Oil-electricity hybrid driven double-engine short-distance vertical take-off and landing aircraft and control method thereof

Abstract

The invention relates to an oil-electricity hybrid driven double-engine short-distance vertical take-off and landing aircraft and a control method thereof, and the short-distance vertical take-off and landing aircraft comprises an aircraft body, electric lift fans and vector engines; the fuselage comprises a fuselage body, wings and a full-moving empennage; the two electric lift fans are arranged in lift fan cabins formed in the two sides of the front portion of the machine body and provided with folding and unfolding driving mechanisms. When the lift fan cabin door is closed, the lift fan cabin door is conformal with the outer surface of the fuselage, and when the lift fan cabin door is opened, the electric lift fan can extend out of the lift fan cabin under the driving of the retraction driving mechanism; the two vector engines are arranged in engine cabins formed in the two sides of the tail of the machine body, and the vector engines are provided with three-bearing rotating spray pipes. When the engine cabin door is closed, the engine cabin door is conformal with the outer surface of the fuselage, nozzles of the bearing rotating spray pipes are exposed out of the engine cabin backwards, and when the engine cabin door is opened, the nozzles of the three-bearing rotating spray pipes can be adjusted to be downward from the backward direction.

Description

Technical Field

[0001] The present application belongs to the technical field of overall aircraft design, and specifically relates to an oil-electric hybrid drive twin-engine short-range vertical take-off and landing aircraft and a control method thereof. Background Art

[0002] Through power design and the use of a vertical lift system, short-distance vertical take-off and landing aircraft can better adapt to take-off and landing in small spaces such as decks and simple airports.

[0003] At present, short vertical take-off and landing aircraft usually use a vertical lift system with a single lift / cruise engine + a single lift fan + two left and right attitude adjustment nozzles, such as Figure 1 As shown, this technical solution has the following defects:

[0004] 1) It is tightly coupled with the engine, which is the only power source. Engine failure will threaten the function of the entire power system and the flight safety of the aircraft. When the aircraft takes off and lands, only a single engine and lift fan provide vertical lift, and the lifting force that can be provided is limited;

[0005] 2) Tightly coupled with the fuselage structure, the engine is connected to the lift fan through a transmission shaft, clutch, etc. to provide power for the lift fan. It needs to pass through the fuselage structure, which increases the complexity of the fuselage structure and is inconvenient to arrange. In addition, the mechanical transmission shaft device has poor reliability at high torque and high speed.

[0006] 3) Vertical lift control is difficult. 82% of the lift is usually provided by the engine and lift fan on the symmetry plane, and the lift provided by the attitude adjustment nozzles on both sides accounts for only 9%. This bicycle-like lift layout is prone to roll and has a greater safety risk.

[0007] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0008] The purpose of the present application is to provide a hybrid oil-electric drive twin-engine short-distance vertical take-off and landing aircraft and a control method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] On the one hand, a hybrid oil-electric drive twin-engine short-distance vertical take-off and landing aircraft is provided, comprising: a fuselage, an electric lift fan, and a vector engine;

[0011] The fuselage includes the fuselage, wings, and all-moving tail;

[0012] There are two electric lift fans, which are arranged in lift fan compartments opened on both sides of the front part of the fuselage and are equipped with a retractable and extendable driving mechanism;

[0013] When the lift fan door is closed, it conforms to the outer surface of the fuselage. When the lift fan door is opened, the electric lift fan can be extended from the lift fan cabin or retracted from the outside into the lift fan cabin under the drive of the retractable drive mechanism.

[0014] There are two vector engines, which are installed in the engine compartments on both sides of the tail of the fuselage. The vector engines are equipped with three-bearing rotating nozzles.

[0015] When the engine door is closed, it conforms to the outer surface of the fuselage, and the nozzle of the bearing rotating nozzle is exposed backward outside the engine compartment. When the engine door is opened, the nozzle of the three-bearing rotating nozzle can be adjusted from backward to downward, and from downward to backward;

[0016] A hybrid-electric twin-engine short-distance vertical take-off and landing aircraft with vertical take-off, cruising flight and vertical landing capabilities;

[0017] During takeoff: the electric lift fan extends from the lift fan compartment and rotates to generate lift; the wing control surfaces and the full-moving tail are tilted downward at a large angle to switch to a high-lift configuration; the engine starts, and the nozzle of the three-bearing rotating nozzle is adjusted to face backward to generate thrust;

[0018] In the cruising state: the lift of the electric lift fan and the aircraft angle of attack gradually decrease until they are zero; the electric lift fan is retracted from the outside into the lift fan compartment; the nozzle of the three-bearing rotating nozzle of the engine is adjusted to face backward to generate thrust;

[0019] When landing: the electric lift fan extends from the lift fan compartment and rotates to generate vertical lift; the nozzle of the engine's three-bearing rotating nozzle is adjusted downward to generate vertical lift.

[0020] According to at least one embodiment of the present application, in the control method of the above-mentioned hybrid-electric twin-engine short-distance vertical take-off and landing aircraft, in the vertical landing state, the electric lift fan is less than the vertical lift of the vector engine;

[0021] A single electric lift fan produces vertical lift accounting for 20% of the total lift;

[0022] A single engine produces vertical lift that accounts for 30% of the total lift.

[0023] According to at least one embodiment of the present application, the control method of the above-mentioned hybrid-electric twin-engine short-distance vertical take-off and landing aircraft further includes a hydrogen fuel cell and a hydrogen storage tank;

[0024] The hydrogen fuel cell is arranged in the body, connected to the electric lift fan through a cable to provide power for the operation of the electric lift fan, and connected to the starter of the vector engine through a cable to provide power for starting the engine;

[0025] The hydrogen storage tank is arranged in the fuselage and connected to the hydrogen fuel cell through a pipeline to provide hydrogen fuel for the hydrogen fuel cell. The hydrogen filling port is arranged at the bottom of the front landing gear compartment.

[0026] On the other hand, a control method of a hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is provided, which is implemented based on the above-mentioned hybrid-electric twin-engine short-distance vertical take-off and landing aircraft, and includes:

[0027] During takeoff, the hybrid-electric twin-engine short-distance vertical takeoff and landing aircraft is set to be in a takeoff state and accelerates for takeoff;

[0028] After takeoff, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is set in a cruising state for a cruising flight;

[0029] During landing, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is placed in a landing state to hover and land in the air.

[0030] According to at least one embodiment of the present application, in the control method of the above-mentioned hybrid-electric twin-engine short-distance vertical take-off and landing aircraft, the angular velocity acceleration of the pitch angle, roll angle, and yaw angle of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is controlled by controlling the magnitude of the vertical lift generated by the electric lift fan and the engine, specifically as follows:

[0031]

[0032] in,

[0033] m is the mass of the hybrid-electric twin-engine short-range vertical takeoff and landing aircraft;

[0034] They are the angular velocity accelerations of the pitch angle, roll angle, and yaw angle of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft;

[0035] L1, L2, L3, and L4 are the vertical lifts generated by the left and right engines, and the vertical lifts generated by the left and right electric lift fans, respectively;

[0036] The components of lift generated by the electric lift fan and engine on the y-axis and z-axis;

[0037] G is the gravity of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of the vertical lift system of the current short vertical take-off and landing aircraft, which uses a single lift / cruise engine + a single lift fan + two left and right attitude adjustment nozzles;

[0039] Figure 2is a schematic diagram of a hybrid-electric twin-engine short-range vertical take-off and landing aircraft provided in an embodiment of the present application;

[0040] Figure 3 It is a schematic diagram of an electric lift fan provided in an embodiment of the present application being extended from a lift fan compartment and retracted from the outside into the lift fan compartment under the drive of a retracting and extending driving mechanism;

[0041] Figure 4 It is a schematic diagram of vertical lift distribution of a hybrid-electric twin-engine short-distance vertical take-off and landing aircraft in a vertical landing state provided by an embodiment of the present application;

[0042] Figure 5 It is a schematic diagram of attitude adjustment of a hybrid-electric twin-engine short-distance vertical take-off and landing aircraft provided in an embodiment of the present application;

[0043] in:

[0044] 1-fuselage; 2-electric lift fan; 3-vector engine; 4-hydrogen fuel cell; 5-hydrogen storage tank.

[0045] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0046] 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.

[0047] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0048] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms 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.

[0049] A hybrid electric twin-engine short-distance vertical take-off and landing aircraft, such as Figure 2 As shown, it includes a fuselage 1, an electric lift fan 2, and a vector engine 3.

[0050] The fuselage 1 includes a fuselage, wings, a fully movable tail, etc., and a landing gear compartment for retracting and extending the front landing gear and the main landing gear is arranged at the bottom of the fuselage.

[0051] There are two electric lift fans 2, which are arranged in lift fan compartments opened on both sides of the front of the fuselage and are equipped with a retractable drive mechanism. When the lift fan compartment door is closed, it conforms to the outer surface of the fuselage. When the lift fan compartment door is opened, the electric lift fan 2 can be extended from the lift fan compartment or retracted from the outside into the lift fan compartment under the drive of the retractable drive mechanism. Figure 3 The retractable drive mechanism can be designed to include components such as a motor and a connecting rod, wherein the motor is connected in the lift fan compartment and connected to the electric lift fan 2 via the connecting rod, which can drive the connecting rod to swing, thereby driving the electric lift fan 2 to extend from the lift fan compartment or to be retracted from the outside into the lift fan compartment.

[0052] There are two vector engines 3, which are set in the engine compartments opened on both sides of the tail of the fuselage. The vector engines 3 are equipped with three-bearing rotating nozzles. When the engine compartment door is closed, it conforms to the outer surface of the fuselage, and the nozzle of the bearing rotating nozzle is exposed backward outside the engine compartment. When the engine compartment door is opened, the nozzle of the three-bearing rotating nozzle can be adjusted from backward to downward, and from downward to backward.

[0053] The hybrid-electric twin-engine short-distance vertical take-off and landing aircraft disclosed in the above embodiment has a vertical take-off state, a cruising flight state, and a vertical landing state.

[0054] During takeoff:

[0055] The electric lift fan 2 extends from the lift fan cabin and rotates to generate lift;

[0056] The wing control surfaces and the all-moving tail are tilted downward at a large angle, switching to a high-lift configuration;

[0057] Vector engine 3 starts, and the nozzle of the three-bearing rotating nozzle is adjusted to face backward, generating thrust to accelerate the aircraft to take off.

[0058] In the vertical take-off state, the two electric lift fans 2 can provide a strong nose-up moment, which is balanced by the nose-down moment of the downward-biased wing control surfaces and the full-moving tail, generating a much higher low-speed take-off lift than that of ordinary aircraft, thus achieving short-distance take-off.

[0059] In cruising mode:

[0060] The lift of the electric lift fan 2 and the angle of attack of the aircraft gradually decrease until they are zero;

[0061] The electric lift fan 2 is retracted from the outside into the lift fan compartment;

[0062] The nozzle of the three-bearing rotating nozzle of the vector engine 3 is adjusted to face backwards to generate thrust, and the aircraft performs cruising flight.

[0063] When landing:

[0064] The electric lift fan 2 extends from the lift fan cabin and rotates to generate vertical lift;

[0065] The nozzle of the three-bearing rotating nozzle of the vector engine 3 is adjusted downward to generate vertical lift, allowing the aircraft to land vertically.

[0066] In the vertical landing state, two electric lift fans 2 and vector engines 3 provide lift to achieve vertical lift of the twin-engine, twin-fan "four-jet" configuration. The lift of the electric lift fans 2 and vector engines 3 of the entire aircraft is evenly arranged, generating low-speed lift to overcome the landing gravity, allowing the aircraft to hover in the air and land.

[0067] In the vertical landing state, the electric lift fan 2 can be designed to be smaller than the vertical lift of the vector engine 3. The lift generated by a single electric lift fan 2 can account for 20% of the total lift, and the lift generated by a single engine 3 can account for 30% of the total lift, so as to avoid the lift fan system being too large and too heavy. Figure 4 shown.

[0068] The oil-electric hybrid driven twin-engine short-distance vertical take-off and landing aircraft disclosed in the above embodiment can be further designed to include a hydrogen fuel cell 4 and a hydrogen storage tank 5.

[0069] The hydrogen fuel cell 4 is disposed in the body, connected to the electric lift fan 2 via a cable to provide power for the operation of the electric lift fan 2 , and connected to the starter of the vector engine 3 via a cable to provide power for starting the vector engine 3 .

[0070] The hydrogen storage tank 5 is arranged in the body and connected to the hydrogen fuel cell 4 through a pipeline to provide hydrogen fuel for the hydrogen fuel cell 4. The upper hydrogen filling port is arranged at the bottom of the front landing gear compartment.

[0071] Based on the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft disclosed in the above embodiments, the present application further provides a control method for the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft, including:

[0072] During takeoff, the hybrid-electric twin-engine short-distance vertical takeoff and landing aircraft is set to be in a takeoff state and accelerates for takeoff;

[0073] After takeoff, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is set in a cruising state for a cruising flight;

[0074] During landing, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is placed in a landing state to hover and land in the air.

[0075] In addition, the attitude of the aircraft can be adjusted by controlling the magnitude of the lift generated by the electric lift fan 2 and the engine 3, and controlling the angular velocity acceleration of the pitch angle, roll angle, and yaw angle, such as Figure 5 As shown, the details are as follows:

[0076]

[0077] in,

[0078] m is the mass of the hybrid-electric twin-engine short-range vertical takeoff and landing aircraft;

[0079] They are the angular velocity accelerations of the pitch angle, roll angle, and yaw angle of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft;

[0080] L1, L2, L3, L4 are respectively the lift generated by the left and right engines 3, and the lift generated by the left and right electric lift fans 2;

[0081] The components of lift generated by the electric lift fan 2 and the engine 3 on the y-axis and the z-axis;

[0082] G is the gravity of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft.

[0083] Compared with the aircraft with existing vertical lift systems, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft disclosed in the above embodiment has the following significant advantages:

[0084] 1 The lift fan is designed to be an electric lift fan 2, which is decoupled from the vector engine 3. The electric lift fan 2 and the vector engine 3 are highly independent, which is convenient for fault isolation. In addition, two electric lift fans 2 and the vector engine 3 can provide vertical lift, which can provide a larger lifting force.

[0085] 2. The electric lift fan 2 and the vector engine 3 no longer need to be connected by a transmission shaft, a clutch, etc., which can reduce the complexity of the fuselage structure design, facilitate flexible arrangement, and have high reliability and are not prone to mechanical failures;

[0086] 3. It can realize the vertical lift of the twin-engine, twin-fan "four-jet" configuration, and can conveniently and flexibly adjust the aircraft's attitude.

[0087] In addition, the response time of the electrical system is usually milliseconds, which is much higher than the second-level response of the traditional mechanical system. In the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft disclosed in the above embodiment, the electric lift fan 2 has higher energy efficiency, greater torque and faster response capability, and the attitude control of the aircraft can be more precise and rapid.

[0088] 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 hybrid electric twin-engine short take-off and vertical landing aircraft, characterized in that: include: Airframe (1), electric lift fan (2), vector engine (3); The fuselage (1) comprises a fuselage, wings, and a fully movable tail; There are two electric lift fans (2), which are arranged in lift fan compartments opened on both sides of the front part of the machine body and are equipped with a retractable and extendable driving mechanism; When the lift fan door is closed, it conforms to the outer surface of the fuselage. When the lift fan door is opened, the electric lift fan (2) can be extended from the lift fan door or retracted from the outside into the lift fan door under the drive of the retractable drive mechanism. There are two vector engines (3), which are arranged in engine compartments opened on both sides of the tail of the fuselage. The vector engines (3) are equipped with three-bearing rotating nozzles; When the engine door is closed, it conforms to the outer surface of the fuselage, and the nozzle of the bearing rotating nozzle is exposed backward outside the engine compartment. When the engine door is opened, the nozzle of the three-bearing rotating nozzle can be adjusted from backward to downward, and from downward to backward; A hybrid-electric twin-engine short-distance vertical take-off and landing aircraft with vertical take-off, cruising flight and vertical landing capabilities; In the take-off state: the electric lift fan (2) extends from the lift fan compartment and rotates to generate lift; the wing control surfaces and the all-moving tail are tilted downward at a large angle to switch to a high-lift configuration; the vector engine (3) is started, and the nozzle of the three-bearing rotating nozzle is adjusted to face backward to generate thrust; In the cruising state: the lift of the electric lift fan (2) and the angle of attack of the aircraft are gradually reduced until they are zero; the electric lift fan (2) is retracted from the outside into the lift fan compartment; the nozzle of the three-bearing rotating nozzle of the vector engine (3) is adjusted to face backwards to generate thrust; In the landing state: the electric lift fan (2) extends from the lift fan cabin and rotates to generate vertical lift; the nozzle of the three-bearing rotating nozzle of the vector engine (3) is adjusted to face downward to generate vertical lift.

2. The hybrid-electric twin-engine short-distance vertical take-off and landing aircraft according to claim 1, characterized in that: In the vertical landing state, the electric lift fan (2) is smaller than the vertical lift of the vector engine (3); A single electric lift fan (2) generates vertical lift accounting for 20% of the total lift; A single engine (3) generates vertical lift accounting for 30% of the total lift.

3. The hybrid-electric twin-engine short-distance vertical take-off and landing aircraft according to claim 1 is characterized in that It also includes a hydrogen fuel cell (4) and a hydrogen storage tank (5); The hydrogen fuel cell (4) is arranged in the body, connected to the electric lift fan (2) through a cable to provide power for the operation of the electric lift fan (2), and connected to the starter of the vector engine (3) through a cable to provide power for starting the electric engine (3); The hydrogen storage tank (5) is arranged in the body and connected to the hydrogen fuel cell (4) through a pipeline to provide hydrogen fuel for the hydrogen fuel cell (4). The hydrogen filling port is arranged at the bottom of the front landing gear compartment.

4. A method for controlling a hybrid-electric twin-engine short-distance vertical take-off and landing aircraft, based on the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft of claim 1, characterized in that: include: During takeoff, the hybrid-electric twin-engine short-distance vertical takeoff and landing aircraft is set to be in a takeoff state and accelerates for takeoff; After takeoff, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is set in a cruising state for a cruising flight; During landing, the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft is placed in a landing state to hover and land in the air.

5. The control method of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft according to claim 4 is characterized in that: By controlling the magnitude of the vertical lift generated by the electric lift fan (2) and the vector engine (3), the angular velocity acceleration of the pitch angle, roll angle and yaw angle of the electric hybrid drive twin-engine short-distance vertical take-off and landing aircraft is controlled, specifically as follows: in, m is the mass of the hybrid-electric twin-engine short-range vertical takeoff and landing aircraft; They are the angular velocity accelerations of the pitch angle, roll angle, and yaw angle of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft; L1, L2, L3, and L4 are respectively the vertical lifts generated by the left and right vector engines (3), and the vertical lifts generated by the left and right electric lift fans (2); The electric lift fan (2) and the vector engine (3) generate components of vertical lift on the y-axis and the z-axis; G is the gravity of the hybrid-electric twin-engine short-distance vertical take-off and landing aircraft.

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