阅读说明：本技术 空中可调喷射角度涡喷制雾系统 (Aerial adjustable spray angle vortex spraying system ) 是由 蔡元虎 魏佳加 杨小航 于 2021-11-16 设计创作，主要内容包括：本发明涉及一种空中可调喷射角度涡喷制雾系统,包括飞行平台、连接在飞行平台上的起落架以及微型涡喷发动机；所述的微型涡喷发动机通过发动机支撑架安装在支撑平台的下方,还包括用于接收无线控制信号的无线控制装置,无线控制装置控制发动机燃油泵配合微型涡喷发动机的启停供油,控制制雾剂泵将制雾剂由制雾剂喷管喷出,制雾剂在所述尾喷管喷口处的高温高压气体加热下形成雾气,发动机转动装置使微型涡喷发动机在水平状态下起动,而在喷雾作业时,将所述尾喷管喷口方向朝向地面转动,从而使雾气由尾喷管喷口垂直喷向地面。本发明是一种速率高、发烟量大,能够满足新型制雾剂高温雾化需求的空中制雾装置。(The invention relates to an aerial adjustable jet angle turbojet mist making system, which comprises a flight platform, an undercarriage connected to the flight platform and a miniature turbojet engine, wherein the undercarriage is connected with the upper part of the flight platform; the miniature turbojet engine pass through the engine supporting frame and install in supporting platform's below, still including the wireless control device who is used for receiving wireless control signal, the wireless control device control engine fuel pump cooperation miniature turbojet engine open the fuel feeding that stops, control system fog pump will make the fog agent by system fog agent spray tube blowout, the system fog agent is in form fog under the high temperature high-pressure gas heating of tail spray tube spout department, engine rotating device makes miniature turbojet engine start under the horizontality, and when the spraying operation, will tail spray tube spout direction rotates towards ground to make fog by the perpendicular injection of tail spray tube spout to ground. The aerial fog-making device has high speed and large smoke quantity, and can meet the high-temperature atomization requirement of the novel fog-making agent.)

1. The air-adjustable-spraying-angle turbojet mist making system is characterized by comprising a flight platform (1), an undercarriage (4) connected to the flight platform (1) and a micro turbojet engine (2), wherein the flight platform (1) comprises a supporting platform (11) and an aircraft (12) for driving the supporting platform (11) to fly; the micro turbojet engine (2) is arranged below the supporting platform (11) through an engine supporting frame (6);

the supporting platform (11) is provided with an aerosol making box (31), an aerosol making pump (32) and a fuel oil tank (5) for supplying oil to the micro turbojet engine (2), and the fuel oil tank (5) is communicated with the micro turbojet engine (2) through an engine fuel pump and a connecting pipeline; a mist-making agent spray pipe (33) is arranged at the outlet of the nozzle of the tail spray pipe of the micro turbojet engine (2), and the mist-making agent spray pipe (33) is communicated with the mist-making agent box (31) through a mist-making pipeline (34) and a mist-making agent pump (32); an engine rotating device (8) for driving the micro turbojet engine (2) to rotate in a pitching manner is arranged on the engine supporting frame (6);

the engine support frame (6) is provided with a wireless control device (10), and the wireless control device (10) is respectively and electrically connected with the micro turbojet engine (2), the engine fuel pump, the mist making agent pump (32) and the engine rotating device (8); the wireless control device (10) is used for receiving wireless control signals, controls the starting and stopping oil supply of the engine fuel pump matched with the micro turbojet engine (2), controls the mist making pump (32) to spray the mist making agent from a mist making agent spray pipe (33), so that the mist making agent is heated by high-temperature high-pressure gas at the position of a tail spray pipe nozzle to form mist, and simultaneously controls the engine rotating device (8) to start the micro turbojet engine (2) in a horizontal state, and during spraying operation, the tail spray pipe nozzle direction of the micro turbojet engine (2) rotates towards the ground until the micro turbojet engine (2) vertically rotates towards the ground, so that the mist is vertically sprayed to the ground through the tail spray pipe nozzle.

2. The aerial adjustable spray angle turbojet mist generation system of claim 1, wherein the engine rotating device (8) comprises a servo steering engine (81), an upper rocker arm (82) and a lower rocker arm (84), one end of the upper rocker arm (82) and one end of the lower rocker arm (84) are rotating ends, and the other end of the upper rocker arm and the lower rocker arm are swinging ends; the swinging ends of the upper rocker arm (82) and the lower rocker arm (84) are connected through a pull rod (83); the rudder stock of the servo steering engine (81) is connected with the rotating end of the upper rocker arm (82), the rotating end of the lower rocker arm (84) is connected with the rotating end of the engine clamping rotating device (9), and the micro turbojet engine (2) is arranged on the engine supporting rack (6) through the engine clamping rotating device (9); the servo steering engine (81) is used for driving the swinging end of the upper rocker arm (82) to swing, so that the swinging end of the lower rocker arm (84) is driven to swing through the pull rod (83), and the rotating end of the lower rocker arm (84) drives the micro turbojet engine (2) to rotate in a pitching mode through the engine clamping and rotating device (9).

3. The aerial adjustable spray angle turbojet mist generation system of claim 2, wherein the engine clamping rotation device (9) comprises a clamp (91) fixedly clamped on the circumferential casing of the micro turbojet engine (2), a pair of connecting lugs (92) are arranged on the clamp (91), one end of each connecting lug (92) is fixedly connected with the clamp (91), a connecting clamping sleeve (93) is arranged at the other end of each connecting lug (92), a rotating shaft (94) is arranged on each connecting clamping sleeve (93), the rotating shaft (94) is rotatably arranged in a connecting hole (95) in the engine support rack (6) in a penetrating manner, and the connecting end part of the rotating shaft (94) is connected with the rotating end of the lower rocker arm (84) of the engine rotation device (8).

4. The air-borne adjustable-spray-angle turbojet aerosol system of claim 1, wherein the aerosol-generating nozzle (33) is an annular aerosol-generating pipe which is matched with a nozzle of a tail nozzle of the micro turbojet engine (2), at least two aerosol-generating nozzles (35) are communicated with the annular aerosol-generating pipe, and an outlet of the aerosol-generating nozzle (35) is obliquely directed to an axial direction of the nozzle of the tail nozzle of the micro turbojet engine (2).

5. The aerial adjustable spray angle vortex spraying mist making system according to claim 4, wherein the mist making agent nozzles (35) are uniformly distributed and communicated on the pipe body on the same peripheral surface of the annular mist making agent spray pipe (33), and the inclination angle of the mist making agent nozzles (35) relative to the axial direction of the tail spray pipe nozzle is 15-60 degrees.

6. The air-adjustable spray angle turbojet mist generation system of claim 4, wherein the aerosol-generating nozzle (33) is welded or a mounting lug is fixed at the nozzle of the micro-engine (2).

7. The aerial adjustable spray angle swirl spray system according to any one of claims 1-6, wherein the fuel tank (5) is fixedly mounted on a mounting platform on the upper surface of the support platform (11), the aerosol generating tank (31) is mounted on a mounting platform on the lower surface of the support platform (11), and the fuel tank (5) and the aerosol generating tank (31) are coaxially arranged.

8. The aerial adjustable spray angle turbojet mist generation system of any one of claims 1 to 6, wherein the landing gear (4) is a pair of U-shaped landing gears which are arranged correspondingly, both ends of the open side of each U-shaped landing gear are fixedly connected to the support platform (11), one end of each U-shaped landing gear, which is in contact with the ground, is provided with a pair of arc-shaped supporting feet (41), and the arc-shaped supporting feet (41) are provided with anti-skidding sleeves; the width of the opening end of the U-shaped landing gear is smaller than that of the end, in contact with the ground, of the U-shaped landing gear.

9. The aerial adjustable spray angle turbojet system of any one of claims 1 to 6, wherein an opening for adding engine fuel is provided in the fuel tank (5), and a handle is provided on the fuel tank (5) on the side of the opening.

Technical Field

The invention relates to mist making equipment for military use, in particular to a mist making system of an aerial miniature turbojet engine.

Background

The modern battlefield space is wide, the transparency is increased, the attack and defense conversion is rapid, the maneuvering operation requirement is high, the battlefield is more difficult to conceal, the fog making system is used as a military concealing camouflage weapon with unique shielding, interference, blindness and camouflage functions, the military concealing camouflage weapon reduces the visual and optical instrument observation capability of enemies, can prevent light radiation, is an effective barrier in the modern battlefield and is generally valued by military forces of various countries, and in the actual battlefield, the smog is not only widely applied to supporting tactical attack and defense combat, but also is a satellite of various photoelectric reconnaissance devices and precise guided weapons.

At present, the domestic fog making system is mainly a ground fog making system, most of the fog is heated by aerosol of liquid and then smoke is removed by an air blower, but because the contact area between a heating wire and the fog making agent is limited, the resulting smoking rate is slow, the smoking efficiency is low, and because the heating capacity is limited, the fog making system can not be heated to 800 ℃ or even higher temperature, so as to meet the atomization demands of different fog making agents, the novel multifunctional fog making agent with higher atomization temperature is particularly needed, the adaptability of the fog making system to the fog making agent is poor, and the large-area effective generation of the smoke is seriously influenced.

Compared with a ground fog making system, the aerial fog making system can be quicker, effective concealment of important military targets can be accurately completed, battlefield viability is improved, the aerial fog making system is particularly suitable for regions where motor vehicles such as mountain areas and jungles cannot reach or cannot reach quickly, the fog making range and the fog making direction can be more accurately judged, but the mature technology of aerial fog making is not adopted in the prior art, the aerial fog generating rate is low, the smoke generation amount is small, the applicability of a fog making agent is poor, the high-temperature atomization demand of a novel fog making agent cannot be met, the ground fog making system is compared with aerial fog making, maneuverability and flexibility are poor, and the requirement for quick fog making of complex terrains cannot be met.

Disclosure of Invention

The invention aims to avoid the defects of the prior art and provide the air adjustable spray angle vortex spraying mist making system which has high generation rate of smoke in the air and large smoke generation amount, adjusts the spray angle in the mist making process, changes the direction of generated smoke and meets different mist making requirements.

In order to achieve the purpose, the invention adopts the technical scheme that: a turbojet fog-making system with adjustable jet angle in the air comprises a flight platform, an undercarriage connected to the flight platform and a micro turbojet engine, wherein the flight platform comprises a supporting platform and an aircraft for driving the supporting platform to fly; the micro turbojet engine is arranged below the supporting platform through an engine supporting frame; the aerial flight platform can be reasonably selected according to the overall weight of the aerial fog system, the fog-making operation time and the like, and can be a rotor wing, a fixed wing or a helicopter; the micro turbojet engine can select the existing micro turbojet engine with different thrust levels according to the fog making requirement,

the supporting platform is provided with a mist making agent box, a mist making agent pump and a fuel oil tank for supplying oil to the micro turbojet engine, and the fuel oil tank is communicated with the micro turbojet engine through an engine fuel pump and a connecting pipeline; a spray nozzle outlet of the tail spray pipe of the micro turbojet engine is provided with a mist-making agent spray pipe, and the mist-making agent spray pipe is communicated with the mist-making agent box through a mist-making pipeline and a mist-making agent pump; the engine supporting frame is provided with an engine rotating device which drives the micro turbojet engine to rotate in a pitching manner;

the engine support frame is provided with a wireless control device which is respectively and electrically connected with the micro turbojet engine, the engine fuel pump, the mist making agent pump and the engine rotating device; the wireless control device is used for receiving wireless control signals, controlling an engine fuel pump to be matched with the starting and stopping of the micro turbojet engine to supply oil, controlling the fog making pump to spray fog making agents out of a fog making agent spray pipe, so that the fog making agents are heated by high-temperature and high-pressure gas at the position of a tail spray pipe nozzle to form fog, and simultaneously controlling the engine rotating device to start the micro turbojet engine in a horizontal state.

Furthermore, the engine rotating device comprises a servo steering engine, an upper rocker arm and a lower rocker arm, wherein one end of the upper rocker arm and one end of the lower rocker arm are rotating ends, and the other end of the upper rocker arm and the other end of the lower rocker arm are swinging ends; the swing ends of the upper rocker arm and the lower rocker arm are connected through a pull rod; the rudder stock of the servo steering engine is connected with the rotating end of the upper rocker arm, the rotating end of the lower rocker arm is connected with the rotating end of the engine clamping and rotating device, and the micro turbojet engine is arranged on the engine supporting rack through the engine clamping and rotating device; the servo steering engine is used for driving the swing end of the upper rocker arm to swing, the swing end of the lower rocker arm is driven to swing through the pull rod, and the rotating end of the lower rocker arm drives the micro turbojet engine to rotate in a pitching mode through the engine clamping and rotating device.

Further, engine chucking rotary device be in including fixed chucking the clamp on the miniature turbojet engine circumference casing be equipped with a pair of engaging lug on the clamp, the one end and the clamp of engaging lug link firmly, are equipped with the connecting card cover on the other end of engaging lug, are equipped with the rotation axis on the connecting card cover, the rotation axis is rotatable to be worn to establish the engine support rack on the connecting hole in, just the coupling end portion of rotation axis with the rotation end of engine rotating device's lower rocking arm be connected.

Furthermore, the fog-making agent spray pipe is a circular fog-making pipe matched with a tail spray pipe nozzle of the micro turbojet engine, at least two fog-making agent nozzles are communicated with the circular fog-making pipe, and a spray port of each fog-making agent nozzle obliquely points to the axial direction of the tail spray pipe nozzle of the micro turbojet engine.

Furthermore, the fog-making agent nozzles are uniformly distributed and communicated on the pipe bodies on the same peripheral surface of the annular fog-making agent spray pipe, and the inclination angle of the fog-making agent nozzles relative to the axis direction of the tail spray pipe nozzle is 15-60 degrees.

Furthermore, the fog-making agent spray pipe is welded and fixed or the mounting lug is fixed at the nozzle of the micro-engine.

Furthermore, the fuel oil tank is fixedly arranged on the mounting platform on the upper surface of the supporting platform, the fog-making agent tank is arranged on the mounting platform on the lower surface of the supporting platform, and the fuel oil tank and the fog-making agent tank are coaxially arranged.

Furthermore, the landing gear is a pair of U-shaped landing gears which are arranged correspondingly, two end parts of the opening side of each U-shaped landing gear are fixedly connected to the supporting platform, one end of each U-shaped landing gear, which is in contact with the ground, is provided with a pair of arc-shaped supporting feet, and the arc-shaped supporting feet are provided with anti-skidding sleeves; the width of the opening end of the U-shaped landing gear is smaller than that of the end, in contact with the ground, of the U-shaped landing gear. Design according to miniature turbojet engine's length etc. the undercarriage height that miniature turbojet engine of equidimension needs is also different, and the undercarriage still need have sufficient intensity in addition, guarantees unmanned aerial vehicle's safe take off and land.

Furthermore, an opening for adding fuel oil of the engine is arranged on the fuel oil tank, and a handle is arranged on the fuel oil tank on one side of the opening.

The invention has the beneficial effects that: the invention is on the unmanned aerial vehicle platform, mount the miniature turbojet engine, and increase supporting pedestal, rotate pitching equipment and control system, start the turbojet engine on the ground, make the engine enter the necessary working condition of fog making, then the flight platform rises to certain vertical height and flies to the area needing to be shielded, make fog making agent spray out from the annular spray tube finally, mix with high-temperature wake flow of turbojet engine, atomize, produce the smog of large size fast, because the high-temperature high-speed air current of jet nozzle of turbojet engine tail, atomize and fully mix the fog making agent fast, it is high to have fog making efficiency, the smoke output is large;

the rotary pitching device is used for horizontally starting the turbojet engine, so that the situation that the high-temperature air flow of the engine burns out the similar fuel oil circuit and the electric circuit when the turbojet engine is vertically started is prevented, when fog is required to be made, the engine rotates to the nozzle to be vertically downward, and fog making operation is carried out, and in addition, the rotary pitching device can also adjust the spraying angle of the generated smoke according to local meteorological information (such as wind speed and the like) so as to achieve a better fog making effect; the horizontal starting and the vertical mist making of the micro turbojet engine are realized, and thus, the damage of a fuel oil tank, a pipeline, an electrical system and the like caused by the upward turning back of high-temperature high-speed airflow when the tail nozzle of the engine is fixedly started downwards is avoided, and safety accidents are caused.

Because the invention adopts the maneuvering operation of the unmanned aerial vehicle, the unmanned aerial vehicle can quickly reach the target place for mist making, and can adopt a plurality of unmanned aerial vehicles for coordination operation according to the actual mist making requirement to form a mist making formation and improve the mist making efficiency.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the vertical structure of the nozzle of the micro turbojet engine;

FIG. 3 is a schematic view of the horizontal structure of the nozzle of the micro turbojet engine;

fig. 4 is a schematic structural view of the engine clamping and rotating device of the invention.

In the figure: 1. a flying platform; 2. a micro turbojet engine; 31. preparing an aerosol box; 32. a mist making pump; 33. a mist agent spray pipe; 34. a mist making pipeline box; 35. a mist agent nozzle; 4. a landing gear; 5. a fuel tank; 6. an engine support frame; 8. an engine rotating device; 81. a servo steering engine; 82. an upper rocker arm; 83. a pull rod; 84. a lower rocker arm; 9. an engine clamping and rotating device; 91. clamping a hoop; 92. connecting lugs; 93. connecting the clamping sleeve; 94. a rotating shaft; 95. connecting holes; 10. a wireless control device.

Detailed Description

The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.

Because the aerial fog-making system can be quicker in battle, can accurately finish the effective concealment of important military targets, and improve the survival capability of battle fields, and is particularly suitable for areas where motor vehicles such as mountain areas, jungles and the like can not reach or can not reach quickly, and can more accurately judge fog-making range, direction and the like, the invention provides an aerial fog-making device which has high aerial fog generating speed and large smoke generating amount and can meet the high-temperature atomization requirement of a novel fog-making agent, and the specific implementation mode is as follows:

example 1: as shown in fig. 1-4, an aerial adjustable-injection-angle turbojet mist-making system comprises a flight platform 1, an undercarriage 4 connected to the flight platform 1, and a micro turbojet engine 2, wherein the flight platform 1 comprises a support platform 11 and an aircraft 12 for driving the support platform 11 to fly; the micro turbojet engine 2 is arranged below the supporting platform 11 through an engine supporting frame 6; the undercarriage 4 is a pair of U-shaped undercarriages which are arranged correspondingly, two end parts of the opening side of each U-shaped undercarriage are fixedly connected to the supporting platform 11, one end, which is in contact with the ground, of each U-shaped undercarriage is provided with a pair of arc-shaped supporting feet 41, and the arc-shaped supporting feet 41 are provided with anti-skidding sleeves; the width of the opening end of the U-shaped landing gear is smaller than that of the end, in contact with the ground, of the U-shaped landing gear.

The supporting platform 11 is provided with an aerosol making tank 31, an aerosol making pump 32 and a fuel oil tank 5 for supplying oil to the micro turbojet engine 2, the fuel oil tank 5 is fixedly arranged on the mounting platform on the upper surface of the supporting platform 11, the aerosol making tank 31 is arranged on the mounting platform on the lower surface of the supporting platform 11, and the fuel oil tank 5 and the aerosol making tank 31 are coaxially arranged; an opening for adding fuel oil of an engine is arranged on the fuel oil tank 5, and a handle is arranged on the fuel oil tank 5 on one side of the opening; the fuel oil tank 5 is communicated with the micro turbojet engine 2 through an engine fuel pump and a connecting pipeline; a spray nozzle outlet of a tail spray pipe of the micro turbojet engine 2 is provided with a mist-making agent spray pipe 33, and the mist-making agent spray pipe 33 is communicated with a mist-making agent box 31 through a mist-making pipeline 34 and a mist-making agent pump 32; an engine rotating device 8 for driving the micro turbojet engine 2 to rotate in a pitching manner is arranged on the engine supporting frame 6;

the engine rotating device 8 comprises a servo steering engine 81, an upper rocker arm 82 and a lower rocker arm 84, wherein one end of the upper rocker arm 82 and one end of the lower rocker arm 84 are rotating ends, and the other end of the upper rocker arm 82 and the other end of the lower rocker arm 84 are swinging ends; the swinging ends of the two rocker arms of the upper rocker arm 82 and the lower rocker arm 84 are connected through a pull rod 83; the rudder stock of the servo steering engine 81 is connected with the rotating end of the upper rocker arm 82, the rotating end of the lower rocker arm 84 is connected with the rotating end of the engine clamping and rotating device 9, and the micro turbojet engine 2 is arranged on the engine support stand 6 through the engine clamping and rotating device 9; the servo steering engine 81 is used for driving the swinging end of the upper rocker arm 82 to swing, so that the swinging end of the lower rocker arm 84 is driven to swing through the pull rod 83, and the rotating end of the lower rocker arm 84 drives the micro turbojet engine 2 to rotate in a pitching mode through the engine clamping and rotating device 9. The engine clamping and rotating device 9 comprises a clamp 91 fixedly clamped on the circumferential shell of the micro turbojet engine 2, a pair of connecting lugs 92 are arranged on the clamp 91, one end of each connecting lug 92 is fixedly connected with the clamp 91, a connecting clamping sleeve 93 is arranged at the other end of each connecting lug 92, a rotating shaft 94 is arranged on each connecting clamping sleeve 93, the rotating shaft 94 is rotatably arranged in a connecting hole 95 in the engine supporting rack 6 in a penetrating mode, and the connecting end portion of the rotating shaft 94 is connected with the rotating end of the lower rocker arm 84 of the engine rotating device 8.

The mist making agent spray pipe 33 is a circular mist making pipe matched with the tail spray pipe nozzle of the micro turbojet engine 2, at least two mist making agent nozzles 35 are communicated with the circular mist making pipe, and the spray port of each mist making agent nozzle 35 is obliquely pointed to the axial direction of the tail spray pipe nozzle of the micro turbojet engine 2. The fog-making agent nozzles 35 are uniformly distributed and communicated on the pipe bodies on the same peripheral surface of the annular fog-making agent spray pipe 33, and the inclination angle of the fog-making agent nozzles 35 relative to the axial direction of the tail spray pipe nozzle is 15-60 degrees. The mist-making agent nozzle 33 is welded or fixed at the nozzle of the micro-engine 2 by mounting lugs.

The system also comprises a wireless control device 10 arranged on the engine support frame 6, wherein the wireless control device 10 is respectively and electrically connected with the micro turbojet engine 2, the engine fuel pump, the fog making pump 32 and the engine rotating device 8; the wireless control device 10 is used for receiving a wireless control signal, controlling an engine fuel pump to cooperate with the starting and stopping of the micro turbojet engine 2 to supply oil, controlling an aerosol making pump 32 to spray an aerosol making agent out of an aerosol making agent spray pipe 33, so that the aerosol making agent forms aerosol under the heating of high-temperature and high-pressure gas at a spray opening of a tail spray pipe, and simultaneously controlling an engine rotating device 8 to enable the micro turbojet engine 2 to be started in a horizontal state, and during spraying operation, the spray opening direction of the tail spray pipe of the micro turbojet engine 2 is rotated towards the ground until the micro turbojet engine 2 is vertical to the ground, so that the aerosol is vertically sprayed to the ground through the spray opening of the tail spray pipe.

The wireless control device 10 is provided with a transmitting unit which is in wireless matching with the wireless control device 10, the transmitting unit transmits a push rod control signal to the wireless control device 10 in a wireless mode, and after a receiving unit of the wireless control device 10 receives the signal transmitted by the transmitting unit, the push rod control signal with corresponding frequency is distributed to a corresponding steering engine execution circuit to control the steering engine to act, so that the servo steering engine 81 is controlled.

After the wireless control device 10 receives the control signal, firstly, the micro turbojet engine 2 is ensured to be horizontally arranged, then the micro turbojet engine 2 is started to enable the temperature at the tail nozzle to be increased, and after the aircraft drives the micro turbojet engine 2 to fly to an effective place, the aerosol making pump 32 is controlled to be started, the aerosol making agent is sent into the aerosol making agent nozzle 33, and the aerosol making agent is sprayed to the central position of the tail nozzle through the aerosol making agent nozzle 35, so that the spraying of a large amount of mist to the ground is realized. After the mist is made, the operation of the micro turbojet engine 2 and the mist making pump 32 is stopped, the direction of the micro turbojet engine 2 is turned back to the horizontal, and finally the aircraft lands and lands on the ground through the landing gear.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.