阅读说明：本技术 一种低温隐形多喷口飞行器 (Low-temperature invisible multi-nozzle aircraft ) 是由 温江波 甄灵 许新芳 雷超 张春华 章百宝 董宇光 周军 赖武文 于 2020-05-09 设计创作，主要内容包括：本发明属于飞行器领域,公开了一种低温隐形多喷口飞行器,其包括：飞行器主体、动力系统、控制系统、底部喷口、垂直喷口、水平喷口、俯仰喷口、尾部喷口、气体管道、喷口阀门和降温增压装置,降温增压装置位于飞行器主体的中部位置,用于将动力系统前端进气口进入的一部分空气吸入、压缩、降温后并存储,供给各个喷口使用,用以改变飞行器的飞行姿态；存储的气体还供给尾部喷口,用于与动力系统产生的高温、高压、高速气流混合形成低温、高压、高速气流向后喷出,为飞行器向前高速飞行提供推动力。本发明能够避免因襟翼、副翼、升降舵、方向舵故障造成的空难,同时减少热辐射,解决现有各种喷气式飞机因高温辐射难以隐身的问题。(The invention belongs to the field of aircrafts, and discloses a low-temperature invisible multi-nozzle aircraft, which comprises: the aircraft comprises an aircraft body, a power system, a control system, a bottom nozzle, a vertical nozzle, a horizontal nozzle, a pitching nozzle, a tail nozzle, a gas pipeline, a nozzle valve and a cooling and pressurizing device, wherein the cooling and pressurizing device is positioned in the middle of the aircraft body and used for sucking, compressing, cooling and storing a part of air entering from an air inlet at the front end of the power system and supplying the air to each nozzle for use so as to change the flight attitude of the aircraft; the stored gas is also supplied to the tail nozzle and is used for being mixed with high-temperature, high-pressure and high-speed airflow generated by the power system to form low-temperature, high-pressure and high-speed airflow to be ejected backwards, so that the propulsion force is provided for forward high-speed flight of the aircraft. The invention can avoid the air crash caused by the faults of the flap, the aileron, the elevator and the rudder, simultaneously reduce the heat radiation and solve the problem that the prior various jet airplanes are difficult to hide due to the high-temperature radiation.)

1. A cryogenic invisible multi-jet aircraft, comprising: the aircraft comprises an aircraft body (1), a power system (2), a control system (3), a bottom nozzle (4), a vertical nozzle (5), a horizontal nozzle (6), a pitching nozzle (7), a tail nozzle (8), a gas pipeline (9), a nozzle valve (10) and a cooling and pressurizing device (11); the power systems (2) are positioned at two sides of the center of the aircraft body (1), and jet high-pressure and high-speed airflow backwards to generate driving force for the aircraft to fly forwards at high speed; the control system (3) is positioned in the middle of the front part of the aircraft; the bottom nozzles (4) are positioned around the center of gravity of the bottom of the aircraft body (1), and high-pressure and high-speed airflow is downwards sprayed through the bottom nozzles (4) when the aircraft vertically takes off, so that power is provided for the vertical taking off and landing of the aircraft; the vertical nozzles (5) are positioned in the middle positions of the bottoms of wings on two sides of the aircraft body (1), and high-pressure and high-speed airflow is intermittently and downwards sprayed through the vertical nozzles (5) to provide power for the aircraft to roll along the axial direction; the horizontal nozzles (6) are positioned at the top ends of wings at two sides of the aircraft body (1), and high-pressure high-speed airflow is intermittently ejected forwards or backwards through the horizontal nozzles (6) to provide power for horizontal steering of the aircraft; the pitching nozzles (7) are positioned in the middle positions of the rear ends of wings on two sides of the aircraft body (1), and high-pressure high-speed airflow is intermittently ejected upwards or downwards through the pitching nozzles (7) to provide steering power for the climbing or descending of the aircraft; the tail nozzle (8) is positioned at the tail part of the aircraft power system (3), and high-pressure high-speed airflow is sprayed backwards through the tail nozzle (8) to generate driving force for the aircraft to fly forwards at high speed; the gas pipeline (9) is positioned in the aircraft and is a pipeline for connecting the cooling and pressurizing device (11) with the bottom nozzle (4), the vertical nozzle (5), the horizontal nozzle (6), the pitching nozzle (7), the tail nozzle (8) and the nozzle valve (10); a plurality of nozzle valves (10) are respectively positioned at the front ends of the bottom nozzle (4), the vertical nozzle (5), the horizontal nozzle (6), the pitching nozzle (7) and the tail nozzle (8) and used for controlling the injection time and the flow rate of the high-pressure high-speed air flow; the nozzle valve (10) is controlled by the control system (3), and the control system (3) gives out a control signal to control the opening or closing of the nozzle valve (10); the cooling and pressurizing device (11) is positioned in the middle of the aircraft body (1) and is used for sucking, compressing, cooling and storing a part of air entering from an air inlet at the front end of the power system (2) and supplying the air to each nozzle for use so as to change the flying posture of the aircraft; the stored gas is also supplied to a tail nozzle (8) and is used for being mixed with high-temperature, high-pressure and high-speed airflow generated by the power system (2) to form low-temperature, high-pressure and high-speed airflow to be ejected backwards, so that the propulsion force is provided for forward high-speed flight of the aircraft.

2. The cryogenic invisible multi-jet aircraft according to claim 1, characterized in that the bottom jets (4) are provided with at least four.

3. The low-temperature invisible multi-jet aircraft according to claim 1, wherein the power system (2) is a high-thrust turbojet engine, a hypersonic ramjet engine or an electric motor.

4. The cryogenic invisible multi-jet aircraft according to claim 1, wherein the gas pipeline (9) is divided into a main pipeline and a branch pipeline, the main pipeline connects the bottom jet (4), the vertical jet (5), the horizontal jet (6), the pitching jet (7) and the tail jet (8) in series, the branch pipeline is connected to the jet valve (10) from the main pipeline, and when the jet valve (10) is opened, high-pressure gas is ejected from the main pipeline through the branch pipeline and the jet valve (10) from the corresponding jet.

5. The low-temperature invisible multi-jet aircraft according to claim 1, wherein the cooling and pressurizing device (11) comprises an engine, a compressor and a high-pressure air storage tank; the engine drives the compressor to further compress and pressurize high-speed cold air introduced from an air inlet at the front end of the power system (2) to the high-pressure air storage tank, and the high-pressure air storage tank stores high-pressure air compressed by the compressor.

6. The low-temperature invisible multi-nozzle aircraft as claimed in claim 5, wherein the cooling and pressurizing device (11) further comprises a heat exchange cooling device, the heat exchange cooling device comprises a cooling fin and a cooling tube which are coated outside the engine, the compressor and the high-pressure air storage tank, and a part of high-speed cold air introduced from the air inlet at the front end of the power system (2) is branched to enter the heat exchange cooling device to cool the cooling fin and the cooling tube, so as to reduce the outside temperature of the engine, the compressor and the high-pressure air storage tank.

7. The cryogenic invisible multi-jet aircraft according to claim 5, wherein the high pressure gas tank is a steel cylinder high pressure gas tank.

8. The low-temperature invisible multi-jet aircraft according to claim 1, wherein the jet valve (10) is an electromagnetic valve.

9. The low-temperature invisible multi-jet aircraft according to claim 1, wherein the jet valve (10) is a hydraulic valve controlled by an additional hydraulic control system.

10. The low-temperature invisible multi-jet aircraft according to claim 1, wherein the aircraft body (1) is in the aerodynamic shape of an American B2 invisible bomber or in the shape of a French fly 20 or C919.

Technical Field

The invention belongs to the technical field of aircrafts, and relates to a low-temperature invisible multi-nozzle aircraft.

Background

In the existing aircraft, the fixed wing aircraft needs to control the flight attitude of the aircraft by using flaps, ailerons, horizontal empennages, elevators, vertical empennages, rudders and the like, and the air crash caused by the faults of the flaps, the ailerons, the elevators and the rudders is easy to generate; on the other hand, the heat radiation is high, and the stealth is difficult.

Disclosure of Invention

Objects of the invention

The purpose of the invention is: the utility model provides a stealthy many spouts aircraft of low temperature based on a plurality of directions, a plurality of jet orifices to avoid the air crash because of flap, aileron, elevator, rudder trouble that rudder trouble caused, reduce the heat radiation simultaneously, solve current various jet plane because of the problem that high temperature radiation is difficult to stealthy.

(II) technical scheme

In order to solve the technical problem, the invention provides a low-temperature invisible multi-jet aircraft, which comprises: the device comprises an aircraft body 1, a power system 2, a control system 3, a bottom nozzle 4, a vertical nozzle 5, a horizontal nozzle 6, a pitching nozzle 7, a tail nozzle 8, a gas pipeline 9, a nozzle valve 10 and a cooling and pressurizing device 11; the power systems 2 are positioned at two sides of the center of the aircraft body 1, and jet high-pressure and high-speed airflow backwards to generate driving force for the forward high-speed flight of the aircraft; the control system 3 is located in the middle of the front of the aircraft; the bottom nozzles 4 are positioned around the bottom gravity center of the aircraft body 1, and high-pressure and high-speed airflow is downwards sprayed through the bottom nozzles 4 when the aircraft vertically takes off, so that power is provided for the vertical taking off and landing of the aircraft; the vertical nozzles 5 are positioned in the middle of the bottoms of wings on two sides of the aircraft body 1, and intermittently and downwards jet high-pressure high-speed airflow through the vertical nozzles 5 to provide power for the aircraft to roll along the axial direction; the horizontal nozzles 6 are positioned at the top ends of wings at two sides of the aircraft body 1, and high-pressure high-speed airflow is intermittently ejected forwards or backwards through the horizontal nozzles 6 to provide power for horizontal steering of the aircraft; the pitching nozzles 7 are positioned in the middle positions of the rear ends of wings on two sides of the aircraft body 1, and high-pressure high-speed airflow is intermittently ejected upwards or downwards through the pitching nozzles 7 to provide steering power for climbing or descending of the aircraft; the tail nozzle 8 is positioned at the tail part of the aircraft power system 3, and high-pressure and high-speed airflow is sprayed backwards through the tail nozzle 8 to generate driving force for forward high-speed flight of the aircraft; the gas pipeline 9 is positioned in the aircraft and is a pipeline for connecting the cooling and pressurizing device 11 with the bottom nozzle 4, the vertical nozzle 5, the horizontal nozzle 6, the pitching nozzle 7, the tail nozzle 8 and the nozzle valve 10; a plurality of nozzle valves 10 are respectively positioned at the front ends of the bottom nozzles 4, the vertical nozzles 5, the horizontal nozzles 6, the pitching nozzles 7 and the tail nozzles 8, and are used for controlling the injection time and the flow of the high-pressure high-speed airflow; the nozzle valve 10 is controlled by the control system 3, and the control system 3 gives out a control signal to control the opening or closing of the nozzle valve 10; the cooling and pressurizing device 11 is positioned in the middle of the aircraft body 1 and used for sucking, compressing, cooling and storing a part of air entering from an air inlet at the front end of the power system 2, and supplying the part of air to each nozzle for use so as to change the flight attitude of the aircraft; the stored gas is also supplied to a tail nozzle 8 and is used for being mixed with high-temperature, high-pressure and high-speed airflow generated by the power system 2 to form low-temperature, high-pressure and high-speed airflow to be ejected backwards, so that the propulsion force is provided for forward high-speed flight of the aircraft.

Wherein the bottom jets 4 are provided with at least four.

Wherein, the power system 2 adopts a high-thrust turbojet engine, a hypersonic ramjet engine or an electric motor.

Wherein, gas conduit 9 divide into trunk line and lateral conduit, and the trunk line is established ties bottom spout 4, perpendicular spout 5, horizontal spout 6, every single move spout 7, afterbody spout 8, and the lateral conduit is connected to spout valve 10 from the trunk line, and when spout valve 10 was opened, high-pressure gas followed the trunk line through lateral conduit and spout valve 10 from corresponding spout blowout.

The cooling and pressurizing device 11 comprises an engine, a compressor and a high-pressure air storage tank; the engine drives the compressor to further compress and pressurize the high-speed cold air introduced from the air inlet at the front end of the power system 2 to the high-pressure air storage tank, and the high-pressure air storage tank stores the high-pressure air compressed by the compressor.

Wherein, cooling supercharging device 11 still includes the heat exchange heat sink, and the heat exchange heat sink is including cladding in engine, compressor and the outside fin and the cooling tube of high-pressure gas holder, and the high-speed cold air reposition of redundant personnel that 2 front ends air inlets of driving system introduce partly gets into the heat exchange heat sink, cools down fin, cooling tube to reduce the outside temperature of engine, compressor and high-pressure gas holder.

Wherein, the high-pressure gas storage tank is a steel cylinder high-pressure gas storage tank.

Wherein, the spout valve 10 is an electromagnetic valve.

The spout valve 10 is a hydraulic valve controlled by an additionally arranged hydraulic control system.

The aircraft body 1 is in the aerodynamic shape of an American B2 invisible bomber or in the shapes of 20 and C919.

(III) advantageous effects

The low-temperature invisible multi-nozzle aircraft provided by the technical scheme has the following advantages:

(1) the aircraft is provided with a plurality of horizontal and vertical jet ports besides the tail power jet port, and the speed and the posture of the aircraft can be adjusted by adjusting the jet flow, the pressure and the time of each jet port, so that the control of the aircraft is more convenient, concise and smooth;

(2) the aircraft is free of flaps, ailerons, elevators and rudders, the strength of the wings and the empennage is higher, the overall structure is simpler, the safety is better, and the manufacturing cost is lower;

(3) the aircraft has more free external shape, can adopt more excellent pneumatic shapes, has better adaptability, wider application and larger load range;

(4) the aircraft can adopt various power systems, almost existing high-efficiency engines or motors can be used, the number and the distribution positions of the power systems can be freely designed according to needs, and the design freedom degree is larger;

(5) the aircraft is provided with the cooling and pressurizing device at the rear end of a power system, so that the temperature of high-pressure gas sprayed out of each jet orifice, particularly the tail jet orifice, is close to the ambient temperature, the heat radiation is reduced, the problem that the existing various jet airplanes are difficult to hide due to high-temperature radiation is solved, and a solid foundation is laid for designing high-performance invisible fighters;

(6) the high-pressure gas sprayed by the aircraft is close to the ambient temperature, so that high-temperature environmental pollution caused by high temperature of thousands of degrees is reduced, the damage and the injury of the aircraft to the atmospheric environment and air-flying organisms are reduced, and the earth is in blue sky and white cloud.

Drawings

FIG. 1 is a front view of the cryogenic invisible multi-jet aircraft of the present invention.

Fig. 2 is a view taken along direction a of fig. 1.

Fig. 3 is a top view of fig. 1.

Detailed Description

In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.

Referring to fig. 1 to 3, the low-temperature invisible multi-jet aircraft of the present embodiment includes: the aircraft comprises an aircraft body 1, a power system 2, a control system 3, a bottom nozzle 4, a vertical nozzle 5, a horizontal nozzle 6, a pitching nozzle 7, a tail nozzle 8, a gas pipeline 9, a nozzle valve 10 and a cooling and pressurizing device 11.

The aircraft body 1 described in this embodiment is a body that carries all the system components of the aircraft, and is a body that generates a flight lift force. The aircraft body 1 of the present embodiment is an aerodynamic model of an american B2 invisible bomber, and is illustrated.

In fact, the aircraft body 1 of the invention can also be designed into various other more suitable aerodynamic shapes, and various existing jet airplanes such as 20 fighters and C919 in China can be designed, processed or modified by the multi-nozzle technology provided by the invention by adopting the design concept of the invention.

The design concept of the invention can eliminate the wing flap, the aileron, the elevator and the rudder of the aircraft, so that the wing and the empennage of the aircraft have higher strength, simpler integral structure, better safety, lower manufacturing cost and low-temperature stealth effect.

The power system 2 described in this embodiment is located at both sides of the center of the aircraft body 1, and two sets of existing suitable high-thrust turbojet engines are used, and jet high-pressure high-speed airflow backwards to generate a driving force for forward high-speed flight of the aircraft.

The power system 2 described in this embodiment may also adopt other more advanced engines, such as hypersonic ramjet engines, where hypersonic air is inhaled from an air inlet and then mixed with aviation fuel to be combusted, and then ejected at hypersonic speed, which is used as the power for the forward high-speed flight of the aircraft.

The power system 2 described in this embodiment may also adopt an electric motor, if an electric motor is adopted, a high-power battery pack needs to be added, the whole aircraft is powered by a battery, two sets of high-thrust turbojet engines need to be changed into two sets of high-speed high-pressure electric turbojet motors, and the airflow at the air inlet is directly sucked in and pressurized and ejected at a high speed to serve as the power for the forward high-speed flight of the aircraft.

The control system 3 described in this embodiment is located in the middle of the front portion of the aircraft, and is used for controlling take-off and landing of the aircraft, flight attitude, opening and closing of the cabin door, wireless communication, opening and closing of the nozzle valve 10, and the like, and is a control center of the aircraft and a brain of the aircraft.

The bottom nozzle 4 described in this embodiment is located around the center of gravity of the bottom of the aircraft body 1, and four or more nozzles may be provided, so that the aircraft vertically takes off and jets high-pressure and high-speed airflow downwards through the bottom nozzle 4, thereby providing power for the vertical take-off and landing of the aircraft.

The vertical nozzles 5 are located in the middle of the bottoms of the wings on the two sides of the aircraft body 1, and high-pressure and high-speed airflow is intermittently and downwards injected through the vertical nozzles 5 to provide power for the aircraft to roll in the axial direction.

The horizontal nozzles 6 are positioned at the top ends of wings on two sides of the aircraft body 1, and high-pressure high-speed airflow is intermittently ejected forwards or backwards through the horizontal nozzles 6 to provide power for horizontal steering of the aircraft.

The pitching nozzles 7 described in this embodiment are located in the middle of the rear ends of the wings on both sides of the aircraft body 1, and intermittently eject high-pressure and high-speed airflow upwards or downwards through the pitching nozzles 7 to provide steering power for the aircraft to climb or descend.

The tail nozzle 8 is located at the tail of the aircraft power system 3, and high-pressure and high-speed airflow is ejected backwards through the tail nozzle 8 to generate driving force for forward high-speed flight of the aircraft.

The gas pipeline 9 described in this embodiment is located inside the aircraft, and is a pipeline in which the cooling and pressurizing device 11 is connected with the bottom nozzle 4, the vertical nozzle 5, the horizontal nozzle 6, the pitching nozzle 7, the tail nozzle 8, and the nozzle valve 10.

Gas conduit 9 divide into trunk line and lateral conduit, and the trunk line is in the same place bottom spout 4, perpendicular spout 5, horizontal spout 6, every single move spout 7, afterbody spout 8 series connection, and the lateral conduit is connected to spout valve 10 from the trunk line, and when spout valve 10 was opened, high-pressure gas was from the trunk line through lateral conduit and spout valve 10 from corresponding spout blowout.

The nozzle valves 10 described in this embodiment are provided in plural, and are respectively located at the front ends of the nozzles of the bottom nozzle 4, the vertical nozzle 5, the horizontal nozzle 6, the pitching nozzle 7, and the tail nozzle 8, and control the injection time and flow rate of the high-pressure and high-speed air flow.

The spout valve 10 is controlled by the control system 3, and the spout valve 10 can be controlled to be opened or closed only by the control system 3 giving a control signal.

The spout valve 10 is preferably a solenoid valve. Of course, the spout valve 10 may be a hydraulic valve, but this requires an additional hydraulic control system, and the control method is relatively tedious and complicated.

The cooling and pressurizing device 11 is located in the middle of the aircraft body 1 and comprises an engine, a compressor, a heat exchange cooling device and a high-pressure air storage tank; the engine can use the existing appropriate high-efficiency gasoline engine, and drives the compressor to further compress and pressurize the high-speed cold air introduced from the air inlet at the front end of the power system 2 to the high-pressure air storage tank; the compressor can use the existing suitable high-pressure gas compressor, and is used for compressing the high-speed cold air introduced by the air inlet; the high-pressure gas storage tank can be designed into a steel cylinder high-pressure gas storage tank with a proper shape and a proper capacity and is used for storing high-pressure gas compressed by a compressor, the heat exchange cooling device is a radiating assembly which is coated on an engine, radiating fins outside the compressor and the gas storage tank and a radiating pipe, and a part of high-speed cold air entering from the air inlet channel can be shunted to enter the heat exchange cooling device to cool the radiating fins and the radiating pipe, so that the external temperature of the engine, the compressor and the gas storage tank is reduced, and the high-pressure gas in the gas storage.

The cooling and pressurizing device 11 is used for sucking, compressing and cooling a part of air entering from an air inlet at the front end of the power system 2, storing the part of air in a low-temperature high-pressure air storage tank, and supplying the part of air to each nozzle for use at any time so as to change the flight attitude of an aircraft; the gas compressed and stored by the cooling and pressurizing device 11 can also provide a part of low-temperature, high-pressure and high-speed airflow for the tail nozzle 8, the part of the airflow is mixed with the high-temperature, high-pressure and high-speed airflow generated by the high-thrust turbojet engine of the power system 2 to form low-temperature, high-pressure and high-speed airflow to be ejected backwards, so that the driving force is provided for forward high-speed flight of the aircraft, and the mixed airflow has relatively low temperature, so that the heat radiation intensity is relatively low, and a good stealth effect can be provided for the aircraft.

The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.