CN201077530Y - Vertically taking off and landing energy-saving pre-warning device - Google Patents
Vertically taking off and landing energy-saving pre-warning device Download PDFInfo
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- CN201077530Y CN201077530Y CNU2007200136596U CN200720013659U CN201077530Y CN 201077530 Y CN201077530 Y CN 201077530Y CN U2007200136596 U CNU2007200136596 U CN U2007200136596U CN 200720013659 U CN200720013659 U CN 200720013659U CN 201077530 Y CN201077530 Y CN 201077530Y
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Abstract
The utility model relates to a vertical-takeoff energy-saving early warning aircraft. The power unit of the aircraft is movingly connected with a belt and a generator through the engine. The electric energy output by the generator is connected with a plurality of motors on the front and rear parts through wires, which can save fuel oil. Propellers are arranged on a plurality of front motors. A plurality of rear motors is positioned inside the air jet duct of the empennage. Impellers are arranged on the rear motors. Two hydraulic pistons are arranged on very front motor casing and on the outer casing of the air jet duct. The drawing and pushing of the pistons drive every motor and air jet duct to lift vertically. The front motors drives the propellers and the rear air jet duct to rotate at 90 degree and to push air downwards, so the utility model has the advantages of ingenious conception, less oil consumption, complete function in particular vertical-takeoff and landing function, simple structure, light-weighted parts, low cost of fabrication and flight, convenient installation and maintenance, and special use for aviation.
Description
Technical field
The utility model relates to aircraft, concrete is the energy-conservation early warning plane of a kind of vertical takeoff and landing.
Background technology
The development of aeronautical technology is at present maked rapid progress, and numerous in variety, performance is different, but the principle of work of its engine installation and working process are similar, simply say it is to make engine operation with fuel oil, and then promotes air and produce application force and fly.The weakness of this engine installation is that consumption of fuel is big, so that there is the small part fuel oil not have economic combustion just outside the form ejection machine with oil gas.In addition, at present aircraft does not also possess the function of vertical takeoff and landing, and this is a thing of making us feeling regret to fighter plane, detective's machine, early warning plane, and this is in aircraft function almost out of this world today, looms large especially and important.
Summary of the invention
The purpose of this utility model is that will to solve present aircraft consumption of fuel big, does not have the problem of vertical takeoff and landing function, and provides vertical takeoff and landing energy-conservation early warning plane.
The technical scheme that adopts is:
The energy-conservation early warning plane of vertical takeoff and landing comprises preceding wing, the tail wing, engine installation, hydraulic actuator, pad blocking device; Described engine installation comprises center unit, a plurality of anterior electrical motor and a plurality of rear portions electrical motor; The center unit is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with a plurality of electrical motors in rear portion with anterior a plurality of electrical motors by lead is corresponding respectively, the below of wing before anterior a plurality of electrical motors are positioned at, the relative position of motor field frame both sides is provided with two axostylus axostyles parallel with preceding wing, one end of two axostylus axostyles is rotationally connected with the housing both sides of electrical motor respectively, and the other end of two axostylus axostyles is captiveed joint with preceding wing respectively.
The a plurality of electrical motors in rear portion are positioned at the jet air channel of the tail wing, and the rear portion electrical motor is captiveed joint with the inwall in the jet air channel of the tail wing.On the both sides relative position of the body skin in jet air channel two axostylus axostyles are set, an end of two axostylus axostyles and the body skin both sides in jet air channel are rotationally connected, and the other end of two axostylus axostyles is captiveed joint with the tail wing.
Described hydraulic actuator comprises a plurality of anterior hydraulic pistons, a plurality of rear portions hydraulic piston; Hydraulic compressor is positioned at the center unit, and hydraulic compressor is connected with electrical generator by lead in the unit of center, and hydraulic compressor is connected with a plurality of rear portions hydraulic piston with a plurality of anterior hydraulic pistons with the rear portion hydraulic tubing by anterior hydraulic tubing respectively.
The piston rod of per two anterior hydraulic pistons is rotationally connected with the forward and backward both sides of the housing axostylus axostyle axle of each anterior electrical motor respectively, synchronization action, before stretch after contracting or protract after contract, thereby make anterior electrical motor rotate 90 ° around the axle of axostylus axostyle, become plumbness.By the piston rod action homing of anterior hydraulic piston, the piston seat of front piston is fixedly connected on the lower surface of preceding wing again.
The piston rod of per two rear portion hydraulic pistons is rotationally connected with the forward and backward both sides of the body skin axostylus axostyle axle in each jet air channel respectively, synchronization action, before stretch after contracting or protract after contract, and make jet air channel rotate 90 ° around the axostylus axostyle axle, become plumbness, the piston seat of rear portion hydraulic piston is fixedly connected on the lower surface of the tail wing.
Described pad registration device comprises a plurality of anterior pad hydraulic pistons, a plurality of rear portions pad hydraulic piston; The forward and backward both sides of the shell axostylus axostyle axle of each anterior electrical motor are provided with pin-and-hole, the front end of the piston rod of anterior pad hydraulic piston is provided with pad, when anterior electrical motor is vertical, the pad of anterior pad hydraulic piston is replaced in pin-and-hole, the lower surface of wing before the piston seat of anterior pad hydraulic piston is fixedly connected on.
The forward and backward both sides of the axostylus axostyle axle of jet air channel, each rear portion body skin are provided with pin-and-hole, the front end of the piston rod of rear portion pad hydraulic piston is provided with pad, when jet air channel, rear portion is vertical, the pad of rear portion pad hydraulic piston is replaced in pin-and-hole, and the piston seat of rear portion pad hydraulic piston is fixedly connected on the lower surface of the tail wing.
The shaft installing screw propeller of above-mentioned a plurality of anterior electrical motors.
The shaft installing impeller of above-mentioned a plurality of rear portions electrical motor.
The utility model is skillfully constructed, because of carrying out 90 ° of rotations in the jet air channel at anterior motor drives screw propeller and rear portion, and push air downwards, so early warning plane has the function of vertical takeoff and landing, consumption of fuel is few, multiple functional, simple in structure, parts are light, cheap, be convenient to installation and maintenance, flight cost is low, suitable aviation special use.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is that Figure 1A-A is to scheme drawing.
Fig. 3 is that Figure 1B-B is to scheme drawing.
The specific embodiment
Embodiment
The energy-conservation early warning plane of vertical takeoff and landing, wing 10, the tail wing 6, engine installation, hydraulic actuator, pad blocking device before comprising; Engine installation comprises center unit 3, four anterior electrical motors 11 and two rear portion electrical motors 8; Center unit 3 is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with two electrical motors 8 of anterior four electrical motors 11 and rear portions by lead is corresponding respectively, the below of wing 10 before anterior four electrical motors 11 are positioned at, the relative position of electrical motor 11 housing both sides is provided with two axostylus axostyles parallel with preceding wing 16, one end of two axostylus axostyles 16 is rotationally connected with the housing both sides of electrical motor 11 respectively, and the other end of two axostylus axostyles 16 is captiveed joint with preceding wing 10 respectively.The shaft of four anterior electrical motors 11 is equiped with four screw propellers 12.
Two electrical motors 8 in rear portion are positioned at the jet air channel 5 of the tail wing 6, and rear portion electrical motor 8 is captiveed joint with the inwall in jet air channel 5.One end of two axostylus axostyles, 22, two axostylus axostyles 22 and the body skin both sides in jet air channel 5 are set on the both sides relative position of the body skin in jet air channel 5 are rotationally connected, the other end of two axostylus axostyles 22 is captiveed joint with the tail wing 6, the shaft installing impeller 4 of two rear portion electrical motors 8.
Hydraulic actuator comprises eight anterior hydraulic pistons 17, four rear portion hydraulic pistons 23; Hydraulic compressor is positioned at center unit 3, and hydraulic compressor is connected with electrical generator by lead in center unit 3, and hydraulic compressor is connected with four rear portion hydraulic pistons 23 with eight anterior hydraulic pistons 17 with rear portion hydraulic tubing 7 by anterior hydraulic tubing 2 respectively.
The piston rod of per two anterior hydraulic pistons 17 is rotationally connected with the forward and backward both sides of 16 of the housing axostylus axostyles of each anterior electrical motor 11 respectively, synchronization action, before stretch after contracting or protract after contract, thereby make anterior electrical motor 11 rotate 90 ° around the axle of axostylus axostyle 16, become plumbness.The action homing of the piston rod by anterior hydraulic piston 17 again, the lower surface of wing 10 before the piston seat 14 of anterior hydraulic piston is fixedly connected on, front and rear portions piston seat 14 and 20 front and back are respectively arranged with two hydraulic pressure entrance pressure pressure relief openings 15 and 13.
The piston rod of per two rear portion hydraulic pistons 23 is rotationally connected with the forward and backward both sides of 22 of the body skin axostylus axostyles in each jet air channel 5 respectively, synchronization action, before stretch after contracting or protract after contract, and make jet air channel 5 rotate 90 ° around 22 of axostylus axostyles, become plumbness, the piston seat 20 of rear portion hydraulic piston is fixedly connected on the lower surface of the tail wing 6.
The pad registration device comprises eight anterior pad hydraulic pistons 26, four rear portion pad hydraulic pistons 24; The forward and backward both sides that the shell axostylus axostyle of each anterior electrical motor 11 is 16 are provided with pin-and-hole 18, the piston rod front end of anterior pad hydraulic piston 26 is provided with pad, when anterior electrical motor 11 is vertical, the pad of anterior pad hydraulic piston 26 is replaced in pin-and-hole 18, when anterior electrical motor 11 is intended resetting to level, the pad of anterior pad hydraulic piston 26 is withdrawal in advance, the lower surface of wing 10 before anterior pad hydraulic piston seat 19 is fixedly connected on, front and rear portions pad hydraulic piston seat 19 and 21 front and back are respectively arranged with two hydraulic pressure entrance pressure pressure relief openings 15 and 13.
The forward and backward both sides that the body skin axostylus axostyle in jet air channel 5, each rear portion is 22 are provided with pin-and-hole 25, the piston rod front end of rear portion pad hydraulic piston 24 is provided with pad, when jet air channel, rear portion 5 is vertical, the pad of rear portion pad hydraulic piston 24 is replaced in pin-and-hole 25, when jet air channel 5, rear portion intends resetting to level, the pad of rear portion pad hydraulic piston 24 is withdrawal in advance, and rear portion pad hydraulic piston seat 21 is fixedly connected on the lower surface of the tail wing 6.
The driving wheel 1 of the energy-conservation early warning plane of vertical takeoff and landing is a control center, make the turn of engine of center unit 3 and then make generator for electricity generation by instruction, front and rear portions electrical motor 11 and 8 possesses the rotation condition, primer fluid press output hydraulic pressure when taking off vertically, and a plurality of front and rear portions hydraulic pistons 17 and 23 are moved simultaneously, thereby anterior electrical motor 11 and jet air channel 5 are rotated 90 °, then connect front and rear portions electrical motor 11 and 8 power supplys, rotate by screw propeller 12 and impeller 4, just can implement the vertical takeoff and landing function; Warning function is implemented by the radar 9 of fuselage setting.
Claims (3)
1. the energy-conservation early warning plane of vertical takeoff and landing comprises preceding wing (10), the tail wing (6), engine installation, hydraulic actuator, pad blocking device; It is characterized in that:
Described engine installation comprises center unit (3), a plurality of anterior electrical motor (11) and a plurality of rear portions electrical motors (8); Center unit (3) is by driving engine, electrical generator and hydraulic compressor are formed, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with a plurality of electrical motors in rear portion (8) with anterior a plurality of electrical motors (11) by lead is corresponding respectively, anterior a plurality of electrical motors (11) are positioned at the below of preceding wing (10), the relative position of electrical motor (11) housing both sides is provided with two axostylus axostyles parallel with preceding wing (16), one end of two axostylus axostyles (16) is rotationally connected with the housing both sides of electrical motor (11) respectively, and the other end of two axostylus axostyles (16) is captiveed joint with preceding wing (10) respectively;
The a plurality of electrical motors in rear portion (8) are positioned at the jet air channel (5) of the tail wing (6), and rear portion electrical motor (8) is captiveed joint with the inwall in the jet air channel of the tail wing (6) (5); Two axostylus axostyles (22) are set on the both sides relative position of the body skin in jet air channel (5), and the body skin both sides of an end of two axostylus axostyles (22) and jet air channel (5) are rotationally connected, and the other end of two axostylus axostyles (22) is captiveed joint with the tail wing (6);
Described hydraulic actuator comprises that a plurality of anterior hydraulic pistons (17), a plurality of rear portions hydraulic pistons (23) hydraulic compressor are positioned at center unit (3), and hydraulic compressor is connected with a plurality of rear portions hydraulic pistons (23) with a plurality of anterior hydraulic pistons (17) with rear portion hydraulic tubing (7) by anterior hydraulic tubing (2) respectively;
The piston rod of per two anterior hydraulic pistons (17) is rotationally connected with the forward and backward both sides of the housing axostylus axostyle (16) of each anterior electrical motor (11) axle respectively, and anterior hydraulic piston seat (14) is fixedly connected on the lower surface of preceding wing (10);
The piston rod of per two rear portion hydraulic pistons (23) is rotationally connected with the forward and backward both sides of the body skin axostylus axostyle (22) in each jet air channel (5) axle respectively, and rear portion hydraulic piston seat (20) is fixedly connected on the lower surface of the tail wing (6);
Described pad registration device comprises a plurality of anterior pad hydraulic pistons (26), a plurality of rear portion pad hydraulic pistons (24); The forward and backward both sides of shell axostylus axostyle (16) axle of each anterior electrical motor (11) are provided with pin-and-hole (18), the front end of anterior pad hydraulic piston (26) is provided with pad, the pad of anterior pad hydraulic piston (26) is replaced in pin-and-hole (18) or withdrawal, and anterior pad hydraulic piston seat (19) is fixedly connected on the lower surface of preceding wing (10);
The forward and backward both sides of axostylus axostyle (22) axle of jet air channel, each rear portion (5) body skin are provided with pin-and-hole (25), the front end of rear portion pad hydraulic piston (24) is provided with pad, the pad of rear portion pad hydraulic piston (24) is replaced in pin-and-hole (25) or withdrawal, and rear portion pad hydraulic piston seat (21) is fixedly connected on the lower surface of the tail wing (6).
2. the energy-conservation early warning plane of vertical takeoff and landing according to claim 1 is characterized in that: the shaft installing screw propeller (12) of above-mentioned a plurality of anterior electrical motors (11).
3. the energy-conservation early warning plane of vertical takeoff and landing according to claim 1 is characterized in that: the shaft installing impeller (4) of above-mentioned a plurality of rear portions electrical motors (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200136596U CN201077530Y (en) | 2007-08-02 | 2007-08-02 | Vertically taking off and landing energy-saving pre-warning device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200136596U CN201077530Y (en) | 2007-08-02 | 2007-08-02 | Vertically taking off and landing energy-saving pre-warning device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201077530Y true CN201077530Y (en) | 2008-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200136596U Expired - Fee Related CN201077530Y (en) | 2007-08-02 | 2007-08-02 | Vertically taking off and landing energy-saving pre-warning device |
Country Status (1)
| Country | Link |
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| CN (1) | CN201077530Y (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616374A (en) * | 2012-04-16 | 2012-08-01 | 牟玉昌 | Helicopter |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN103192981A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN106275458A (en) * | 2015-06-23 | 2017-01-04 | 张怡月 | A kind of equipment not hindering aircraft |
| CN106573678A (en) * | 2014-03-18 | 2017-04-19 | 杰欧比航空有限公司 | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN107745796A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | A kind of double supporting legs of backpack large-scale antenna dome |
| CN109415120A (en) * | 2016-04-19 | 2019-03-01 | 先进飞机公司 | Unmanned plane |
-
2007
- 2007-08-02 CN CNU2007200136596U patent/CN201077530Y/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN102616374A (en) * | 2012-04-16 | 2012-08-01 | 牟玉昌 | Helicopter |
| CN103192981A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
| CN106573678A (en) * | 2014-03-18 | 2017-04-19 | 杰欧比航空有限公司 | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| CN106573678B (en) * | 2014-03-18 | 2021-04-13 | 杰欧比飞行有限公司 | Aircraft suitable for vertical take-off and horizontal flight |
| CN106275458A (en) * | 2015-06-23 | 2017-01-04 | 张怡月 | A kind of equipment not hindering aircraft |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN109415120A (en) * | 2016-04-19 | 2019-03-01 | 先进飞机公司 | Unmanned plane |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN107745796A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | A kind of double supporting legs of backpack large-scale antenna dome |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080625 Termination date: 20100802 |