阅读说明：本技术 一种无人机高空低温可靠点火结构 (High-altitude low-temperature reliable ignition structure of unmanned aerial vehicle ) 是由 田颖 王雨龙 蔡文哲 余海生 邵伏永 于 2020-11-25 设计创作，主要内容包括：本发明公开了一种无人机高空低温可靠点火结构,其包括：燃油增温装置A和预燃室B两部分,燃油增温装置A通过对流向预燃室B的低温燃油进行加热,至目标温度后,预燃室点火进而点燃主燃烧室,实现无人机高空、低温点火。本发明用于预燃室点火时对通过流向预燃室的低温燃油进行加热,将燃油增温至目标温度,使预燃室在高空、低温环境下可靠点火,进而保证主燃室成功点火,达到提高无人机在高空、低温环境可靠起动的目的,本装置具有结构简单、成本低、重量轻、加热快等优点。(The invention discloses a high-altitude low-temperature reliable ignition structure of an unmanned aerial vehicle, which comprises: the fuel oil heating device A heats low-temperature fuel oil flowing to the precombustion chamber B through convection, and after the low-temperature fuel oil reaches a target temperature, the precombustion chamber ignites to further ignite the main combustion chamber, so that high-altitude and low-temperature ignition of the unmanned aerial vehicle is realized. The device is used for heating low-temperature fuel flowing to the precombustion chamber when the precombustion chamber is ignited, and heating the fuel to a target temperature, so that the precombustion chamber can be reliably ignited in a high-altitude and low-temperature environment, the main combustion chamber can be further ensured to be successfully ignited, and the purpose of improving the reliable starting of the unmanned aerial vehicle in the high-altitude and low-temperature environment is achieved.)

1. The utility model provides an unmanned aerial vehicle high altitude low temperature reliable ignition structure which characterized in that includes: the fuel oil heating device A heats low-temperature fuel oil flowing to the precombustion chamber B through convection, and after the low-temperature fuel oil reaches a target temperature, the precombustion chamber ignites to further ignite the main combustion chamber, so that high-altitude and low-temperature ignition of the unmanned aerial vehicle is realized.

2. The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle as claimed in claim 1, wherein the fuel oil heating device a comprises an electric heating core assembly and a heating pipe assembly, one end of the electric heating core assembly is installed in the heating pipe assembly, and the other end of the electric heating core assembly is externally connected with a heating power supply; an oil inlet filler neck and an oil outlet filler neck are arranged on the heating pipe assembly, the oil inlet filler neck feeds fuel oil into the heating pipe assembly, and the fuel oil flows out of the oil outlet filler neck to the prechamber B after being heated.

3. The high altitude low temperature reliable ignition structure of unmanned aerial vehicle of claim 2, characterized in that the heating pipe sub-assembly includes tubular casing, and the oil inlet filler neck is fixed in tubular casing one end through welding, and the oil outlet filler neck is fixed on tubular casing lateral wall through welding, and the tubular casing other end penetrates electric heating core sub-assembly.

4. The high altitude low temperature reliable ignition structure of unmanned aerial vehicle of claim 3, characterized in that, the electric heating core sub-assembly includes electric heating core 1 and electric heating wire 7, and electric heating core 1 is packed into the tubular casing and one end stretches out outside the tubular casing, and electric heating wire 7 welds on electric heating core 1 inside the tubular casing.

5. The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle as claimed in claim 4, wherein the electric heating wire 7 is connected with the inner wall of the tubular shell through threads, a heat insulation spacer 6 is arranged between the electric heating wire and the tubular shell, and the heat insulation spacer 6 is fixedly bonded with the inner wall of the tubular shell.

6. The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle as claimed in claim 5, wherein the electric heating core 1 is in threaded connection with the other end of the tubular shell, a plurality of stages of mounting steps are arranged at the joint, and heat insulation gaskets are arranged on the mounting steps.

7. The high altitude low temperature reliable ignition structure of unmanned aerial vehicle of claim 6, characterized in that, the thermal insulating gasket is provided with three layers, and the outermost layer is located at tubular casing tip terminal surface.

8. The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle as claimed in claim 7, wherein the end of the electric heating core 1 extending out of the tubular shell is provided with threads, and when the temperature increasing device works, the positive electrode of the power supply is connected with the electric heating core 1 through the threads, and the negative electrode of the power supply is connected with the heating pipe assembly.

9. The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle as claimed in claim 8, wherein the fuel oil temperature increasing device A works at an ambient temperature of-55 ℃ to +55 ℃, the fuel oil temperature of-40 ℃ to 0 ℃, the ignition starting time of the engine does not exceed 15s, and the temperature increasing rated voltage: DC 28V; rated current: not greater than 30A.

10. Use of the high altitude low temperature reliable ignition structure of unmanned aerial vehicle according to any one of claims 1-9 in the technical field of turbine engine.

Technical Field

The invention belongs to the technical field of turbine engines, and relates to an unmanned aerial vehicle high-altitude low-temperature reliable ignition structure.

Background

The aircraft faces a series of problems of low air pressure and temperature, low oil injection flow under the condition of the same oil-gas ratio, poor atomization quality, low combustion efficiency, narrow ignition range and the like when working and igniting on plateau, so that measures must be taken to ensure successful ignition in a high altitude state.

The high-altitude low-temperature ignition of the existing aircraft generally adopts an air oxygen supplement mode and an igniter capacity increasing mode, such as a firework igniter or two sets of igniters for simultaneous ignition, fuel oil with good volatility for ignition and the like to improve the air ignition capacity.

The oxygen supplement scheme improves the oxygen concentration of the precombustion chamber by supplying oxygen to the precombustion chamber, thereby achieving the purpose of improving the ignition capacity of the precombustion chamber.

By utilizing the high energy of the pyrotechnic igniter, the ignition nozzle is replaced by the pyrotechnic igniter, so that the ignition capability of the engine can be obviously improved.

In addition, the experiment research on the high-altitude low-pressure ignition performance of the aircraft by warming the fuel oil by people such as Chennengkun and Zhou Yan of Beijing aerospace university shows that the air ignition range of the engine can be obviously expanded by adopting the fuel oil warming measure.

The oxygen supplement scheme is limited by the weight and the space structure of the engine, an oxygen tank is required, the oxygen supplement amount is limited, and once the oxygen is exhausted, the engine is not ignited, and the ignition fails.

The pyrotechnic ignition scheme is high in cost, tens of thousands and hundreds of thousands of yuan for a single igniter, and is not suitable for wide popularization under the current low-cost and large-trend turbine engine.

Disclosure of Invention

Objects of the invention

The purpose of the invention is: the utility model provides an unmanned aerial vehicle high altitude low temperature reliably ignites the structure, thereby can realize fast with fuel from low temperature heating to normal atmospheric temperature state realization engine smooth ignition.

(II) technical scheme

In order to solve the technical problem, the invention provides an unmanned aerial vehicle high-altitude low-temperature reliable ignition structure, which comprises: the fuel oil heating device A heats low-temperature fuel oil flowing to the precombustion chamber B through convection, and after the low-temperature fuel oil reaches a target temperature, the precombustion chamber ignites to further ignite the main combustion chamber, so that high-altitude and low-temperature ignition of the unmanned aerial vehicle is realized.

Preferably, the fuel oil temperature increasing device a comprises an electric heating core assembly and a heating pipe assembly, one end of the electric heating core assembly is installed in the heating pipe assembly, and the other end of the electric heating core assembly is externally connected with a heating power supply; an oil inlet filler neck and an oil outlet filler neck are arranged on the heating pipe assembly, the oil inlet filler neck feeds fuel oil into the heating pipe assembly, and the fuel oil flows out of the oil outlet filler neck to the prechamber B after being heated.

Preferably, the heating tube assembly comprises a tubular shell, the oil inlet filler neck is fixed at one end of the tubular shell by welding, the oil outlet filler neck is fixed on the side wall of the tubular shell by welding, and the other end of the tubular shell penetrates into the electric heating core assembly.

Preferably, the electric heating core assembly comprises an electric heating core 1 and an electric heating wire 7, the electric heating core 1 is installed in the tubular shell, one end of the electric heating wire extends out of the tubular shell, and the electric heating wire 7 is welded on the electric heating core 1 in the tubular shell.

Preferably, the electric heating wire 7 is connected with the inner wall of the tubular shell through threads, a heat insulation spacer 6 is arranged between the electric heating wire and the inner wall of the tubular shell, and the heat insulation spacer 6 is fixedly bonded with the inner wall of the tubular shell.

Preferably, the electric heating core 1 is connected with the other end of the tubular shell through threads, a multi-stage mounting step is arranged at the joint, and a heat insulation gasket is arranged on the mounting step.

Preferably, the insulating mat is provided with three layers, the outermost layer being located at the end face of the tubular casing end.

Preferably, the end of the electric heating core 1 extending out of the tubular shell is provided with threads, when the heating device works, the positive electrode of the power supply is connected with the electric heating core 1 through the threads, and the negative electrode of the power supply is connected with the heating pipe assembly.

Preferably, the environment temperature of the fuel oil temperature increasing device A is-55 ℃ to +55 ℃, the fuel oil temperature is-40 ℃ to 0 ℃, the ignition starting time of the engine is not more than 15s, and the temperature increasing rated voltage is as follows: DC 28V; rated current: not greater than 30A.

(III) advantageous effects

The high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle, which is provided by the technical scheme, is used for heating low-temperature fuel oil flowing to the precombustion chamber when the precombustion chamber is ignited, heating the fuel oil to a target temperature, so that the precombustion chamber can be reliably ignited in a high-altitude and low-temperature environment, further ensuring that the main combustion chamber is successfully ignited, and achieving the purpose of improving the reliable starting of the unmanned aerial vehicle in the high-altitude and low-temperature environment.

Drawings

Fig. 1 is a schematic diagram of the ignition structure of the present invention.

Fig. 2 is a schematic structural view of the fuel oil temperature increasing device of the present invention.

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, the high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle comprises a fuel oil temperature increasing device A and a precombustion chamber B, wherein the fuel oil temperature increasing device A heats low-temperature fuel oil flowing to the precombustion chamber B, and after the low-temperature fuel oil reaches a target temperature, the precombustion chamber ignites to further ignite a main combustion chamber, so that the purpose of reliable ignition of the unmanned aerial vehicle in a high-altitude low-temperature environment is achieved.

Referring to fig. 2, the fuel oil temperature increasing device a includes an electric heating core assembly and a heating pipe assembly, one end of the electric heating core assembly is installed in the heating pipe assembly, and the other end is externally connected with a heating power supply; an oil inlet filler neck and an oil outlet filler neck are arranged on the heating pipe assembly, the oil inlet filler neck feeds fuel oil into the heating pipe assembly, and the fuel oil flows out of the oil outlet filler neck to the prechamber B after being heated.

The heating pipe assembly comprises a tubular shell, an oil inlet filler neck is fixed at one end of the tubular shell through welding, an oil outlet filler neck is fixed on the side wall of the tubular shell through welding, and the other end of the tubular shell penetrates into the electric heating core assembly.

The electric heating core assembly comprises an electric heating core 1 and an electric heating wire 7, wherein the electric heating core 1 is arranged in the tubular shell, one end of the electric heating core extends out of the tubular shell, and the electric heating wire 7 is welded on the electric heating core 1 in the tubular shell. The electric heating wire 7 is connected with the inner wall of the tubular shell through threads, a heat insulation spacer 6 is arranged between the electric heating wire and the inner wall of the tubular shell, and the heat insulation spacer 6 and the inner wall of the tubular shell are fixedly bonded. The electric heating core 1 is connected with the other end of the tubular shell through threads, a plurality of stages of installation steps are arranged at the joint, and heat insulation gaskets are arranged on the installation steps.

When the heating device works, the positive electrode of the power supply is connected with the right end part of the electric heating core 1 through threads, the negative electrode of the power supply is connected with the heating pipe assembly, and fuel oil fed into the oil inlet connecting pipe nozzle is heated by the electric heating wire 7 and then flows out of the upper oil outlet connecting pipe nozzle to flow to the pre-combustion chamber.

In this embodiment, the temperature increasing device should have the capability of realizing smooth ignition of the engine under typical conditions, wherein the ambient temperature is-55 ℃ to +55 ℃, and the fuel temperature is-40 ℃ to 0 ℃.

The ignition start time of the engine does not exceed 15 s.

Temperature rise rated voltage: DC 28V; rated current: not greater than 30A.

According to the technical scheme, the high-altitude low-temperature reliable ignition structure of the unmanned aerial vehicle can effectively improve the ignition capability of an engine, low-temperature fuel oil is introduced into the fuel oil temperature increasing device before the fuel oil enters the pre-combustion chamber, and electric energy is converted into heat energy of the fuel oil by using the resistance value of the electric heating wire, so that the low-temperature fuel oil is heated to a normal temperature state, and the purpose of improving the ignition capability of the combustion chamber is further achieved. Compared with the existing scheme of oxygen supplement and ignition energy increase, the invention has the advantages of low cost, simple structure, high heating efficiency and repeated use, and makes up for the defects of the prior art.

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.