CN112498710A

CN112498710A - Unmanned aerial vehicle with supercharged fuel system

Info

Publication number: CN112498710A
Application number: CN202011509877.5A
Authority: CN
Inventors: 王海亮; 母玉洁; 马蕾; 司晟维; 卢亮; 尉文
Original assignee: Weihai Guangtai Airport Equipment Co Ltd
Current assignee: Weihai Guangtai Airport Equipment Co Ltd
Priority date: 2020-12-19
Filing date: 2020-12-19
Publication date: 2021-03-16

Abstract

The invention discloses an unmanned aerial vehicle with a supercharged fuel system, which comprises a body, wings and an empennage, wherein a fuel supply system and a control system are arranged in the body, and the fuel supply system is controlled by the control system; meanwhile, the substantial technical problem that the oil supply pipeline is air-locked is solved.

Description

Unmanned aerial vehicle with supercharged fuel system

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a supercharged fuel system.

Background

As is well known, a fixed-wing drone mainly comprises a body structure, a power system, a take-off and landing system, a flight control system, an airborne measurement and control system, an avionic system and the like. The oil supply system is an important component system of the fixed-wing unmanned aerial vehicle power system and is mainly used for storing fuel oil and conveying the fuel oil to an engine. The oil supply system mainly comprises components such as an oil tank, fuel oil, a valve, a pipeline and the like.

At present, unmanned aerial vehicle oil feeding system generally adopts hard formula box structure oil tank of monomer, and this type of oil tank has following problem:

1. adopt regular appearance oil tank usually, therefore hardly with the conformal of fixed wing unmanned aerial vehicle covering, consequently, unable make full use of unmanned aerial vehicle inner space storage fuel.

2. For an unmanned aerial vehicle, particularly a scaling unmanned aerial vehicle of a real airplane, mass characteristic parameters such as the gravity center, the inertia moment and the like of the unmanned aerial vehicle have certain requirements. Along with the consumption of fuel, especially when the unmanned aerial vehicle is in high maneuver flight states (rotation) such as excessive stall maneuver, tail spin, etc., the single-oil-tank oil supply system is difficult to meet the control requirement of the quality characteristic parameters of the unmanned aerial vehicle.

3. When high maneuvering flight is carried out, the special-shaped oil tank can be in any posture in the air, the heavy hammer in the oil tank can be exposed out of the oil surface and oil cannot be pumped out, or the oil supply of the oil tank is not smooth, so that the engine is flamed out. The high dynamic flight characteristic of unmanned aerial vehicle has proposed higher requirement to the reliability that the oil tank smoothly goes out oil.

Although the invention patent of CN 109573071 discloses a special-shaped distributed pressurized oil supply system for unmanned aerial vehicle, which solves the above technical problems, there are the following substantial technical problems: 1. because the flight lifting limit of the unmanned aerial vehicle is 12000m, under the condition that the air at the flight height is thin, the air supplied to the engine swirls in front of the engine to form turbulent flow, and the air cannot smoothly enter the engine, so that the surge phenomenon is formed in the running process of the engine, and the engine breaks down.

2. Under the condition that the flight ascending limit of the unmanned aerial vehicle is 12000m, the pressure of the external atmospheric environment is basically close to the saturated vapor pressure of aviation kerosene, the oil tank is not pressurized at the moment, the fuel in the oil tank boils, a large amount of gas in the oil tank is separated out, and further, the fuel pump of an engine cannot work, the problems of 'air lock' and the like of an oil supply pipeline are solved, although the technical problem of air lock can be solved by the technology disclosed by the patent, the air supply pipeline is connected with the first oil tank, the fuel of the No. 1 oil tank, the No. 2 oil tank, the No. 3 oil tank and the No. 4 oil tank is sequentially consumed in the operation process of the unmanned aerial vehicle, the No. 1 oil tank is positioned at the rear parts of the No. 3 oil tank and the No. 4 oil tank, the No. 2 oil tank is positioned at the front parts of the No. 3 oil tank and the No. 4 oil tank, when the No. 1 oil, leading to poor high dynamic flight stability of the unmanned aerial vehicle;

2. because the fuel oil tank is made of glass fiber reinforced plastic composite materials and the structure of the fuel oil tank is complex, the fuel oil tank cannot bear the overload of an airplane, the shaking load of fuel oil and the differential pressure load inside and outside the fuel oil tank.

3. Because the heavy hammer is arranged in each oil tank in the invention application, the structure is complex, and the load capacity of the unmanned aerial vehicle is greatly increased.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provide the unmanned aerial vehicle with the supercharged fuel system, which has the advantages of simple structure, smooth oil transportation, light weight, stable gravity center, high running performance and long service life.

The technical scheme adopted by the invention for solving the technical problems is as follows:

an unmanned aerial vehicle with a supercharged fuel system comprises a body 1, wherein wings 2 are symmetrically arranged on two sides of the body 1 respectively, a tail wing 3 is symmetrically arranged on the rear portion of the body 1, a fuel oil supply system and a control system are arranged in the body 1, the fuel oil supply system is controlled by the control system, and the unmanned aerial vehicle is characterized in that an engine air inlet rectifying device is arranged at the upper end of the rear portion of the body 1 and comprises an air inlet passage 5 and an air inlet rectifying cover 4, the air inlet end of the air inlet passage 5 is communicated with the air inlet rectifying cover 4, the air inlet rectifying cover 4 is oblate and is arranged towards the advancing direction of an airplane, the air inlet rectifying cover 4 is formed by gradually contracting in an arc shape towards the direction of the head from two sides of the body to the center, air entering the air inlet passage 5 is rectified by the air inlet rectifying cover 4, and then enters, the air inlet of the engine is smooth, and the failure caused by turbulent flow generated by unsmooth air inlet of the engine is prevented; meanwhile, the substantial technical problem that the 'air lock' occurs in the oil supply pipeline when the unmanned aerial vehicle flies to 12000m high altitude and the pressure of the external atmospheric environment and the saturated vapor pressure of aviation kerosene are basically close to each other is solved.

The invention relates to a pressurized fuel system which comprises at least three unit soft fuel tanks 7, an oil supply pipeline 8, at least two oil conveying pipelines 9, a gas introducing pipeline 10, a unit transverse partition frame 11, a flexible oil taking heavy hammer 12 and an engine 13,

unit transverse partition frames 11 are longitudinally fixed in the machine body 1 at intervals, unit soft oil tanks 7 are arranged between the adjacent unit transverse partition frames 11, the unit soft oil tanks 7 are fixedly clamped on the unit transverse partition frames 11,

the three unit soft oil tanks 7 comprise a first oil conveying tank 7-1, an oil collecting tank 7-2 and a second oil conveying tank 7-3 which are sequentially arranged, the two oil conveying pipelines 9 comprise a first oil conveying pipeline 9-1 and a second oil conveying pipeline 9-2, the oil collecting tank 7-2 is positioned at the gravity center position of a machine body, the bottom of the left side of the oil collecting tank 7-2 is communicated with the first oil conveying tank 7-1 through the first oil conveying pipeline 9-1, the bottom of the right side of the oil collecting tank is communicated with the second oil conveying tank 7-3 through the second oil conveying pipeline 9-2, a flexible oil taking heavy hammer is arranged in the oil collecting tank,

the oil inlet end of the oil supply pipeline 8 penetrates through the oil collecting tank 7-2 in a sealing way to be connected with a flexible oil taking heavy hammer 12 in the oil collecting tank 7-2, the oil outlet end is connected with an engine 13,

the air inlet end of the air guide pipeline 10 is connected with an air guide nozzle 18 on the shell of the engine 13, the air outlet end is respectively connected with the air inlet of the first oil transmission tank 7-1 and the air inlet at the top end of the second oil transmission tank 7-3,

when the unmanned aerial vehicle is supplied with oil, high-pressure gas in an engine shell is respectively injected into the first oil delivery tank 7-1 and the second oil delivery tank 7-3 through the bleed nozzle through the bleed pipe 10, so that fuel oil in the first oil delivery tank and the second oil delivery tank is simultaneously pressed into the oil collection tank 7-2, the oil collection tank 7-2 is always in an oil collection state under the condition that the air pressure in the oil collection tank, the air pressure in the first oil delivery tank and the air pressure in the second oil delivery tank are balanced with the external pressure, the flexible oil taking heavy hammer 12 is always immersed in the fuel oil, meanwhile, the gravity center of the aircraft is always kept near coordinates (2550, 0 and 0), and the stable operation of the unmanned aerial vehicle is obviously improved.

According to the invention, the bleed air pipeline 10 is provided with the flow limiting valve 15 and the one-way valve 14, so that the gas in the first oil delivery tank 7-1 and the second oil delivery tank 7-3 is prevented from flowing back into the engine 13 in the state that the airplane fiercely closes the accelerator and the like, and the safe and stable running of the unmanned aerial vehicle is ensured.

The fuel filter 16 can be arranged on the fuel supply pipeline 8, so that the cleanliness of fuel entering an engine is guaranteed.

The height and the width of the oil collecting tank 7-2 are respectively smaller than the first oil conveying tank 7-1 and the second oil conveying tank 7-3, and the oil collecting tank is clamped on the unit transverse partition frame 11, so that the unit transverse partition frame 11 can bear the impact load of sailing.

The unit soft oil tank is made of TPU materials, and the outer molded surfaces of the first oil conveying tank 7-1 and the second oil conveying tank 7-3 and the inner molded surface of the machine body are in shape-preserving mode so as to ensure that the oil tanks are sealed under a normal use environment; and can bear the overload of the airplane, the shaking load of the fuel oil and the differential pressure load inside and outside the oil tank.

The invention can also be fixedly provided with a longitudinal supporting frame 17 in the longitudinal direction of the axle center of the machine body 1, and the longitudinal supporting frame 17 is fixedly connected with the unit transverse partition frame 11 so as to further achieve the effect of bearing sailing impact load.

The invention has the advantages of simple structure, smooth oil transportation, light weight of the whole machine, stable gravity center, high running performance, long service life and the like.

Drawings

Fig. 1 is a schematic structural diagram of an embodiment of the present invention.

Fig. 2 is a schematic view of the cut-away internal structure of fig. 1 (engine not shown).

Fig. 3 is a schematic structural view of the engine intake air rectifying device in fig. 1.

FIG. 4 is a functional block diagram of a pressurized fuel system of the present invention.

Reference numerals: the device comprises a body 1, wings 2, a tail wing 3, an air inlet fairing 4, an air inlet channel 5, an air outlet 6, a unit soft oil tank 7, a first oil delivery tank 7-1, an oil collection tank 7-2, a second oil delivery tank 7-3, an oil supply pipeline 8, at least two oil delivery pipelines 9, a first oil delivery pipeline 9-1, a second oil delivery pipeline 9-2, an air entraining pipeline 10, a unit transverse partition frame 11, a flexible oil taking heavy hammer 12, an engine 13, a one-way valve 14, a flow limiting valve 15, a fuel oil filter 16, a longitudinal support frame 17 and an air entraining nozzle 18.

Detailed Description

The invention is described below with reference to the accompanying drawings and examples.

As shown in the attached

drawings

1, 2 and 3, an unmanned aerial vehicle with a supercharged fuel system comprises a body 1, wherein wings 2 are symmetrically arranged on two sides of the body 1 respectively, empennages 3 are symmetrically arranged on the rear portion of the body 1, a fuel supply system and a control system are arranged in the body 1, the fuel supply system is controlled by the control system, the control system is the prior art and is not repeated, and the unmanned aerial vehicle is characterized in that an engine air inlet fairing is arranged at the upper end of the rear portion of the body 1 and comprises an air inlet duct 5 and an air inlet fairing 4, the air inlet end of the air inlet duct 5 is communicated with the air inlet fairing 4, the air inlet of the air inlet fairing 4 is oblate and is arranged towards the advancing direction of the aircraft, the air inlet fairing 4 is formed by gradually contracting and extending in an arc shape towards the direction of the head from two sides of the body, and rectifies air entering the air inlet duct, then enters the front end of an engine 13 through an air inlet 5, so that the air inlet of the engine is smooth, and the failure caused by the turbulent flow generated by the unsmooth air inlet of the engine is prevented; meanwhile, the substantial technical problem that the 'air lock' occurs in the oil supply pipeline when the unmanned aerial vehicle flies to 12000m high altitude and the pressure of the external atmospheric environment and the saturated vapor pressure of aviation kerosene are basically close to each other is solved.

Example (b): as shown in figure 4, the invention symmetrically installs a first oil delivery tank 7-1, an oil collection tank 7-2 and a second oil delivery tank 7-3 between unit transverse bulkheads at two sides of a longitudinal support frame in the inner cavity of the unmanned aerial vehicle body, the oil collection tank is arranged at the gravity center position of the unmanned aerial vehicle body, so that a flexible oil taking heavy hammer in the oil collection tank at the left side of the longitudinal support frame supplies oil for a left engine, a flexible oil taking heavy hammer in the oil collection tank at the right side supplies oil for a right engine,

during flight, fuel oil in the first fuel delivery tank 7-1 and the second fuel delivery tank 7-3 on two sides of the longitudinal support frame is simultaneously input into the oil collection tank 7-2 through the first oil delivery pipeline 9-1 and the second oil delivery pipeline 9-2 under the pressurization effect of the air guide pipeline 10, so that the fuel oil in the oil collection tank 7-2 is basically in a full oil and pressure stabilizing state in the flight process, the substantial technical problem of 'air lock' of an oil supply pipeline is solved, and the flexible oil taking heavy hammers 12 and the oil supply pipeline 8 in the oil collection tank 7-2 on two sides of the longitudinal support frame supply oil to respective engines 13, so that independent oil supply is ensured;

in the oil supply process, the oil collecting tank 7-2 is positioned at the gravity center position of the airplane, and the oil in the first oil conveying tank 7-1 and the second oil conveying tank 7-3 at the front end and the rear end is simultaneously input into the oil collecting tank through the oil conveying pipeline, so that the gravity center stability of the unmanned aerial vehicle is remarkably improved, and the unmanned aerial vehicle is basically kept near coordinates (2550, 0, 0) in the flight process;

in the flying process, gas is guided into the air inlet end of the engine through the air inlet fairing through the air inlet channel and smoothly enters the engine, so that the problem that the air inlet of the engine is not smooth to form turbulent flow is avoided, and the surging phenomenon of the engine in the running process is solved.

When the fuel oil in the first fuel delivery tank and the second fuel delivery tank is completely delivered to the oil collection tank under the pressure increase of the bleed air pipeline, the fuel oil in the oil collection tank begins to be consumed until the fuel oil is exhausted.

Claims

1. An unmanned aerial vehicle with a pressurized fuel system, comprising a fuselage, two sides of the fuselage are respectively provided with wings symmetrically, the rear of the fuselage is symmetrically provided with a tail, and a fuel supply is provided in the fuselage. Oil system and control system, the fuel oil supply system is controlled by the control system, and it is characterized in that the upper end of the rear part of the fuselage is provided with an engine air intake fairing device, which includes an air intake duct, an air intake fairing, the air intake The air inlet end is communicated with the air inlet fairing, and the air outlet end is communicated with the engine air inlet. The air inlet fairing is in the shape of an oblate shape and is arranged toward the traveling direction of the aircraft. The air inlet fairing is composed of The sides of the fuselage gradually shrink and extend in an arc toward the center toward the nose.

2. The unmanned aerial vehicle with a pressurized fuel system according to claim 1, wherein the pressurized fuel system of the present invention is composed of at least three units of a soft oil tank, an oil supply pipeline, and at least two oil pipelines. It is composed of road, air bleed pipeline, unit transverse bulkhead, flexible oil taking hammer and engine.

A unit horizontal partition frame is fixed at a longitudinal interval in the fuselage, a unit soft oil tank is arranged between the adjacent unit horizontal partition frames, and the unit soft oil tank is fixed on the unit horizontal partition frame,

The three unit soft fuel tanks include a first fuel tank, a collection tank and a second fuel tank arranged in sequence, the two fuel pipelines include a first fuel pipeline and a second fuel pipeline, and the fuel collector is located at the center of gravity of the fuselage. position, the bottom of the left side of the oil collecting tank is connected with the first oil delivery tank through the first oil delivery pipeline, and the bottom of the right side is connected with the second fuel delivery tank through the second oil delivery pipeline, and the oil collecting tank is provided with a flexible oil taking weight ,

The oil inlet end of the oil supply pipeline is sealed through the oil collecting tank and is connected with the flexible oil taking weight in the oil collecting tank, and the oil outlet end is connected with the engine,

The air inlet end of the air bleed pipeline is connected with the air bleed nozzle on the engine casing, and the air outlet end is respectively connected to the air inlet of the first fuel tank and the air inlet of the top of the second fuel tank.

3 . The unmanned aerial vehicle with a pressurized fuel system according to claim 2 , wherein a one-way valve and a restrictor valve are provided on the air bleed pipeline. 4 .

4. A drone with a pressurized fuel system according to claim 3, characterized in that a fuel filter is provided on the fuel supply pipeline.

5. A kind of unmanned aerial vehicle with pressurized fuel system according to claim 2 or 3 or 4, it is characterized in that the height and width of described oil collecting tank are respectively smaller than the first fuel tank and the second fuel tank, and the On unit transverse bulkheads.

6. A kind of unmanned aerial vehicle with pressurized fuel system according to claim 5, is characterized in that described unit soft fuel tank is made of TPU material, and described first fuel tank and second fuel tank have the same outer shape as the one described above. The inner surface of the fuselage is guaranteed.

7. The unmanned aerial vehicle with a pressurized fuel system according to claim 6, characterized in that a longitudinal support frame is fixed longitudinally on the axis of the fuselage, and the longitudinal support frame is fixedly connected with the unit transverse partition frame .