Double-engine flying wing layout aircraft exhaust system and method for improving engine extraction power

Abstract

The invention belongs to the technical field of aerospace, and particularly relates to a double-engine flying wing layout aircraft exhaust system and method for improving engine extraction power. According to the exhaust system, the engine extraction power output end of a first engine is connected with a confrontation task system, and the first engine is connected with a nitrogen making system through a nitrogen making air entraining pipeline and connected with an exhaust port in the surface of an engine body through a first air discharging pipeline; the engine extraction power output end of the second engine is connected with other electric equipment except the confrontation task system on the aircraft, and the second engine is connected with an exhaust port in the surface of the aircraft body through a second deflation pipeline. The air entraining amount of the air compressor is increased, meanwhile, redundant air is discharged out of the machine body through the air discharging pipeline, the engine extraction power can be improved within a short time, and then the whole-machine electricity utilization requirement is met; the system does not cause adverse effects on other systems of the aircraft, and can be popularized to aircrafts with similar layouts for verification.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, and particularly relates to a twin-engine flying wing layout aircraft exhaust system and method for improving the extraction power of an engine. Background Art

[0002] The all-aircraft electrical energy is an important indicator for aircraft design and needs to meet the electrical energy requirements at all stages of aircraft flight. The extraction power of the engine is related to the engine speed. During the glide phase, the engine is in the idle state and the extraction power is relatively low.

[0003] Traditional twin-engine aircraft are generally statically stable aircraft. When encountering gusts or turbulence during the glide phase, the control surfaces will not deflect rapidly in a short time, and there is no problem of insufficient extraction power. Most twin-engine flying wing layout unmanned aircraft are statically unstable aircraft. When encountering gusts or turbulence during the glide phase, due to the need for stability augmentation, the control surfaces will deflect rapidly in a short time, the power consumption demand will increase rapidly, and the demand for the extraction power of the engine is relatively large. As a result, there will be a problem that the extraction power of the engine does not meet the all-aircraft electrical energy requirements. In addition, when encountering gusts or turbulence, the equipment performing countermeasure tasks also has a higher demand for the extraction power of the engine, and there will also be a problem that the extraction power of the engine does not meet the all-aircraft electrical energy requirements.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least mitigate at least one of the above-mentioned defects of the prior art. Summary of the Invention

[0005] The purpose of this application is to provide a twin-engine flying wing layout aircraft exhaust system and method for improving the extraction power of an engine to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is as follows:

[0007] The first aspect of this application provides a twin-engine flying wing layout aircraft exhaust system for improving the extraction power of an engine. The twin-engine flying wing layout aircraft has a first engine and a second engine. Both the first engine and the second engine draw air through their respective compressors and exhaust through their respective nozzles, including:

[0008] The engine extraction power output end of the first engine is connected to the countermeasure task system. The first engine is connected to the nitrogen generation system through a nitrogen generation air duct and is connected to the air exhaust port on the aircraft body surface through a first exhaust duct;

[0009] The engine extraction power output end of the second engine is connected to other electrical equipment on the aircraft except the countermeasure task system. The second engine is connected to the air exhaust port on the aircraft body surface through a second exhaust duct.

[0010] In at least one embodiment of the present application, the countermeasure mission system includes a radar device and an optoelectronic device.

[0011] In at least one embodiment of the present application, other electrical devices on the aircraft except the countermeasure mission system include a control surface deflection device.

[0012] In at least one embodiment of the present application, valves are provided on both the first exhaust gas pipeline and the second exhaust gas pipeline.

[0013] In at least one embodiment of the present application, an exhaust port is opened at the lowest point of the upper surface of the fuselage to ensure that the exhaust port can be blocked forward when the aircraft is in the cruise state.

[0014] The second aspect of the present application provides an exhaust method for a twin-engine flying wing layout aircraft to improve the extracted power of the engine. Based on the twin-engine flying wing layout aircraft exhaust system for improving the extracted power of the engine as described above, it includes:

[0015] In the flight phase where the extracted power of the engine meets the electrical demand of the whole aircraft:

[0016] The extracted power of the first engine is used to supply power to the countermeasure mission system. The first engine draws air through the compressor. Part of the gas discharged by the first engine is discharged through the nozzle, and the other part of the gas is supplied to the nitrogen generation system through the nitrogen generation air intake pipeline. The first exhaust gas pipeline does not exhaust.

[0017] The extracted power of the second engine is used to supply power to other electrical devices on the aircraft except the countermeasure mission system. The second engine draws air through the compressor. The gas discharged by the second engine is discharged through the nozzle, and the second exhaust gas pipeline does not exhaust.

[0018] In the flight phase where the extracted power of the engine cannot meet the electrical demand of the whole aircraft:

[0019] When the extracted power of the first engine cannot meet the electrical demand of the countermeasure mission system, increase the air intake volume of the compressor of the first engine. Part of the gas discharged by the first engine is discharged through the nozzle, part of the gas is supplied to the nitrogen generation system through the nitrogen generation air intake pipeline, and part of the gas is discharged outside the fuselage through the first exhaust gas pipeline.

[0020] When the extracted power of the second engine cannot meet the electrical demand of other electrical devices on the aircraft except the countermeasure mission system, increase the air intake volume of the compressor of the second engine. Part of the gas discharged by the second engine is discharged through the nozzle, and the other part of the gas is discharged outside the fuselage through the second exhaust gas pipeline.

[0021] The invention has at least the following beneficial technical effects:

[0022] The exhaust system of a twin-engine flying wing layout aircraft for improving the engine extraction power of the present application can increase the compressor air extraction volume and discharge the excess gas outside the aircraft body through the bleed pipeline, thereby improving the engine extraction power in a short time and meeting the electrical power demand of the whole aircraft. This system will not have an adverse impact on other aircraft systems and can be extended to similar layout aircraft for verification. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 FIG. is a schematic diagram of the exhaust system of a twin-engine flying wing layout aircraft for improving the engine extraction power according to an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0024] To make the objectives, technical solutions, and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present application and should not be construed as a limitation of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0025] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the scope of protection of the present application.

[0026] The following will be further described in detail with reference to the attached Figure 1 for the present application.

[0027] The first aspect of the present application provides an exhaust system for a twin-engine flying wing layout aircraft for improving the engine extraction power. The twin-engine flying wing layout aircraft has a first engine and a second engine. Each engine draws air through its own compressor and discharges exhaust through its own nozzle. This system configures the engine extraction power of each engine and improves the exhaust mode of the engine.

[0028] Specifically, as Figure 1As shown, the engine extraction power output end of the first engine is connected to the countermeasure mission system to supply power to the countermeasure mission system; the first engine is connected to the nitrogen generation system through a nitrogen generation air intake pipeline and to the air exhaust port on the body surface through a first exhaust pipeline. The first engine draws air through a compressor. In addition to exhausting through a nozzle, the first engine also provides nitrogen generation air intake for the nitrogen generation system, and the excess gas can also be discharged outside the body through the first exhaust pipeline.

[0029] The engine extraction power output end of the second engine is connected to other electrical equipment on the aircraft except the countermeasure mission system, and the second engine is connected to the air exhaust port on the body surface through a second exhaust pipeline. The second engine draws air through a compressor. In addition to exhausting through a nozzle, the excess gas of the second engine can also be discharged outside the body through the second exhaust pipeline.

[0030] In a preferred embodiment of the present application, the engine extraction power is provided by the first engine for the countermeasure mission system, and the engine extraction power is provided by the second engine for the rudder surface deflection device. The countermeasure mission system includes radar equipment and optoelectronic equipment, and other electrical equipment on the aircraft except the countermeasure mission system includes the rudder surface deflection device. When there is a problem of insufficient engine extraction power, only the extraction power of the corresponding engine needs to be increased.

[0031] In a preferred embodiment of the present application, valves are provided on both the first exhaust pipeline and the second exhaust pipeline to realize the regulation of the corresponding pipelines.

[0032] In a preferred embodiment of the present application, the design of the air exhaust port on the upper surface of the body is carried out. The lowest point is found on the upper surface of the body, and an air exhaust port is opened at the lowest point on the upper surface of the body to ensure that the exhaust port can be blocked forward when the aircraft is in the cruise state.

[0033] Based on the above exhaust system of a twin-engine flying wing layout aircraft for improving engine extraction power, the second aspect of the present application provides a method for exhausting a twin-engine flying wing layout aircraft for improving engine extraction power, including:

[0034] In the flight stage when the engine extraction power meets the electrical demand of the whole aircraft:

[0035] The engine extraction power of the first engine is used to supply power to the countermeasure mission system. The first engine draws air through a compressor. Part of the gas discharged by the first engine is exhausted through a nozzle, and the other part of the gas supplies gas to the nitrogen generation system through the nitrogen generation air intake pipeline, and the first exhaust pipeline does not exhaust;

[0036] The engine extraction power of the second engine is used to supply power to other electrical equipment on the aircraft except the countermeasure mission system. The second engine draws air through a compressor. The gas discharged by the second engine is exhausted through a nozzle, and the second exhaust pipeline does not exhaust;

[0037] During the flight phase when the engine extraction power cannot meet the electricity demand of the whole aircraft:

[0038] When the engine extraction power of the first engine cannot meet the electricity demand of the countermeasure mission system, increase the compressor bleed air volume of the first engine. Part of the gas discharged from the first engine is discharged through the nozzle, part of the gas is supplied to the nitrogen generation system through the nitrogen generation bleed air pipeline, and part of the gas is discharged outside the aircraft through the first bleed air pipeline.

[0039] When the engine extraction power of the second engine cannot meet the electricity demand of other electrical equipment on the aircraft except the countermeasure mission system, increase the compressor bleed air volume of the second engine. Part of the gas discharged from the second engine is discharged through the nozzle, and the other part of the gas is discharged outside the aircraft through the second bleed air pipeline.

[0040] For the exhaust method of the twin-engine flying wing layout aircraft that improves the engine extraction power in this application, when the aircraft encounters gusts or turbulence, if the engine extraction power cannot meet the requirements of the countermeasure mission system, by increasing the compressor bleed air volume and discharging the excess gas outside the aircraft through the bleed air pipeline at the same time, the engine extraction power can be increased in a short time, so as to meet the electricity demand of the countermeasure mission system. When the aircraft encounters gusts or turbulence, if the engine extraction power cannot meet the requirements of the control surface deflection equipment, by increasing the compressor bleed air volume and discharging the excess gas outside the aircraft through the bleed air pipeline at the same time, the engine extraction power can be increased in a short time, so as to meet the electricity demand of the control surface deflection equipment.

[0041] For the exhaust system and method of the twin-engine flying wing layout aircraft that improves the engine extraction power in this application, by increasing the compressor bleed air volume and discharging the excess gas outside the aircraft through the bleed air pipeline at the same time, the extraction power in the engine idle state can be increased, and the problem that the extraction power of the engine in the glide phase of the twin-engine flying wing layout aircraft cannot meet the electricity demand of the whole aircraft can be solved.

[0042] The above is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in this application should be covered by the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claims.

Claims

1. An exhaust system for a twin-engine flying wing aircraft for improving engine power extraction, wherein the twin-engine flying wing aircraft has a first engine and a second engine, wherein the first engine and the second engine are both bleed by their respective compressors and exhausted by their respective nozzles, wherein: include: The engine power extraction output end of the first engine is connected to the countermeasure mission system, the first engine is connected to the nitrogen production system through a nitrogen production bleed pipe, and is connected to the exhaust port on the surface of the fuselage through a first exhaust pipe; The engine power extraction output end of the second engine is connected to other electrical equipment on the aircraft except the countermeasure mission system, and the second engine is connected to the exhaust port on the surface of the aircraft through a second exhaust pipe.

2. The exhaust system for twin-engine flying wing aircraft with improved engine power extraction according to claim 1, characterized in that: The countermeasure mission system includes radar equipment and optoelectronic equipment.

3. The exhaust system for twin-engine flying wing aircraft with improved engine power extraction according to claim 2, characterized in that: Other electrical equipment on board besides the countermeasure mission system includes control surface deflection equipment.

4. The exhaust system for twin-engine flying wing aircraft with improved engine power extraction according to claim 3, characterized in that: The first air release pipeline and the second air release pipeline are both provided with valves.

5. The exhaust system for twin-engine flying wing aircraft with improved engine power extraction according to claim 4, characterized in that: An exhaust port is provided at the lowest point of the upper surface of the fuselage to ensure that the exhaust port can be shielded in the forward direction when the aircraft is in cruising state.

6. A twin-engine flying wing aircraft exhaust method for improving engine power extraction, based on the twin-engine flying wing aircraft exhaust system for improving engine power extraction according to any one of claims 1 to 5, characterized in that: include: During the flight phase when the engine extracts power to meet the electrical needs of the entire aircraft: The engine extraction power of the first engine is used to power the countermeasure mission system. The first engine bleeds air through the compressor. Part of the gas exhausted by the first engine is discharged through the nozzle, and the other part of the gas is supplied to the nitrogen making system through the nitrogen making bleed pipeline. The first bleed pipeline does not exhaust gas. The engine power extraction of the second engine is used to supply power to other electrical equipment on board except the countermeasure mission system. The second engine bleeds air through the compressor, and the exhaust gas of the second engine is discharged through the nozzle. The second bleed air pipeline does not exhaust air. During the flight phase when the engine power extraction cannot meet the power demand of the entire aircraft: When the engine extraction power of the first engine cannot meet the power demand of the countermeasure mission system, the compressor bleed air volume of the first engine is increased, part of the gas exhausted by the first engine is discharged through the nozzle, part of the gas is supplied to the nitrogen making system through the nitrogen making bleed air pipeline, and part of the gas is discharged to the outside of the fuselage through the first bleed air pipeline; When the engine extraction power of the second engine cannot meet the power demand of other electrical equipment on the aircraft except the countermeasure mission system, the compressor bleed air volume of the second engine is increased, part of the gas exhausted by the second engine is discharged through the nozzle, and the other part of the gas is discharged to the outside of the aircraft through the second bleed pipe.

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