Supersonic unmanned aerial vehicle combined power system and control method thereof

Abstract

The invention belongs to the technical field of unmanned aerial vehicle power system design, and particularly relates to a supersonic unmanned aerial vehicle combined power system and a control method thereof.The supersonic unmanned aerial vehicle combined power system adopts a layout form of a main engine and a distributed ducted fan, is integrally arranged in a fuselage, is integrally designed with the unmanned aerial vehicle fuselage, is small in resistance, and is high in reliability. And the requirements of supersonic flight of the unmanned aerial vehicle for high thrust and subsonic flight for low oil consumption can be well met by controlling the main engine and the ducted fan.

Description

Technical Field

[0001] The present application belongs to the technical field of UAV power system design, and specifically relates to a supersonic UAV combined power system and a control method thereof. Background Art

[0002] Supersonic drones are usually powered by turbojet engines or low-bypass turbofan engines to ensure thrust to break the sound barrier and fly at supersonic speeds. However, due to the limited working conditions, it is difficult to simultaneously achieve high thrust for supersonic flight and low fuel consumption for subsonic flight. Usually, the flight time and range are short, which greatly limits the effectiveness of drones. In addition, the engine exhaust temperature is high and the infrared radiation signal is strong, making it difficult to ensure low detectability.

[0003] Distributed ducted fans can effectively reduce the fuel consumption of engines in subsonic cruise state, but they are generally used in low-speed aircraft. During supersonic flight, the compression effect will deteriorate, resulting in a significant reduction in thrust, making it difficult to use on supersonic UAVs. In addition, there are varying degrees of overflow losses under various operating conditions.

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

[0005] The purpose of this application is to provide a supersonic UAV combined power system and a control method thereof to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is: On the one hand, a supersonic UAV combined power system is provided, including a main engine, a ducted fan, an air inlet, and an exhaust duct; The main engine includes a fan, a compressor, a main combustion chamber, a high-pressure turbine, a low-pressure turbine, an afterburner, and a nozzle arranged in sequence; The main engine and ducted fans are installed in the fuselage, with the main engine located in the middle of the upper part of the fuselage. There are four ducted fans, located at the upper left, upper right, lower left and lower right of the main engine, respectively, and arranged around the main engine. The air inlet outlet is connected to the main engine and the inlet of four ducted fans, and the inlet extends to the belly of the fuselage and is located in front of the belly of the fuselage; The exhaust duct inlet is connected to the outlets of the main engine and four ducted fans, and the outlet extends to the tail of the fuselage.

[0007] Optionally, the above-mentioned supersonic UAV combined power system has a high thrust working mode and a low fuel consumption working mode; In high thrust working mode, the main engine is working, afterburner is on, the ducted fan is not powered, and it is in windmill state; In the low fuel consumption working mode, the main engine is working without afterburner, and the ducted fan is powered and in working condition.

[0008] Optionally, the above-mentioned supersonic UAV combined power system is provided with a generator and a generator on the main engine; The generator is sleeved on the front end of the high-voltage shaft of the main engine and connected to the main engine and the aircraft's power supply system through lines; The generator is sleeved on the rear end of the low-pressure shaft of the main engine and connected to four ducted fans through lines.

[0009] Optionally, the above-mentioned supersonic UAV combined power system controls the starter generator to be in electric mode when the main engine is started, drives the high-voltage shaft to rotate, and when the speed of the high-voltage shaft reaches the speed required for starting the main engine, ignites the main engine to start the main engine; After the main engine is started, the starter generator is controlled to be in power generation mode, so that the starter generator generates electricity driven by the high-pressure shaft to supply the main engine and the aircraft's power supply system, and the generator generates electricity driven by the low-pressure shaft to supply the ducted fan.

[0010] Optionally, in the above-mentioned supersonic UAV combined power system, the inlet portion of the air inlet is bent upward; An upwardly bent special-shaped shielding nozzle is arranged at the exhaust duct outlet.

[0011] On the other hand, a method for controlling a supersonic UAV combined power system is provided, which is used to control the supersonic UAV combined power system, comprising: When the UAV takes off, accelerates, or flies at supersonic speed, the supersonic UAV combined power system is set to a high thrust working mode; When the UAV is flying at subsonic speed, the combined power system of the supersonic UAV is set to a low fuel consumption working mode; When the main engine is started, the starter generator is controlled to be in electric mode to drive the high-voltage shaft to rotate. When the speed of the high-voltage shaft reaches the speed required for starting the main engine, the main engine is ignited to start the main engine; After the main engine is started, the starter generator is controlled to be in power generation mode, so that the starter generator generates electricity driven by the high-pressure shaft to supply the main engine and the aircraft's power supply system, and the generator generates electricity driven by the low-pressure shaft to supply the ducted fan.

[0012] This application has at least the following beneficial technical effects: A supersonic UAV combined power system is provided, which adopts a main engine + distributed ducted fan layout, is placed in a fuselage as a whole, and is integrated with the UAV fuselage. It has low resistance and can well take into account the requirements of high thrust for supersonic flight of the UAV and low fuel consumption for subsonic flight through the control of the main engine and the ducted fan. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 is a schematic diagram of a supersonic UAV combined power system provided in an embodiment of the present application; Figure 2 is a schematic diagram of the main engine and its ducted fan structure layout provided in an embodiment of the present application; Figure 3 It is a schematic diagram of the arrangement of the main engine, ducted fan, air inlet, exhaust duct, and special-shaped shielded nozzle provided in the embodiment of the present application; in: 1-main engine; 2-ducted fan; 3-intake duct; 4-exhaust duct; 5-fan; 6-compressor; 7-main combustion chamber; 8-high-pressure turbine; 9-low-pressure turbine; 10-afterburner; 11-nozzle; 12-generator; 13-high-pressure shaft; 14-low-pressure shaft; 15-special-shaped shielded nozzle; 16-generator.

[0014] 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

[0015] 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.

[0016] 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.

[0017] 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.

[0018] A supersonic UAV combined power system, such as Figure 1 As shown, it includes a main engine 1, a ducted fan 2, an air intake duct 3, and an exhaust duct 4.

[0019] The main engine 1 includes a fan 5, a compressor 6, a main combustion chamber 7, a high-pressure turbine 8, a low-pressure turbine 9, an afterburner 10, and a nozzle 11, which are arranged in sequence. Figure 2 shown.

[0020] The main engine 1 and the ducted fan 2 are arranged in the fuselage, wherein the main engine 1 can adopt a turbojet engine or a small bypass ratio turbofan engine, and is located in the upper middle position of the fuselage; there are four ducted fans 2, which are respectively located at the upper left, upper right, lower left and lower right of the main engine 1, and are arranged around the main engine 1.

[0021] The air inlet 3 is a supersonic air inlet, and its outlet is connected to the inlets of the main engine 1 and four ducted fans 2, that is, the main engine 1 and the four ducted fans 2 share the air inlet 3, and the inlet of the air inlet 3 extends to the belly of the fuselage and is located in front of the belly of the fuselage.

[0022] The inlet of the exhaust duct 4 is connected to the outlets of the main engine 1 and the four ducted fans 2, that is, the main engine 1 and the four ducted fans 2 share the exhaust duct 4, and the outlet of the exhaust duct 4 extends to the tail of the fuselage.

[0023] The supersonic UAV combined power system disclosed in the above embodiment has a high thrust working mode and a low fuel consumption working mode.

[0024] In the high-thrust working mode, the main engine 1 is working and the afterburner is turned on, that is, the main combustion chamber 7 and the afterburner combustion chamber 10 are working at the same time, the ducted fan 2 is not powered and is in a windmill state, and the supersonic UAV combined power system is in a small bypass ratio state as a whole, which can generate a large thrust and can well meet the thrust requirements of the UAV during takeoff, acceleration and supersonic flight. In the high-thrust working mode, due to the ejection effect of the exhaust of the main engine 1, the exhaust flow of the ducted fan 2 will increase significantly compared to the case without the ejection effect, the resistance of the ducted fan 2 is reduced, and thrust is generated, which can further increase the thrust of the supersonic UAV combined power system.

[0025] In the low fuel consumption working mode, the main engine 1 works, but the afterburner is not turned on, that is, only the main combustion chamber 7 works, the afterburner combustion chamber 10 does not work, the ducted fan 2 is powered and is in a working state, and the supersonic UAV combined power system is in a large bypass ratio state as a whole, and the thrust that can be generated is relatively small, but the fuel consumption rate is reduced, which can well meet the low fuel consumption requirements of the subsonic flight of the UAV. In the low fuel consumption working mode, the thrust and flow generated by the ducted fan 2 can supplement the thrust generated by the main engine 1, and reduce the overflow loss, which can ensure that the supersonic UAV combined power system has sufficient thrust.

[0026] The supersonic UAV combined power system disclosed in the above embodiment adopts the layout of main engine + distributed ducted fan, which is placed in the fuselage as a whole and integrated with the UAV fuselage. It has low resistance and can well take into account the requirements of high thrust for supersonic flight of the UAV and low fuel consumption for subsonic flight by controlling the main engine 1 and the ducted fan 2.

[0027] In the supersonic UAV combined power system disclosed in the above embodiment, four ducted fans 2 are designed to be arranged around the main engine 1, and share the air inlet duct 3 and the exhaust duct 4. On the one hand, the complexity of the power system structure can be reduced. On the other hand, the low-temperature exhaust of the four ducted fans 2 can wrap the high-temperature exhaust of the main engine 1. The low-temperature exhaust of the four ducted fans 2 can be efficiently mixed with the high-temperature exhaust of the main engine 1, thereby effectively reducing the temperature of the high-temperature exhaust of the main engine 1, reducing the temperature of the power system exhaust and its infrared radiation signal, thereby ensuring the low detectability of the power system and avoiding high-temperature damage to the structure caused by the high-temperature exhaust of the main engine 1.

[0028] A starter generator 16 and a generator 12 may be further arranged on the main engine 1, wherein the starter generator 16 is sleeved on the front end of the high-pressure shaft 13 of the main engine 1, and is connected to the main engine 1 and the power supply system of the aircraft through lines; the generator 12 is sleeved on the rear end of the low-pressure shaft 14 of the main engine 1, and is connected to the four ducted fans 2 through lines.

[0029] When the main engine 1 is started, the starter generator 16 can be controlled to be in electric mode to drive the high-voltage shaft 13 to rotate. When the speed of the high-voltage shaft 13 reaches the speed required for starting the main engine 1, the main engine 1 is ignited to start the main engine 1.

[0030] After the main engine 1 is started, the starter generator 16 can be controlled to be in the power generation mode, so that the starter generator 16 generates electricity driven by the high-pressure shaft 13 to supply the main engine 1 and the aircraft's power supply system. At the same time, the generator 12 generates electricity driven by the low-pressure shaft 14 to supply the ducted fan 2 for operation.

[0031] An energy management system can be set up to control the switching of the working mode of the generator 16, and to distribute the electric energy generated by the generator 16 and the generator 12, and to store the excess electric energy in the battery. When the power generation of the generator 16 and the generator 12 cannot meet the demand, the battery is used to supplement the electric energy, thereby ensuring the stability of the power supply of the supersonic UAV combined power system.

[0032] In order to further ensure the low detectability performance of the combined power system of the supersonic UAV, the inlet of the air inlet 3 can be designed to be bent upward, and a special-shaped shielding nozzle 15 bent upward can be set at the outlet of the exhaust duct 4, such as Figure 3 As shown, the inlet and outlet of the main engine 1 and the four ducted fans 2 are completely shielded, the forward and backward infrared radiation signals of the main engine 1 and the four ducted fans 2 are reduced, and the low detectability performance of the supersonic UAV combined power system is ensured.

[0033] A control method for a supersonic UAV combined power system, used to control the supersonic UAV combined power system disclosed in the above embodiment, comprising: When the UAV takes off, accelerates, or flies at supersonic speed, the supersonic UAV combined power system is set to a high thrust working mode; When the UAV is flying at subsonic speed, the combined power system of the supersonic UAV is set to a low fuel consumption working mode; When the main engine 1 is started, the starter generator 16 is controlled to be in electric mode to drive the high-voltage shaft 13 to rotate. When the speed of the high-voltage shaft 13 reaches the speed required for starting the main engine 1, the main engine 1 is ignited to start the main engine 1; After the main engine 1 is started, the starter generator 16 is controlled to be in the power generation mode, so that the starter generator 16 generates electricity driven by the high-pressure shaft 13 to supply the main engine 1 and the aircraft's power supply system, and the generator 12 generates electricity driven by the low-pressure shaft 14 to supply the ducted fan 2 for operation.

[0034] The control method of the supersonic UAV combined power system disclosed in the above embodiment is used to control the supersonic UAV combined power system disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the supersonic UAV combined power system part. Its technical effects can also refer to the technical effects of the relevant parts of the supersonic UAV combined power system, which will not be repeated here.

[0035] 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 supersonic UAV combined power system, characterized in that: It comprises a main engine (1), a ducted fan (2), an air intake duct (3), and an exhaust duct (4); The main engine (1) comprises a fan (5), a compressor (6), a main combustion chamber (7), a high-pressure turbine (8), a low-pressure turbine (9), an afterburner (10), and a nozzle (11) which are arranged in sequence; The main engine (1) and the ducted fan (2) are arranged in the fuselage, wherein the main engine (1) is located in the middle of the upper part of the fuselage; there are four ducted fans (2), which are respectively located at the upper left, upper right, lower left and lower right of the main engine (1) and arranged around the main engine (1); The outlet of the air inlet (3) is connected to the inlet of the main engine (1) and four ducted fans (2), and the inlet extends to the belly of the fuselage and is located in front of the belly of the fuselage; The inlet of the exhaust duct (4) is connected to the outlets of the main engine (1) and four ducted fans (2), and the outlet extends to the tail of the fuselage.

2. The supersonic UAV combined power system according to claim 1, characterized in that: It has high thrust working mode and low fuel consumption working mode; In the high-thrust working mode, the main engine (1) is working, afterburner is turned on, and the ducted fan (2) is not powered and is in a windmill state; In the low fuel consumption working mode, the main engine (1) is working without afterburner, and the ducted fan (2) is powered and in working condition.

3. The supersonic UAV combined power system according to claim 2 is characterized in that: A generator (16) and a generator (12) are arranged on the main engine (1); The generator (16) is sleeved on the front end of the high-voltage shaft (13) of the main engine (1) and is connected to the main engine (1) and the power supply system of the aircraft through a line; The generator (12) is sleeved on the rear end of the low-pressure shaft (14) of the main engine (1) and is connected to four ducted fans (2) through lines.

4. The supersonic UAV combined power system according to claim 3 is characterized in that: When the main engine (1) is started, the starter generator (16) is controlled to be in an electric mode to drive the high-voltage shaft (13) to rotate, and when the rotation speed of the high-voltage shaft (13) reaches the rotation speed required for starting the main engine (1), the main engine (1) is ignited to start the main engine (1); After the main engine (1) is started, the starter generator (16) is controlled to be in a power generation mode, so that the starter generator (16) generates electricity driven by the high-pressure shaft (13) to supply the main engine (1) and the aircraft's power supply system, and the generator (12) generates electricity driven by the low-pressure shaft (14) to supply the ducted fan (2) for operation.

5. The supersonic UAV combined power system according to claim 4, characterized in that: The inlet portion of the air inlet duct (3) is bent upward; The outlet of the exhaust duct (4) is provided with a special-shaped shielding nozzle (15) that bends upward.

6. A method for controlling a supersonic UAV combined power system, for controlling the supersonic UAV combined power system of claim 5, characterized in that: include: When the UAV takes off, accelerates, or flies at supersonic speed, the supersonic UAV combined power system is set to a high thrust working mode; When the UAV is flying at subsonic speed, the combined power system of the supersonic UAV is set to a low fuel consumption working mode; When the main engine (1) is started, the starter generator (16) is controlled to be in an electric mode to drive the high-voltage shaft (13) to rotate, and when the rotation speed of the high-voltage shaft (13) reaches the rotation speed required for starting the main engine (1), the main engine (1) is ignited to start the main engine (1); After the main engine (1) is started, the starter generator (16) is controlled to be in a power generation mode, so that the starter generator (16) generates electricity driven by the high-pressure shaft (13) to supply the main engine (1) and the aircraft's power supply system, and the generator (12) generates electricity driven by the low-pressure shaft (14) to supply the ducted fan (2) for operation.

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