively; Advance oar to be located at fuselage bottom and to be connected with motor it is driven, bending moment system opposite side is provided with gear ring, and gear ring cooperates with the driving device of gear forms; The power input shaft of driving device connects power system; Power system is made up of change speed gear box, power-transfer clutch and driving engine, is arranged in the fuselage compartment, and alighting gear is fixed on fuselage bottom.

Said driving compartment is made up of seat, hatch door and control panel; Hatch door is made up of the glass outer cover and the inner layer glass cover of 1/4 ball-type, and wherein the inner layer glass cover is fixed, and glass outer is covered with S. A.; The outside is provided with handle, and seat and control panel are arranged in the hatch door.

Said bending moment system is arranged on fuselage outer side, comprises being positioned at blade terminal bending moment hinge and bending moment bar, and bending moment bar one end connects bending moment and cuts with scissors; The other end connects rotating ring; Fixed ring is connected through ball with rotating ring, and rotating ring is captiveed joint with a thread rod of handling through modified nitriding, and thread rod cooperates with the driven gear that is provided with negative thread; Driven gear and driving gear engagement, driving gear connects servomotor through gear wheel shaft.

Said rotor system comprises blade, following blade and propelling oar, and last blade, following blade are asymmetric protruding rotor, and last blade, following blade outer end are fixed by last blade mounting ring, following blade mounting ring respectively; Blade tips is drawn output shaft respectively; Output shaft is connected with the blade mounting ring, and last blade, down each 6 of blades arrange evenly that by circumference last blade and horizontal plane angle guarantee at 15 ° ~ 35 °; The gear ring outside is provided with connecting bore; Blade root axle is connected with gear ring through interference fit, advances oar to connect the electrical motor of a variable-ratio, and electrical motor is captiveed joint with fuselage.

Said output shaft and blade mounting ring are connected through bearing, and bearing is set to needle bearing and thrust ball bearing.Said going up between blade and the bending moment system is provided with vertical hinge and universal coupling, is provided with the damping shimmy-damper above the vertical hinge, and universal coupling is provided with plunging joint load cover outward.

Said driving device is arranged on fuselage interior; Driving engine, power-transfer clutch and change speed gear box are connected successively, and output shaft of gear-box is connected with horizontal bevel gear, and horizontal bevel gear meshes with two vertical finishing bevel gear cuters simultaneously; Vertically the finishing bevel gear cuter other end is connected with inner gear respectively, inner gear and gear ring engagement.

The invention has the beneficial effects as follows: parts convenient processing and manufacture, cost are low; Simple in structure, amount of parts is few, and fault rate is low, and is safe; Volume is little, saves the space, and can be manned, applied widely; When breaking down, just open and to find the source of trouble easily as long as fuselage is covered plate; Screw propeller adopts coaxial pair of paddle structure, compares the single-blade structure and can under equal rotating speed, bigger hoisting force be provided, and can realize VTOL easily, advance and turn to.

Description of drawings

Fig. 1 is the integral structure scheme drawing of the embodiment of the invention;

Fig. 2 is the birds-eye view of Fig. 1;

Fig. 3 is the transmission structures scheme drawing of the embodiment of the invention;

Fig. 4 is the bending moment system architecture scheme drawing of the embodiment of the invention;

Fig. 5 is the most advanced and sophisticated fixedly scheme drawing of the blade of the embodiment of the invention;

Fig. 6 goes up fixedly scheme drawing of propeller shank;

Fig. 7 is the birds-eye view of Fig. 6;

Fig. 8 is a driving compartment fixed sturcture scheme drawing;

Fig. 9 is that blade is connected scheme drawing with fuselage;

Among the figure: 1 driving compartment, 2 vertical hinges, 3 damping shimmy-dampers, 4 bending moments hinges, 5 plunging joint load covers, 6 bending moment bars, blade on 7; Blade mounting ring on 8,9 times blade mounting rings, 10 handles, 11 thread rods, 12 servomotors, 13 fixed rings, 14 rotating rings; 15 advance oar, 16 alighting gears, 17 glass outer covers, 18 seats, 19-1 thrust ball bearing I, 19-2 thrust ball bearing II, 19-3 thrust ball bearing III; 19-4 thrust ball bearing IV, 20 self-aligning roller bearings, 21 gear rings, 22 horizontal bevel gear, 23 inner geares, 24 inner layer glass covers, 25 control panels; 26 change speed gear boxs, 27 power-transfer clutchs, 28 driving engines, 29 thrust bearing retainers, 30 central principal axis, 31 balls, 32 driven gears; 33 driving gears, 34 needle bearings, 35 blade root axles, 36 times blades, 37-1 deep groove ball bearing I, 37-2 deep groove ball bearing II, the last blade output shaft of 38-1; Blade output shaft under the 38-2,39 bearing stopper rings, 40 Biserial cylindrical roller bearings, 41 universal couplings, 42 electrical motors, 43 motor strut bars.

The specific embodiment

Below in conjunction with accompanying drawing and embodiment the present invention is further specified.

Like Fig. 1, shown in Figure 2, disc aircraft comprises driving compartment 1, fuselage, bending moment system, rotor system, driving device, power system and alighting gear 16, and fuselage is as the integrally-built fixing bracket body of aircraft; Driving compartment 1 is arranged on body upper, and the bending moment system is driven by servomotor 12, servomotor 12 connection gear transmission devices and bending moment hinge 4; Bending moment system one side connects rotor system, and rotor system is arranged on the fuselage outer rim, comprises blade 7, following blade 36 and advances oar 15; Last blade 7, blade 36 outer ends are fixed by mounting ring respectively down, advance oar 15 to be located at fuselage bottom and to be connected with motor it is driven, and bending moment system opposite side is provided with gear ring 21; Gear ring 21 cooperates with the driving device of gear forms; The power input shaft of driving device connects power system, and power system is made up of change speed gear box 26, power-transfer clutch 27 and driving engine 28, is arranged in the fuselage compartment; Alighting gear 16 is fixed on fuselage bottom, is connected through thrust ball bearing II19-2 and central principal axis 30.

Like Fig. 3, shown in Figure 8, said driving compartment 1 is made up of seat 18, hatch door and control panel 25, and hatch door is made up of with inner layer glass cover 24 the glass outer cover 17 of 1/4 ball-type; Wherein inner layer glass cover 24 is fixing; Glass outer cover 17 is provided with S. A., and the outside is provided with handle 10, and seat 18 is arranged in the hatch door with control panel 25; Driving compartment 1 bottom is provided with central principal axis 30; Central principal axis 30 is connected with thrust ball bearing I 19-1 and fuselage through self-aligning roller bearing 20 respectively, is provided with bearing stopper ring 39 outside the self-aligning roller bearing 20, and thrust ball bearing I 19-1 is provided with thrust bearing retainer 29 outward; Driving compartment 1 side-lower is provided with the parachute storehouse, chaufeur and passenger escape when being used for the aircraft fault.

As shown in Figure 4, said bending moment system is arranged on fuselage outer side, comprises being positioned at blade terminal bending moment hinge 4 and bending moment bar 6; Bending moment bar 6 one ends connect bending moment hinge 4; The other end connects rotating ring 14, and rotating ring 14 rotates with blade synchronously, encircles 13 surely and is connected through ball 30 with rotating ring 14; Rotating ring 14 and thread rod 11 welding of handling through modified nitriding are fixed; Thread rod 11 cooperates with the driven gear that is provided with negative thread 32, driven gear 32 and driving gear 33 engagements, and driving gear 33 connects servomotor 12 through gear wheel shaft; The angle that is driven bending moment hinge 4 by the left-right rotation of servomotor 12 changes, thereby the angle of attack that orders about blade becomes big or diminishes and reaches the purpose that changes torque.

Like Fig. 5, shown in Figure 9, said rotor system comprises blade 7, following blade 36 and advance oar 15, and last blade 7, to descend blade 36 be asymmetric protruding rotor; Last blade 7, blade 36 outer ends are respectively by last blade mounting ring 8, blade mounting ring 9 is fixing down down, and blade tips is drawn output shaft respectively, and output shaft is connected with the blade mounting ring; Last blade 7, down blade 36 each 6 evenly arrange by circumference; Last blade 7 guarantees at 15 ° ~ 35 ° with horizontal plane angle, by last blade 7, the rotation of blade 36 forms a conical surface down, can reduce to produce owing to the fuselage sectional area is excessive bigger useless resistance during flight; Gear ring 21 outsides are provided with connecting bore; Blade root axle 35 is connected with gear ring 21 through interference fit, advances oar 15 to connect the electrical motor 42 of a variable-ratio, and electrical motor 42 is captiveed joint with fuselage through motor strut bar 43; The rotation direction of two propelling oars 15 is opposite, to eliminate owing to the moment of torsion that advances oar 15 rotations to produce makes aircraft can not keep balance.

Said go up blade output shaft 38-1 and following blade output shaft 38-2 respectively with last blade mounting ring 8, descend blade mounting ring 9 to be connected through bearing; Bearing is set to needle bearing 34 and thrust ball bearing III 19-3; Needle bearing 34 can prevent the relative motion of blade and blade mounting ring generation in the vertical direction; Enable to connect more firmly, thrust ball bearing III 19-3 can prevent relatively moving on blade and the blade mounting ring occurred level direction.

Like Fig. 6, shown in Figure 7; Said going up between blade 7 and the bending moment system is provided with vertical hinge 2 and universal coupling 41; Vertical hinge 2 tops are provided with damping shimmy-damper 3; Because universal coupling 41 can not bear big diametral load, the universal coupling 41 outer plunging joint load covers 5 of installing, universal coupling 41 adopts Biserial cylindrical roller bearing 40 to realize with the relative motion of plunging joint load cover 5; Through the Biserial cylindrical roller bearing 40 that is arranged on two ends power is passed to plunging joint load cover 5 when universal coupling 41 receives diametral load, come bearing radial force by plunging joint load cover 5; Bending moment cuts with scissors 4 set inside thrust ball bearing IV 19-4 and deep groove ball bearing I 37-1, deep groove ball bearing II 37-2, and what be used for guaranteeing overcoat and inner shaft relatively rotates and prevent its relative motion radially; Universal coupling 41 is used to realize the maintenance of blade 7 and the propeller hub angle of level; Vertical hinge 2 is formed the drag reduction system with damping shimmy-damper 5; Blade 7 can be round vertical hinge 2 swings on when aircraft startup, acceleration, deceleration; Reduce swing by damping shimmy-damper 5, can prevent that aircraft flat-out acceleration or deceleration from causing the propeller hub fracture.

As shown in Figure 2, said driving device is arranged on fuselage interior, and driving engine 28, power-transfer clutch 27 and change speed gear box 26 are connected successively; Change speed gear box 26 output shafts are connected with horizontal bevel gear 22; Horizontal bevel gear 22 meshes with two vertical finishing bevel gear cuters simultaneously, and the rotation of horizontal bevel gear 22 can drive two vertical finishing bevel gear cuters and rotate with identical speed, and vertically the finishing bevel gear cuter other end is connected with inner gear 23 respectively; Internal tooth 23 and gear ring 21 engagements are through rotation drive gear ring 21 rotations of inner gear 23.

Said alighting gear 16 adopts the Sledge type alighting gear; This structure not only can alleviate aircraft weight but also can reduce place that very big pressure makes that aircraft is softer at soil or sandstone are a lot of and stop falling and be unlikely to be absorbed in ground; And this landing gear structure is simple; Design and manufacture cost is low, is more suitable for civilian.

During aircraft takeoff, by driving engine 28 drive go up blade 7, blade 36 rotates down, last blade 7, blade 36 direction of rotation down produce equal and opposite in direction, torque in the opposite direction, keep stablizing of aircraft; Thereby size by change speed gear box 26 control output speed control ascending velocity;, rotating speed calculates blade 7, the torque of blade 36 down when changing by control panel 25 programmed systems; Make computational analysis; And control signal is passed to servomotor 12, thereby the change of the control blade angle of attack, and then make blade 7, the torque of blade 36 is equal down; During decline, change output speed, reduce the blade rotating speed by change speed gear box 26; Aircraft begins to quicken to descend; When the speed of fall degree reaches theoretical value, change output speed, the blade pulling force is equated with gravity; This moment, aircraft at the uniform velocity descended, thereby the relation that whole process is calculated between blade state and the blade pulling force by control panel 25 programmed systems in real time realizes the closed loop control that aircraft goes up and down.

Claims

1. a disc aircraft comprises driving compartment, fuselage and alighting gear, it is characterized in that: this aircraft also comprises bending moment system, rotor system, driving device, power system; Fuselage is as the integrally-built fixing bracket body of aircraft, and driving compartment is arranged on body upper, and the bending moment system is by driven by servomotor; Servomotor connection gear transmission device and bending moment hinge, bending moment system one side connects rotor system, and rotor system is arranged on the fuselage outer rim; Comprise blade, following blade and advance oar, last blade, following blade outer end are fixed by mounting ring respectively, advance oar to be located at fuselage bottom and to be connected with motor it is driven; Bending moment system opposite side is provided with gear ring; Gear ring cooperates with the driving device of gear forms, and the power input shaft of driving device connects power system, and power system is made up of change speed gear box, power-transfer clutch and driving engine; Be arranged in the fuselage compartment, alighting gear is fixed on fuselage bottom.

2. disc aircraft according to claim 1; It is characterized in that said driving compartment is made up of seat, hatch door and control panel; Hatch door is made up of the glass outer cover and the inner layer glass cover of 1/4 ball-type, and wherein the inner layer glass cover is fixed, and glass outer is covered with S. A.; The outside is provided with handle, and seat and control panel are arranged in the hatch door.

3. disc aircraft according to claim 1 is characterized in that said bending moment system is arranged on fuselage outer side, comprises being positioned at blade terminal bending moment hinge and bending moment bar; Bending moment bar one end connects the bending moment hinge, and the other end connects rotating ring, and fixed ring is connected through ball with rotating ring; Rotating ring is captiveed joint with a thread rod; Thread rod cooperates with the driven gear that is provided with negative thread, driven gear and driving gear engagement, and driving gear connects servomotor through gear wheel shaft.

4. disc aircraft according to claim 3 is characterized in that said thread rod is the thread rod that modified nitriding is handled.

5. disc aircraft according to claim 1 is characterized in that said rotor system comprises blade, following blade and advances oar, and last blade, following blade outer end are fixed by last blade mounting ring, following blade mounting ring respectively; Blade tips is drawn output shaft respectively; Output shaft is connected with the blade mounting ring, and last blade, down each 6 of blades arrange evenly that by circumference last blade and horizontal plane angle guarantee at 15 ° ~ 35 °; The gear ring outside is provided with connecting bore; Blade root axle is connected with gear ring through interference fit, advances oar to connect the electrical motor of a variable-ratio, and electrical motor is captiveed joint with fuselage.

6. disc aircraft according to claim 5 is characterized in that said output shaft and blade mounting ring are connected through bearing, and bearing is set to needle bearing and thrust ball bearing.

7. disc aircraft according to claim 5 is characterized in that said upward blade, following blade are asymmetric protruding rotor.

8. disc aircraft according to claim 5 is characterized in that said going up between blade and the bending moment system is provided with vertical hinge and universal coupling, is provided with the damping shimmy-damper above the vertical hinge, and universal coupling is provided with plunging joint load cover outward.

9. disc aircraft according to claim 1; It is characterized in that said driving device is arranged on fuselage interior; Driving engine, power-transfer clutch and change speed gear box are connected successively, and output shaft of gear-box is connected with horizontal bevel gear, and horizontal bevel gear meshes with two vertical finishing bevel gear cuters simultaneously; Vertically the finishing bevel gear cuter other end is connected with inner gear respectively, inner gear and gear ring engagement.