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

Abstract

The invention belongs to the technical field of short-distance vertical take-off and landing aircraft power system design, and particularly relates to a short-distance vertical take-off and landing aircraft power system and a control method thereof. The complexity, the weight and the design difficulty of the power system can be reduced, liquid hydrogen is designed to cool the superconducting motor, the hydrogen fuel cell is designed to utilize hydrogen to generate electricity, the requirement for extracting power from the 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 of a short take-off and vertical landing aircraft and a control method thereof. 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 systems of short-distance vertical take-off and landing aircraft mostly adopt a four-point lift layout, which has poor flexibility and increases the difficulty of aircraft layout design. In addition, most of them use a mechanical shaft to drive the fan to achieve the balance and control of lift and torque, which requires the design of couplings, clutches and other devices. The structure is complex, the weight is heavy, and the design is difficult. A long drive shaft is required to transfer the engine power to the lift fan. The drive shaft has high transmission power and high 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 for a short-distance vertical take-off and landing aircraft and a control method thereof, so as to overcome or alleviate at least one of the known technical defects.

[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 integrated energy management system, a lift fan, a superconducting motor, a drive motor, a liquid hydrogen storage tank, a hydrogen fuel cell, and a cassette nozzle;

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

[0009] The integrated energy management system is set outside the engine, has an energy storage function, and is connected to the power supply system of the aircraft and the power system through cables;

[0010] There are multiple lift fans, which are set in front of the engine;

[0011] There are multiple box-type nozzles, connected to the outlets of each lift fan, with the nozzles pointing vertically downward;

[0012] The superconducting motor has an electric mode and a power generation mode. It is set in the front cavity of the engine and is sleeved on the front end of the high-pressure shaft of the engine. It has a cooling flow channel and is connected to the integrated energy management system through cables.

[0013] There are multiple drive motors, which are arranged in each lift fan, connected to the rotating shaft of the lift fan, and connected to the integrated energy management system through cables;

[0014] The liquid hydrogen storage tank is arranged outside the engine and connected to the inlet of the cooling flow channel through a pipeline;

[0015] The hydrogen fuel cell is set in the front cavity of the engine, sleeved on the front end of the high-pressure shaft of the engine, connected to the outlet of the cooling channel through pipes, and connected to the integrated energy management system through cables.

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

[0017] The cable connecting the hydrogen fuel cell to the integrated energy management system is led out from the front support plate of the engine;

[0018] The inlet of the cooling channel is connected to the pipeline of the liquid hydrogen storage tank and is led out from the front support plate of the engine.

[0019] Optionally, in the power system of the above-mentioned short take-off and vertical landing aircraft, the hydrogen fuel cell is located in front of the superconducting motor.

[0020] Optionally, in the power system of the above-mentioned short take-off and vertical landing aircraft, there are two lift fans and their corresponding box nozzles and drive motors, which are arranged symmetrically in front of the engine.

[0021] On the other hand, a method for controlling a power system of a short take-off and vertical landing aircraft is provided, which is used to control the power system of the short take-off and vertical landing aircraft, comprising:

[0022] When starting the engine, the integrated energy management system sets the superconducting motor in electric mode and supplies power to the superconducting motor, so that the superconducting motor drives 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;

[0023] After the engine is started, the integrated energy management system is used to set the superconducting motor in power generation mode, so that the superconducting motor generates electricity driven by the high-voltage shaft of the engine. The generated electric energy is transmitted to the integrated energy management system for storage and can be supplied to the power supply system of the aircraft and the power system and various drive motors for use;

[0024] When the aircraft takes off and lands, the nozzle of the three-bearing rotating nozzle of the engine is controlled to be vertically downward, and the nozzle adjustment plates of each box nozzle are opened to open the nozzles of each box nozzle, and the integrated energy management system is used to supply power to each drive motor, so that each drive 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 hydrogen fuel cell through the pipeline. The integrated energy management system controls the operation of the hydrogen fuel cell, and hydrogen is used to generate electricity. The generated electricity is transmitted to the integrated energy management system for storage;

[0025] When the aircraft is cruising, the nozzle of the engine's three-bearing rotating nozzle is controlled to move horizontally backward, the nozzle adjustment plates of each box nozzle are closed to close the nozzles of each box nozzle, the integrated energy management system is controlled to stop supplying power to the drive motor, the drive lift fan is shut down, the liquid hydrogen storage tank is controlled to stop supplying liquid hydrogen into the cooling flow channel through the pipeline, and the hydrogen fuel cell is controlled to stop working.

[0026] This application has at least the following beneficial technical effects:

[0027] Provided is a power system and control method for a short-distance vertical take-off and landing aircraft, which replaces the form of mechanical shaft driving a lift fan with electric drive, eliminates the transmission shaft and its coupling, clutch and other devices, can reduce the complexity, weight and design difficulty of the power system, and is designed to use liquid hydrogen to cool the superconducting motor, and is designed to use hydrogen fuel cells to generate electricity using hydrogen, which can reduce the demand for extracting power from the engine, reduce the impact on engine performance, and reduce the difficulty of engine design. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the control state of the power system of the short take-off and vertical landing aircraft provided in the embodiment of the present application during take-off and landing of the aircraft;

[0029] Figure 2 It is a schematic diagram of the control state of the power system of the short-distance vertical take-off and landing aircraft provided in an embodiment of the present application when the aircraft is cruising;

[0030] in:

[0031] 1-Engine; 2-Integrated energy management system; 3-Lift fan; 4-Superconducting motor; 5-Drive motor; 6-Liquid hydrogen storage tank; 7-Hydrogen fuel cell; 8-Box nozzle.

[0032] 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

[0033] 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.

[0034] 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.

[0035] 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.

[0036] A power system for a short take-off and vertical landing aircraft, such as Figure 1-Figure 2 As shown, it includes an engine 1, an integrated energy management system 2, a lift fan 3, a superconducting motor 4, a drive motor 5, a liquid hydrogen storage tank 6, a hydrogen fuel cell 7, and a box nozzle 8.

[0037] The nozzle of engine 1 adopts a three-bearing rotating nozzle.

[0038] The integrated energy management system 2 is arranged outside the engine 1 and can be fixed on the aircraft structure. It has an energy storage function, can distribute energy uniformly, and is connected to the power supply system of the aircraft and the power system through cables.

[0039] There are multiple lift fans 3 , which are arranged in front of the engine 1 .

[0040] There are multiple box-type nozzles 8 connected to the outlets of the lift fans 3, with the nozzles pointing vertically downward.

[0041] The superconducting motor 4 has an electric mode and a power generation mode. It is arranged in the front cavity of the engine 1 and is sleeved on the front end of the high-pressure shaft of the engine 1. It has a cooling flow channel and is connected to the integrated energy management system 2 through a cable, which is led out from the front support plate of the engine 1.

[0042] There are multiple drive motors 5, which are arranged in each lift fan 3, connected to the rotating shaft of the lift fan 3, and connected to the integrated energy management system 2 through cables.

[0043] The liquid hydrogen storage tank 6 is arranged outside the engine 1 and can be fixed on the aircraft structure. It is connected to the inlet of the cooling flow channel through a pipeline, and the pipeline is led out from the front support plate of the engine 1.

[0044] The hydrogen fuel cell 7 is arranged in the front cavity of the engine 1, sleeved on the front end of the high-pressure shaft of the engine 1, in front of the superconducting motor 4, connected to the outlet of the cooling channel through a pipeline, and connected to the integrated energy management system 2 through a cable, which is led out from the front support plate of the engine 1.

[0045] In the power system of the short take-off and vertical landing aircraft disclosed in the above embodiment, there are two lift fans 3 and their corresponding box nozzles 8 and drive motors 5, which are symmetrically arranged in front of the engine 1 and can be installed as a whole under the aircraft body. The engine 1 is located at the tail of the fuselage, and the lift fans 3 and their corresponding box nozzles 8 and drive motors 5 are symmetrically arranged at the front of the fuselage.

[0046] The power system of the short take-off and vertical landing aircraft disclosed in the above embodiment can be controlled by referring to the following method.

[0047] When starting the engine 1, the integrated energy management system 2 sets the superconducting motor 4 in the electric mode and supplies power 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.

[0048] After the engine is started, the integrated energy management system 2 sets the superconducting motor 4 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 is transmitted to the integrated energy management system 2 for storage, and can be supplied to the power supply system of the aircraft and the power system and each drive motor 5 for use.

[0049] 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 each box nozzle 8 are opened to open the nozzles of each box nozzle 8, and the integrated energy management system 2 supplies power to each drive motor 5, so that each drive motor 5 drives the lift fan 3 to work, such as Figure 1 As shown, at this time, the exhaust gas of the engine 1 is ejected downward through the three-bearing rotating nozzle, and the exhaust gas of each lift fan 3 is ejected downward through the box nozzle 8, which jointly generate lift, balance and control the lift and torque of the aircraft, and enable the aircraft to perform short-distance vertical takeoff and landing.

[0050] When the aircraft takes off and lands, the superconducting motor 4 extracts power from the engine 1 to generate electricity, which needs to be supplied to each drive motor 5 for use. In order to drive each lift fan 3 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 a 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 hydrogen fuel cell 7 through the pipeline. The integrated energy management system 2 controls the operation of the hydrogen fuel cell 7, and uses hydrogen to generate electricity. The generated electrical energy is transmitted to the integrated energy management system 2 for storage, and is supplied to each drive motor 5 and the power supply system of the aircraft and the power system for use, thereby realizing full utilization of the hydrogen.

[0051] 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 each box nozzle 8 are closed to close the nozzles of each box nozzle 8, the integrated energy management system 2 is controlled to stop supplying power to the drive motor 5, the driving lift fan 3 is turned off, and the liquid hydrogen storage tank 6 is controlled to stop passing liquid hydrogen into the cooling flow channel through the pipeline, and the hydrogen fuel cell 7 is controlled to stop working. Figure 2 As shown, at this time, each 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 to cruise. 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.

[0052] 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 is designed to use hydrogen fuel cells 7 to generate electricity using hydrogen, 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.

[0053] The superconducting motor 4 can be designed to be miniaturized, and together with the hydrogen fuel cell 7, it is built into the engine 1 and occupies a small space, which can make the overall structure of the power system compact and convenient for arrangement on the aircraft. In addition, the electric drive mode replaces the mechanical shaft drive lift fan 3, which facilitates the adjustment and arrangement of the lift point, has good flexibility, and can reduce the design difficulty of the aircraft layout.

[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 includes an engine (1), an integrated energy management system (2), a lift fan (3), a superconducting motor (4), a drive motor (5), a liquid hydrogen storage tank (6), a hydrogen fuel cell (7), and a cassette nozzle (8); The nozzle of the engine (1) adopts a three-bearing rotating nozzle. The integrated energy management system (2) is arranged outside the engine (1), has an energy storage function, and is connected to the power supply system of the aircraft and the power system through cables; There are multiple lift fans (3) arranged in front of the engine (1); There are a plurality of box-type nozzles (8), which are connected to the outlets of the lift fans (3), and the nozzles are 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-voltage shaft of the engine (1), has a cooling flow channel, and is connected to the integrated energy management system (2) via a cable; There are a plurality of drive motors (5), which are arranged in each lift fan (3), connected to the rotating shaft of the lift fan (3), and connected to the integrated energy management system (2) via cables; The liquid hydrogen storage tank (6) is arranged outside the engine (1) and is connected to the inlet of the cooling channel through a pipeline; The hydrogen fuel cell (7) is arranged in the front cavity of the engine (1), sleeved on the front end of the high-pressure shaft of the engine (1), connected to the outlet of the cooling channel through a pipeline, and connected to the integrated energy management system (2) through a cable.

2. The power system of the short take-off and vertical landing aircraft according to claim 1, characterized in that: The cable connecting the superconducting motor (4) to the integrated energy management system (2) is led out from the front support plate of the engine (1); The cable connecting the hydrogen fuel cell (7) to the integrated energy management system (2) is led out from the front support plate of the engine (1); The inlet of the cooling flow channel is connected to a pipeline of a liquid hydrogen storage tank (6) and is led out from the front support plate of the engine (1).

3. The power system of the short take-off and vertical landing aircraft according to claim 2, characterized in that: The hydrogen fuel cell (7) is located in front of the superconducting motor (4).

4. The power system of the short take-off and vertical landing aircraft according to claim 3, characterized in that: There are two lift fans (3) and their corresponding box-type nozzles (8) and drive motors (5), which are symmetrically arranged in front of the engine (1).

5. A method for controlling a power system of a short take-off and vertical landing aircraft, for controlling the power system of the short take-off and vertical landing aircraft according to claim 4, characterized in that: include: When starting the engine (1), the integrated energy management system (2) sets the superconducting motor (4) in an electric mode and supplies power 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 integrated energy management system (2) sets the superconducting motor (4) 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 is transmitted to the integrated energy management system (2) for storage, and can be supplied to the power supply system of the aircraft and the power system and each driving 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 plate of each box nozzle (8) is opened to open the nozzle of each box nozzle (8), and the integrated energy management system (2) supplies power to each drive motor (5), so that each drive 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 the 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 gasifies into gaseous hydrogen, which flows into the hydrogen fuel cell (7) through the pipeline. The integrated energy management system (2) controls the operation of the hydrogen fuel cell (7), and uses hydrogen to generate electricity. The generated electric energy is transmitted to the integrated energy management system (2) for storage; 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 each box nozzle (8) are closed, so that the nozzle of each box nozzle (8) is closed, the integrated energy management system (2) is controlled to stop supplying power to the drive motor (5), the driving lift fan (3) is shut down, and the liquid hydrogen storage tank (6) is controlled to stop supplying liquid hydrogen to the cooling flow channel through the pipeline, and the hydrogen fuel cell (7) is controlled to stop working.

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