Power system for short-distance vertical take-off and landing aircraft and control method

Abstract

The invention belongs to the technical field of design of a power system for a short-distance vertical take-off and landing aircraft, and particularly relates to a power system for a short-distance vertical take-off and landing aircraft and a control method. The complexity, the weight and the design difficulty of the power system can be reduced, liquid hydrogen is designed to cool the superconducting motor, lift force is generated through hydrogen combustion, the requirement for extracting power from an engine can be reduced, the influence on the performance of the engine is reduced, and the design difficulty of the engine is reduced.

Description

Technical Field

[0001] The present application belongs to the technical field of short take-off and vertical landing aircraft power system design, and specifically relates to a power system and a control method for a short take-off and vertical landing aircraft. Background Art

[0002] Short vertical take-off and landing aircraft combine the advantages of fixed-wing and rotary-wing aircraft. They can significantly reduce the aircraft's requirements for take-off and landing ground conditions, while also having higher flight performance.

[0003] At present, the power system of short take-off and vertical landing aircraft uses a mechanical shaft to drive the fan to achieve the balance and control of lift and torque. It is necessary to design couplings, clutches and other devices. The structure is complex, the weight is heavy, and the design is difficult. In addition, a long drive shaft is required to transfer the engine power to the lift fan. The drive shaft has high transmission power and power density, which makes the design extremely difficult and has a high failure rate. In addition, it is necessary to extract a large amount of power from the engine, which affects the performance of the engine and increases the difficulty of starting design.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a power system and a control method for a short-distance vertical take-off and landing aircraft to overcome or alleviate at least one of the technical deficiencies of the known ones.

[0006] The technical solution of this application is:

[0007] On the one hand, a power system for a short-distance vertical take-off and landing aircraft is provided, including an engine, an external duct bleed duct, a lift fan, a superconducting motor, a drive motor, and a liquid hydrogen storage tank;

[0008] The engine's nozzle uses a three-bearing rotating nozzle;

[0009] There are two ducted air pipes, the inlets of which are connected to both sides of the engine and connected to the ducted air pipes of the engine, and the outlets are connected to the ducted air combustion chamber and the tumble nozzle in sequence, and the nozzle of the tumble nozzle is vertically downward;

[0010] The lift fan is arranged in front of the engine and is located on the axis of the engine. The outlet is connected to the lift fan combustion chamber and the box nozzle in sequence. The nozzle of the box nozzle is vertically downward.

[0011] The superconducting motor has an electric mode and a power generation mode, is arranged in the front cavity of the engine, is sleeved on the front end of the high-pressure shaft of the engine, and has a cooling flow channel on it;

[0012] The drive motor is arranged in the lift fan, connected to the rotating shaft of the lift fan, and connected to the superconducting motor through a cable;

[0013] The liquid hydrogen storage tank is arranged outside the engine and connected to the inlet of the cooling flow channel through a pipeline. The outlet of the cooling flow channel is connected to the two external duct bleed air combustion chambers and the lift fan combustion chamber through a pipeline.

[0014] Optionally, in the above-mentioned power system for a short take-off and vertical landing aircraft, the connection position of the two external duct air duct inlets on the engine is located at the compressor part of the engine.

[0015] Optionally, in the above-mentioned power system for short-distance vertical take-off and landing aircraft, the superconducting motor is connected to the power supply system of the aircraft and the power system through a cable, and the cable is led out from the front support plate of the engine.

[0016] Optionally, in the above-mentioned power system for short-distance vertical take-off and landing aircraft, the cable connecting the superconducting motor to the drive motor is led out from the front support plate of the engine.

[0017] Optionally, in the above-mentioned power system for short-distance vertical take-off and landing aircraft, the pipelines between the superconducting motor and the two external duct bleed air combustion chambers and the lift fan combustion chamber and the liquid hydrogen storage tank are led out from the front support plate of the engine.

[0018] On the other hand, a method for controlling a power system for a short take-off and vertical landing aircraft is provided, which is used to control the power system for the short take-off and vertical landing aircraft, comprising:

[0019] When starting the engine, the superconducting motor is set in electric mode and powered to drive the high-voltage shaft of the engine to rotate. After the speed of the high-voltage shaft reaches the speed required for starting the engine, the engine is fueled and ignited to start the engine.

[0020] After the engine is started, the superconducting motor is set in a power generation mode, so that the superconducting motor generates electricity driven by the high-voltage shaft of the engine, and the generated electricity can be supplied to the power supply system of the aircraft and the power system for use, and to the drive motor for use;

[0021] When the aircraft takes off or lands, the nozzle of the three-bearing rotating nozzle of the engine is controlled to be vertically downward, and the nozzle adjustment plates of the two tumble nozzles and the box nozzle are opened to open the nozzles of the two tumble nozzles and the box nozzle, and the superconducting motor is controlled to supply power to the driving motor so that the driving motor drives the lift fan to work. At the same time, the liquid hydrogen storage tank is controlled to pass liquid hydrogen into the cooling flow channel through the pipeline. The liquid hydrogen absorbs the heat generated by the operation of the superconducting motor along the way to cool the superconducting motor. The liquid hydrogen absorbs heat and gasifies into gaseous hydrogen, which flows into the two outer duct bleed air combustion chambers and the lift fan combustion chamber through the pipeline for ignition and combustion;

[0022] When the aircraft is cruising, the nozzle of the engine's three-bearing rotating nozzle is controlled to face horizontally backward, and the nozzle adjustment plates of the two tumble nozzles and the box nozzle are closed to close the nozzles of the two tumble nozzles and the box nozzle. The superconducting motor is controlled to stop supplying power to the drive motor, the drive lift fan is shut down, and the liquid hydrogen storage tank is controlled to stop supplying liquid hydrogen into the cooling flow channel through the pipeline, and the two outer duct bleed air combustion chambers and the lift fan combustion chamber are shut down.

[0023] This application has at least the following beneficial technical effects:

[0024] Provided are a power system and a control method for a short-distance vertical take-off and landing aircraft, which replaces the form of mechanical shaft driving a lift fan with an electric drive, eliminates the transmission shaft and its coupling, clutch and other devices, and can reduce the complexity, weight and design difficulty of the power system. The design uses liquid hydrogen to cool the superconducting motor and uses hydrogen combustion to generate lift, which can reduce the demand for extracting power from the engine, reduce the impact on engine performance, and reduce the design difficulty of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic diagram of a power system for a short vertical take-off and landing aircraft provided in an embodiment of the present application;

[0026] Figure 2 is a schematic diagram of installing a power system for a short vertical take-off and landing aircraft provided in an embodiment of the present application on an aircraft;

[0027] Figure 3 It is a schematic diagram of the control state of a power system for a short-distance vertical take-off and landing aircraft provided in an embodiment of the present application during take-off and landing of the aircraft;

[0028] Figure 4 It is a schematic diagram of the control state of a power system for a short-distance vertical take-off and landing aircraft provided in an embodiment of the present application when the aircraft is cruising;

[0029] in:

[0030] 1-engine; 2-external duct air duct; 3-lift fan; 4-superconducting motor; 5-drive motor; 6-liquid hydrogen storage tank;

[0031] 21-external duct bleed combustion chamber; 22-tumbling nozzle;

[0032] 31-lift fan combustion chamber; 32-box nozzle.

[0033] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0034] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0035] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0036] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0037] A power system for a short take-off and vertical landing aircraft, such as Figure 1 As shown, it includes an engine 1, an external duct air duct 2, a lift fan 3, a superconducting motor 4, a drive motor 5, and a liquid hydrogen storage tank 6.

[0038] The nozzle of engine 1 adopts a three-bearing rotating nozzle.

[0039] There are two duct bleed air pipes 2, the inlets of which are connected to both sides of the engine 1 and communicate with the duct of the engine 1, and the outlets are connected to the duct bleed air combustion chamber 21 and the tumble nozzle 22 in sequence, and the nozzle of the tumble nozzle 22 is vertically downward.

[0040] The two duct air ducts 2 are symmetrically arranged on both sides of the engine 1 , and the connection position of the inlet on the engine 1 is located at the compressor part of the engine 1 .

[0041] The lift fan 3 is arranged in front of the engine 1 and is located on the axis of the engine 1. The outlet is connected to the lift fan combustion chamber 31 and the box nozzle 32 in sequence. The nozzle of the box nozzle 32 is vertically downward.

[0042] The superconducting motor 4 has an electric mode and a power generation mode, is arranged in the front cavity of the engine 1, is sleeved on the front end of the high-pressure shaft of the engine 1, and has a cooling flow channel thereon.

[0043] The superconducting motor 4 is connected to the power supply system of the aircraft and the power system through a cable, and the cable is led out from the front support plate of the engine 1.

[0044] The driving motor 5 is arranged inside the lift fan 3 , connected to the rotating shaft of the lift fan 3 , and connected to the superconducting motor 4 through a cable, and the cable is led out from the front support plate of the engine 1 .

[0045] The liquid hydrogen storage tank 6 is arranged outside the engine 1 and can be fixed on the aircraft structure. The inlet of the cooling flow channel is connected to the inlet of the cooling flow channel through a pipeline. The outlet of the cooling flow channel is connected to the two outer duct bleed air combustion chambers 21 and the lift fan combustion chamber 31 through a pipeline. The pipeline can be set through the front support plate of the engine 1.

[0046] The power system for a short-distance vertical take-off and landing aircraft disclosed in the above embodiment is installed on the aircraft as follows: Figure 2 As shown, the whole is located below the fuselage, the engine 1 is located at the tail of the fuselage, the two external duct bleed air ducts 2 and their external duct bleed air combustion chambers 21 and the roll nozzle 22 are located below the wings, and the lift fan 3 and its lift fan combustion chamber 31 and the box nozzle 32 are located at the front of the fuselage.

[0047] The power system for the short vertical take-off and landing aircraft disclosed in the above embodiment can be controlled by referring to the following method.

[0048] When starting the engine 1, the superconducting motor 4 is set in the electric mode and power is supplied to the superconducting motor 4, so that the superconducting motor drives the high-voltage shaft of the engine 1 to rotate. After the rotation speed of the high-voltage shaft reaches the rotation speed required for starting the engine, the engine 1 is fueled and ignited to start the engine 1.

[0049] After the engine is started, the superconducting motor 4 is set in the power generation mode, so that the superconducting motor 4 generates electricity under the drive of the high-voltage shaft of the engine 1, extracts power from the engine 1 to generate electricity, and the generated electric energy can be supplied to the power supply system of the aircraft and the power system for use, and can be supplied to the drive motor 5 for use.

[0050] When the aircraft takes off or lands, the nozzle of the three-bearing rotating nozzle of the engine 1 is controlled to be vertically downward, and the nozzle adjustment plates of the two rolling nozzles 22 and the box nozzle 32 are opened to open the nozzles of the two rolling nozzles 22 and the box nozzle 32, and the superconducting motor 4 is controlled to supply power to the driving motor 5 so that the driving motor 5 drives the lift fan 3 to work, such as Figure 3As shown, at this time, the exhaust gas of the engine 1 is ejected downward through the three-bearing rotating nozzle, the two duct bleed air pipes 2 eject the bleed air from the duct of the engine 1 downward through the duct bleed air combustion chamber 21 and the roll nozzle 22, and the exhaust gas of the lift fan 3 is ejected downward through the lift fan combustion chamber 31 and the box nozzle 32. The three together generate lift, balance and control the lift and torque of the aircraft, so that the aircraft can perform short-distance vertical take-off and landing.

[0051] When the aircraft takes off and lands, the superconducting motor 4 extracts power from the engine 1 to generate electricity, which is supplied to the driving motor 5 for use, and the lift fan 3 is driven to work. The superconducting motor 4 needs to generate electricity with a large power. For this purpose, the liquid hydrogen storage tank 6 can be controlled to pass liquid hydrogen into the cooling flow channel through the pipeline. The liquid hydrogen absorbs the heat generated by the operation of the superconducting motor 4 along the way to cool the superconducting motor 4 to maintain the low temperature environment required for the superconductivity of the superconducting motor 4, so that the superconducting motor 4 can maintain a large power to generate electricity. At the same time, the liquid hydrogen absorbs heat and gasifies into gaseous hydrogen, which flows into the two outer duct bleed air combustion chambers 21 and the lift fan combustion chamber 31 through the pipeline for ignition and combustion, and then is ejected downward through the two rolling nozzles 22 and the box nozzle 32, so that the bleed air of the two outer duct bleed air pipes 2 and the exhaust of the lift fan 3 can generate greater lift, which is convenient for balancing and controlling the lift and torque of the aircraft, and can fully utilize the hydrogen.

[0052] When the aircraft is cruising, the nozzle of the three-bearing rotating nozzle of the engine 1 is controlled to be horizontally backward, the nozzle adjustment plates of the two tumbling nozzles 22 and the box nozzle 32 are closed, so that the nozzles of the two tumbling nozzles 22 and the box nozzle 32 are closed, and the superconducting motor 4 is controlled to stop supplying power to the driving motor 5, the driving lift fan 3 is shut down, and the liquid hydrogen storage tank 6 is controlled to stop passing liquid hydrogen into the cooling flow channel through the pipeline, and the two outer duct bleed air combustion chambers 21 and the lift fan combustion chamber 31 are shut down. Figure 4 As shown, at this time, the two duct air ducts 2 no longer draw air from the duct of the engine 1, the lift fan 3 stops exhausting, and only the exhaust gas of the engine 1 is ejected backward through the three-bearing rotating nozzle to generate the thrust required for the aircraft cruising. The superconducting motor 4 extracts power from the engine 1 to generate electricity, which only needs to be supplied to the power supply system of the aircraft and the power system for use. It is sufficient to generate electricity with a smaller power, and there is no need to cool it with liquid hydrogen.

[0053] The power system and control method for a short-distance vertical take-off and landing aircraft disclosed in the above-mentioned embodiment replaces the form of mechanical shaft driving the lift fan 3 with electric drive, eliminates the transmission shaft and its coupling, clutch and other devices, which can reduce the complexity, weight and design difficulty of the power system, and is designed to use liquid hydrogen to cool the superconducting motor 4, and uses hydrogen combustion to generate lift, which can reduce the demand for extracting power from the engine 1, reduce the impact on the performance of the engine 1, and reduce the design difficulty of the engine 1. In addition, the superconducting motor 4 can be miniaturized and built into the engine 1 to occupy a small space, which can make the overall structure of the power system compact.

[0054] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A power system for a short take-off and vertical landing aircraft, characterized in that: It comprises an engine (1), an external duct air duct (2), a lift fan (3), a superconducting motor (4), a drive motor (5), and a liquid hydrogen storage tank (6); The nozzle of the engine (1) adopts a three-bearing rotating nozzle; There are two duct bleed air pipes (2), the inlets of which are connected to both sides of the engine (1) and communicate with the duct of the engine (1), and the outlets of which are connected to the duct bleed air combustion chamber (21) and the tumble nozzle (22) in sequence, and the nozzle of the tumble nozzle (22) is vertically downward; The lift fan (3) is arranged in front of the engine (1) and is located on the axis of the engine (1). The outlet is connected to the lift fan combustion chamber (31) and the box nozzle (32) in sequence. The nozzle of the box nozzle (32) is vertically downward. The superconducting motor (4) has an electric mode and a power generation mode, is arranged in the front cavity of the engine (1), is sleeved on the front end of the high-pressure shaft of the engine (1), and has a cooling flow channel thereon; The driving motor (5) is arranged in the lift fan (3), connected to the rotating shaft of the lift fan (3), and connected to the superconducting motor (4) via a cable; The liquid hydrogen storage tank (6) is arranged outside the engine (1) and is connected to the inlet of the cooling flow channel through a pipeline, and the outlet of the cooling flow channel is connected to two external duct bleed air combustion chambers (21) and a lift fan combustion chamber (31) through a pipeline.

2. The power system for a short take-off and vertical landing aircraft according to claim 1, characterized in that: The connection positions of the inlets of the two external duct air ducts (2) on the engine (1) are located at the compressor part of the engine (1).

3. The power system for a short take-off and vertical landing aircraft according to claim 2, characterized in that: The superconducting motor (4) is connected to the power supply system of the aircraft and the power system through a cable, and the cable is led out from the front support plate of the engine (1).

4. The power system for a short vertical take-off and landing aircraft according to claim 3, characterized in that: The cable connecting the superconducting motor (4) to the driving motor (5) is led out from the front support plate of the engine (1).

5. The power system for a short take-off and vertical landing aircraft according to claim 4, characterized in that: The pipelines between the superconducting motor (4) and the two external duct bleed combustion chambers (21), the lift fan combustion chamber (31), and the liquid hydrogen storage tank (6) are led out from the front support plate of the engine (1).

6. A method for controlling a power system for a short take-off and vertical landing aircraft, for controlling the power system for a short take-off and vertical landing aircraft according to claim 5, characterized in that: include: When starting the engine (1), the superconducting motor (4) is set in an electric mode and power is supplied to the superconducting motor (4), so that the superconducting motor drives the high-voltage shaft of the engine (1) to rotate. After the rotation speed of the high-voltage shaft reaches the rotation speed required for starting the engine, the engine (1) is fueled and ignited to start the engine (1); After the engine is started, the superconducting motor (4) is set in a power generation mode, so that the superconducting motor (4) generates electricity under the drive of the high-voltage shaft of the engine (1), and the generated electric energy can be supplied to the power supply system of the aircraft and the power system for use, and to the drive motor (5) for use; When the aircraft takes off or lands, the nozzle of the three-bearing rotating nozzle of the engine (1) is controlled to be vertically downward, and the nozzle adjustment plates of the two tumbling nozzles (22) and the box nozzle (32) are opened so that the nozzles of the two tumbling nozzles (22) and the box nozzle (32) are open, and the superconducting motor (4) is controlled to supply power to the driving motor (5) so that the driving motor (5) drives the lift fan (3) to work. At the same time, the liquid hydrogen storage tank (6) is controlled to pass liquid hydrogen into the cooling flow channel through the pipeline. The liquid hydrogen absorbs heat generated by the operation of the superconducting motor (4) along the way to cool the superconducting motor (4). The liquid hydrogen absorbs heat and is gasified into gaseous hydrogen, which flows into the two outer duct bleed air combustion chambers (21) and the lift fan combustion chamber (31) through the pipeline for ignition and combustion. When the aircraft is cruising, the nozzle of the three-bearing rotating nozzle of the engine (1) is controlled to be horizontally backward, the nozzle adjustment plates of the two rolling nozzles (22) and the box nozzle (32) are closed, so that the nozzles of the two rolling nozzles (22) and the box nozzle (32) are closed, and the superconducting motor (4) is controlled to stop supplying power to the driving motor (5), the driving lift fan (3) is shut down, and the liquid hydrogen storage tank (6) is controlled to stop introducing liquid hydrogen into the cooling flow channel through the pipeline, and the two outer duct bleed air combustion chambers (21) and the lift fan combustion chamber (31) are shut down.

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