Rotor-liquid rocket engine tandem type combined power system for unmanned aerial vehicle

Abstract

The invention discloses a rotor-liquid rocket engine tandem type combined power system for an unmanned aerial vehicle. The system adopts aviation kerosene as fuel, and comprises an oxidant supply system, a miniature liquid rocket engine power system, an engine control system and the like. The oxidant supply system and the fuel supply system are installed in the shell, and the engine control system adjusts the opening time of an oil supply valve and an igniter. On one hand, an oxidizing agent and aviation kerosene fuel enter the rotor engine through the conveying pipeline and are used for combustion acting to drive the centrifugal supercharging device to work; on the other hand, the gas enters the supercharging device, enters the rocket engine after being supercharged, is sprayed out through the exhaust nozzle after being atomized, mixed and ignited, and propulsion power is obtained. And after the power work of the first-stage rocket is finished, the connector is released from constraint, the shell of the patrolling device is abandoned, and the high-speed working state is ended. And at the moment, the built-in unmanned aerial vehicle is powered by the second-stage rotor engine and enters a low-speed cruising state.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle power, and in particular relates to a rotor-liquid rocket engine series combined power system for unmanned aerial vehicles. Background Art

[0002] Recently, small drone technology has developed rapidly, showing great vitality in the aviation field and becoming a hot spot for research in countries around the world. In addition, the introduction and application of new technologies such as information sharing technology and collaborative technology are promoting the expansion of small aircraft application areas, such as high-altitude reconnaissance, detection, disaster relief, and material delivery.

[0003] In order to expand the working range of the aircraft to high altitudes, the selection of the power system is crucial. The inverse triangular rotor engine is small in size, high in power-to-weight ratio, and has a long flight time, which can enable the aircraft to cruise at long distances, low speeds, and low fuel consumption; while the small liquid rocket engine has strong power and good acceleration performance, which can improve the response speed of the aircraft and quickly reach the target area.

[0004] Up to now, liquid rocket engines are mostly used in medium and large aerospace vehicles as the first few power systems. Micro-sized aircraft mostly use internal combustion engines, electric power, small turbojets and other engines as power. However, electric power has insufficient endurance, narrow working margin (working altitude, working temperature), and poor acceleration performance; small turbojet engines have high thrust, but too high fuel consumption; traditional internal combustion engines have poor power performance, and the engine power attenuation at high altitude is more obvious. Compared with the above power systems, the anti-triangular rotor engine is smaller in size, has a higher power-to-weight ratio, and has stronger endurance, and has good prospects in the field of high-altitude aircraft power systems.

[0005] However, the research on the combined power of the inverse delta rotor engine and liquid rocket engine is still blank. Applying the combined power of the inverse delta rotor engine and liquid rocket engine to micro-aircraft can take into account the advantages of both power systems and achieve the transition between high-speed operation and low-speed cruising. The combined power can be used for rapid response and arrival at the target area in the initial stage, and for long-duration cruising in the subsequent stage. It can be used for rapid disaster relief, reconnaissance and other functional aircraft, and has good application prospects. Summary of the invention

[0006] The purpose of the present invention is to provide a rotor-liquid rocket engine series combined power system for unmanned aerial vehicles to solve the above-mentioned technical problems. The present invention sets a micro liquid rocket engine as the first-stage patrol vehicle power, and an inverse triangular rotor engine as the second-stage unmanned aerial vehicle power, and at the same time drives the supercharging device to work. By setting a two-stage power system in series, the unmanned aerial vehicle's rapid response capability and long-term cruising capability are improved at the same time.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions:

[0008] A rotor-liquid rocket engine series combined power system for unmanned aerial vehicles, comprising an aircraft shell, an oxidant supply system and a fuel supply system arranged at the front section of the aircraft shell, a supercharging device, an inverse triangular rotor engine power system and an engine control system arranged at the middle section of the aircraft shell, and a micro liquid rocket engine power system arranged at the rear section of the aircraft shell;

[0009] The oxidizer supply system and the fuel supply system are connected to the inverse triangular rotor engine power system on the one hand, and are connected to the micro liquid rocket engine power system through a booster device on the other hand; the control system is used to control the fuel and oxidizer flow rates and the engine ignition timing.

[0010] A further improvement of the present invention is that the aircraft shell is cylindrical, including a patroller front section, a patroller middle section and a patroller tail section which are connected in sequence through connectors, and an unmanned aerial vehicle shell is arranged in the patroller middle section; the patroller middle section is divided into two stages, and after the first-stage micro liquid rocket engine power system completes the power work, the connector here is released, and the unmanned aerial vehicle shell is provided with thrust by the second-stage anti-triangular rotor engine power system.

[0011] A further improvement of the present invention is that the front section of the patrol vehicle is elliptical.

[0012] A further improvement of the present invention is that the oxidant supply system includes a central oxygen storage tank and an oxygen supply pipeline. The oxygen storage tank contains high-pressure oxygen and is arranged in the front section of the cruiser. One end of the oxygen supply pipeline is connected to the oxygen storage tank, and the other end is connected to the oxygen supply end of the inverse triangular rotor engine power system and the supercharging device, and the oxygen supply amount is adjusted by the main oxygen supply valve and the rotor engine oxygen supply valve respectively.

[0013] A further improvement of the present invention is that the fuel supply system includes a fuel tank, an oil supply pipeline and a fuel preheating pipeline. The fuel tank contains jet fuel, and the fuel tank is circumferentially installed on the oxygen storage tank. One end of the oil supply pipeline is connected to the fuel tank, and the other end is connected to the inverse triangular rotor engine power system and the fuel end of the supercharging device. The fuel supply amount is adjusted by the main oil supply valve and the rotor engine oil supply valve respectively; the fuel preheating pipeline is arranged at the micro liquid rocket engine power system, and is used for heat exchange with the high-temperature exhaust gas in the tail nozzle to achieve fuel preheating and improve combustion efficiency.

[0014] A further improvement of the present invention is that the supercharging device adopts a centrifugal supercharging structure, including a driving gear, a driven gear, a turbo pump main shaft, a supercharging turbine, a turbo pump housing, a turbo pump end cover and a support bearing;

[0015] The turbine pump housing and the turbine pump end cover form an inner cavity. The support bearing is installed on the middle section of the cruiser and is used to position the turbine pump main shaft. The driven gear is installed on the turbine pump main shaft and meshes with the driving gear. The booster turbine is installed in the turbine pump housing and has an interference fit with the turbine pump main shaft. The turbine pump housing is provided with an inlet and an outlet, which are respectively connected to the oxygen supply pipeline, the oil supply pipeline and the fuel preheating pipeline.

[0016] A further improvement of the present invention is that the inverse triangular rotor engine power system includes a carburetor, an intake manifold, a rotor engine body, a rotor engine igniter and an engine output spindle;

[0017] The carburetor is connected to the oil supply pipeline, and the intake manifold is connected to the oxygen supply pipeline; the carburetor and the oxygen supply pipeline are both connected to the intake pipe of the rotary engine body; the rotary engine igniter is controlled by the engine control system; the engine output main shaft passes through the rotary engine body, is connected to the driving gear, and outputs torque outward through rotation.

[0018] A further improvement of the present invention is that the micro liquid rocket engine power system includes an oxidizer injector, a fuel injection nozzle, a rocket engine igniter and a tail nozzle;

[0019] The oxidizer injectors are dispersedly arranged and vertically installed at the head of the tail nozzle. The fuel injector is connected to the fuel preheating pipeline and is circumferentially installed at the front section of the tail nozzle. It is arranged at an angle of 45° backward along the airflow direction. The rocket engine igniter is circumferentially arranged at the front section of the tail nozzle and is controlled by the engine control system. The tail nozzle is installed on the tail of the patrol vehicle.

[0020] A further improvement of the present invention is that the tail nozzle is in a convergent-divergent shape.

[0021] A further improvement of the present invention is that it includes a controller, an oxidant valve controller, an oil supply valve control circuit and an ignition control circuit;

[0022] The oxidizer valve controller and the fuel supply valve control circuit are respectively connected to the main supply valve, the rotor engine oxygen supply valve, the main fuel supply valve, and the rotor engine fuel supply valve. The valve opening is controlled by the controller electrical signal to control the fuel supply of the inverse delta rotor engine power system and the micro liquid rocket engine power system. The ignition control circuit is connected to the rotor engine igniter and the rocket engine igniter, and the ignition timing is controlled by the controller electrical signal.

[0023] Compared with the prior art, the present invention has at least the following beneficial technical effects:

[0024] In terms of working margin, the present invention adopts a combined power of an inverted triangular rotor engine and a liquid rocket engine and uses aviation kerosene as fuel. Compared with traditional single power, such as internal combustion engines and turbojet engines, the high-efficiency inverted triangular rotor engine and liquid rocket engine in the combined power system enable the aircraft to operate at a higher altitude and can be used in high-altitude, low-temperature and low-pressure working environments.

[0025] In terms of mission execution, the combined power of the present invention allows the aircraft to use a liquid rocket engine at the start of work or in the acceleration phase to obtain a higher flight speed and acceleration, which can be used for working conditions such as starting acceleration and rapid arrival; in the uniform flight phase, the aircraft abandons liquid rocket power and uses a rotary engine as power to maintain a longer flight time, which can be used for long-term cruising conditions near the target location.

[0026] In terms of power system layout, the inverted triangular rotor engine in the present invention serves as the UAV power system on the one hand, and drives a small supercharger through a crankshaft gear mechanism on the other hand to pressurize the liquid rocket engine fuel and oxidizer to achieve efficient combustion. The combined power space layout is efficient, occupies a smaller volume, increases the load of the UAV, and can carry more detection equipment, rescue supplies, fire extinguishing powder and other items. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of a rotor-liquid rocket engine series combined power system for a UAV in an embodiment of the present invention.

[0028] Figure 2 Schematic diagram of the cruiser housing in an embodiment of the present invention.

[0029] Figure 3 Schematic diagram of a boosting device in an embodiment of the present invention.

[0030] Figure 4 It is a schematic diagram of the power system of the inverted triangular rotor engine in an embodiment of the present invention.

[0031] Description of reference numerals:

[0032] 1 is the aircraft shell, 1-1 is the front section of the patrol aircraft, 1-2 is the middle section of the patrol aircraft, 1-3 is the tail of the patrol aircraft, 1-4 is the UAV shell, and 1-5 is the connector;

[0033] 2 is the oxidant supply system, 2-1 is the oxygen storage tank, 2-2 is the oxygen supply pipeline, 2-3 is the main oxygen supply valve, and 2-4 is the rotary engine oxygen supply valve;

[0034] 3 is the fuel supply system, 3-1 is the fuel tank, 3-2 is the fuel supply pipeline, 3-3 is the main fuel supply valve, 3-4 is the rotary engine fuel supply valve, and 3-5 is the fuel preheating pipeline;

[0035] 4 is a supercharging device, 4-1 is a driving gear, 4-2 is a driven gear, 4-3 is a turbo pump main shaft, 4-4 is a supercharging turbine, 4-5 is a turbo pump housing, 4-6 is a turbo pump end cover, and 4-7 is a support bearing;

[0036] 5 is the power system of the inverse triangular rotor engine, 5-1 is the carburetor, 5-2 is the intake manifold, 5-3 is the rotor engine body, 5-4 is the rotor engine igniter, and 5-5 is the engine output main shaft;

[0037] 6 is a micro liquid rocket engine power system, 6-1 is an oxidizer injector, 6-2 is a fuel injector, 6-3 is a rocket engine igniter, and 6-4 is a tail nozzle;

[0038] 7 is an engine control system, 7-1 is a controller, 7-2 is an oxidizer valve control circuit, 7-3 is a fuel supply valve control circuit, and 7-4 is an engine ignition control circuit. DETAILED DESCRIPTION

[0039] In the following, only some exemplary embodiments are briefly described. As those skilled in the art will appreciate, the described embodiments may be modified in various ways without departing from the spirit or scope of the present invention. Therefore, the drawings and descriptions are considered to be exemplary and non-restrictive in nature.

[0040] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0041] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0042] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0044] It should also be understood that the terms used in the present specification are only for the purpose of describing specific embodiments and are not intended to limit the present invention. As used in the present specification and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include plural forms.

[0045] It should be further understood that the term "and / or" used in the present description and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0046] Various structural schematic diagrams of the embodiments disclosed in the present invention are shown in the accompanying drawings. These figures are not drawn to scale, and some details are magnified and some details may be omitted for the purpose of clear expression. The shapes of various regions and layers shown in the figures and the relative sizes and positional relationships therebetween are only exemplary, and may deviate in practice due to manufacturing tolerances or technical limitations, and those skilled in the art may additionally design regions / layers with different shapes, sizes, and relative positions according to actual needs.

[0047] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0048] Example 1

[0049] like Figure 1As shown, the present invention provides a rotor-liquid rocket engine series combined power system for unmanned aerial vehicles, including an aircraft shell 1, and an oxidant supply system 2 and a fuel supply system 3 are arranged at the front section of the aircraft shell 1. The oxidant supply system 2 and the fuel supply system 3 are connected to the inverse triangular rotor engine power system 5 on the one hand, and are connected to the micro liquid rocket engine power system 6 through the supercharging device 4 on the other hand. In addition, the combined power system realizes the adjustment of ignition and fuel injection strategies through the control system 7.

[0050] like Figure 1 and Figure 2 As shown, in this embodiment, the aircraft shell 1 is cylindrical, including the front section 1-1 of the patrol vehicle, the middle section 1-2 of the patrol vehicle, and the tail section 1-3 of the patrol vehicle, and each part is connected by a connector 1-5. The unmanned aerial vehicle shell 1-4 is arranged in the middle section 1-2 of the patrol vehicle. Among them, the front section 1-1 of the patrol vehicle is elliptical to reduce air resistance; the middle section 1-2 of the patrol vehicle is divided into two stages. After the power work of the first-stage micro liquid rocket engine power system 6 is completed, the connector 1-5 here is released, and the unmanned aerial vehicle shell 1-4 is provided with thrust by the second-stage anti-triangular rotor engine power system 5 to achieve cruising.

[0051] like Figure 1 As shown, in this embodiment, the oxidant supply system 2, wherein the oxygen storage tank 2-1 contains high-pressure oxygen, is arranged in the front section 1-1 of the cruiser, one end of the oxygen supply pipeline 2-2 is connected to the oxygen storage tank 2-1, and the other end is connected to the intake main manifold 5-2 and the turbine pump housing 4-5, and the oxygen supply amount is adjusted by the oxygen supply main valve 2-3 and the rotary engine oxygen supply valve 2-4 respectively.

[0052] like Figure 1 As shown, in this embodiment, the fuel supply system 3, wherein the fuel tank 3-1 contains jet fuel, the fuel tank 3-1 is circumferentially mounted on the oxygen storage tank 2-1, one end of the fuel supply pipeline 3-2 is connected to the fuel tank 3-1, and the other end is connected to the carburetor 5-1 and the turbine pump housing 4-5. The fuel supply amount is adjusted by the main fuel supply valve 3-3 and the rotary engine fuel supply valve 3-4. The fuel preheating pipeline 3-5 is arranged in a zigzag manner along the tail nozzle 6-4.

[0053] like Figure 1 and Figure 3As shown, in this embodiment, the supercharging device 4 adopts a centrifugal supercharging structure, wherein the turbine pump housing 4-5 and the turbine pump end cover 4-6 form an inner cavity, and the support bearing 4-7 is installed on the cruiser middle section 1-2 for positioning the turbine pump main shaft 4-3. The driving gear 4-1 is connected to the engine main shaft 5-5, and the driven gear 4-2 is installed on the turbine pump main shaft 4-3, and meshes with the driving gear 4-1 according to the set gear ratio. The supercharger turbine 4-4 is installed in the turbine pump housing 4-5 and has an interference fit with the turbine pump main shaft 4-3. The turbine pump housing 4-5 is provided with an inlet and an outlet, which are respectively connected to the oxygen supply pipeline 2-2, the oil supply pipeline 3-2 and the fuel preheating pipeline 3-5.

[0054] like Figure 1 and Figure 4 As shown, in this embodiment, the inverted triangular rotor engine power system 5, wherein the carburetor 5-1 is connected to the oil supply pipeline 3-2, and the intake manifold 5-2 is connected to the oxygen supply pipeline 2-2. The carburetor 5-1 and the oxygen supply pipeline 2-2 are both connected to the intake pipe of the rotor engine body 5-3. The rotor engine igniter 5-4 is connected to the ignition control circuit 7-4, and is controlled by the electrical signal of the controller 7-1. The engine output main shaft 5-5 passes through the rotor engine body 5-3, is connected to the driving gear 4-1, and outputs torque outward by rotation.

[0055] like Figure 1 As shown, in this embodiment, the micro liquid rocket engine power system 6, wherein the oxidizer injector 6-1 is dispersedly arranged and vertically installed at the head of the tail nozzle 6-4, the fuel injector 6-2 is connected to the fuel preheating pipeline 3-5, circumferentially installed at the front section of the tail nozzle 6-4, and arranged at an angle of 45° backward along the airflow direction. The rocket engine igniter 6-3 is circumferentially arranged at the front section of the tail nozzle 6-4, connected to the engine ignition control circuit 7-4, and controlled by the electrical signal of the controller 7-1. The tail nozzle 6-4 is installed on the tail 1-3 of the cruiser, and is in a convergent-divergent shape, which is conducive to the convergence of subsonic airflow and acceleration to supersonic airflow discharge, so as to obtain better power performance.

[0056] like Figure 1 As shown, the engine control system 7 in this embodiment includes a controller 7-1, an oxidizer valve controller 7-2, an oil supply valve control circuit 7-3 and an ignition control circuit 7-3. The oxidizer valve controller 7-2 and the oil supply valve control circuit 7-3 are respectively connected to the main supply valve 2-3, the rotor engine oxygen supply valve 2-4, the main oil supply valve 3-3 and the rotor engine oil supply valve 3-4. The valve opening is controlled by the electrical signal of the controller 7-1 to control the fuel supply of the inverse triangular rotor engine power system 5 and the micro liquid rocket engine power system 6. The ignition control circuit 7-3 is connected to the rotor engine igniter 5-4 and the rocket engine igniter 6-3. The ignition timing is controlled by the electrical signal of the controller 7-1 to maintain stable operation of the engine.

[0057] Example 2

[0058] like Figures 1 to 4 As shown, the present invention provides a rotor-liquid rocket engine series combined power system for unmanned aerial vehicles, and its working process is as follows:

[0059] When the combined power system starts working, the oxidant and fuel enter the inverse triangular rotor engine power system 5 through the oxygen supply pipeline 2-2 and the oil supply pipeline 3-2 respectively from the oxygen storage tank 2-1 and the fuel tank 3-1, and enter the supercharging device 4 on the one hand. The controller 7 controls the opening of the oxygen supply main valve 2-3, the rotor engine oxygen supply valve 2-4, the oil supply main valve 3-3, and the rotor engine oil supply valve 3-4 to adjust the flow of the oxidant and the fuel. At the same time, the control system 7 first controls the ignition of the rotor engine igniter 5-4, and the rotor engine 5-4 starts working, driving the supercharging device 4 to start working. Part of the oxidant and the fuel enter the oxidant injection agent 6-1 and the fuel preheating pipeline 3-5 through supercharging, and are preheated, mixed and sprayed out, and ignited by the rocket engine igniter 6-3 and then sprayed out through the tail nozzle 6-4, providing power for the cruise vehicle, and the aircraft is in a high-speed working state. After reaching the designated area, the connectors 1-5 are released, the aircraft shell 1 disintegrates, the oxidant supply system 2, the fuel supply system 3, the supercharger 4, and the micro liquid rocket engine power system 6 are detached, and the inverse triangular rotor engine power system 5 is changed to natural aspiration and direct fuel injection, and continues to provide power for the UAV shells 1-4, and the aircraft switches to a long-flight cruise state. Through this combined power system, the aircraft can switch between two working modes, expand the working range, and extend the cruising time.

[0060] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the attached claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved.

[0061] In addition, it should be understood that although this specification is described in accordance with the implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation modes that can be understood by those skilled in the art. The above content is only to illustrate the technical idea of ​​the present invention, and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution according to the technical idea proposed by the present invention shall fall within the protection scope of the claims of the present invention.

Claims

1. A rotor-liquid rocket engine series combined power system for unmanned aerial vehicles, characterized in that: It includes an aircraft shell, an oxidant supply system and a fuel supply system are arranged at the front section of the aircraft shell, a supercharging device, an inverse triangular rotor engine power system and an engine control system are arranged at the middle section of the aircraft shell, and a micro liquid rocket engine power system is arranged at the tail section of the aircraft shell; The oxidizer supply system and the fuel supply system are connected to the inverse triangular rotor engine power system on the one hand, and are connected to the micro liquid rocket engine power system through a booster device on the other hand; the control system is used to control the fuel and oxidizer flow rates and the engine ignition timing.

2. A rotor-liquid rocket engine series combined power system for UAV according to claim 1, characterized in that: The aircraft shell is cylindrical, including the front section, middle section and tail section of the patrol vehicle, which are connected in sequence through connectors. The UAV shell is arranged in the middle section of the patrol vehicle. The middle section of the patrol vehicle is divided into two stages. After the first-stage micro liquid rocket engine power system completes the power work, the connector here is released, and the UAV shell is provided with thrust by the second-stage anti-triangular rotor engine power system.

3. The rotor-liquid rocket engine series combined power system for UAV according to claim 2, characterized in that: The front section of the rover is oval-shaped.

4. The rotor-liquid rocket engine series combined power system for unmanned aerial vehicles according to claim 2, characterized in that: The oxidant supply system includes a central oxygen storage tank and an oxygen supply pipeline. The oxygen storage tank contains high-pressure oxygen and is arranged in the front section of the cruiser. One end of the oxygen supply pipeline is connected to the oxygen storage tank, and the other end is connected to the oxygen supply end of the inverse triangular rotor engine power system and the supercharging device. The oxygen supply is regulated by the main oxygen supply valve and the rotor engine oxygen supply valve respectively.

5. The rotor-liquid rocket engine series combined power system for UAV according to claim 4, characterized in that: The fuel supply system includes a fuel tank, a fuel supply pipeline and a fuel preheating pipeline. The fuel tank contains jet fuel and is circumferentially installed on the oxygen storage tank. One end of the fuel supply pipeline is connected to the fuel tank, and the other end is connected to the fuel end of the inverse triangular rotor engine power system and the supercharging device. The fuel supply amount is adjusted by the main fuel supply valve and the rotor engine fuel supply valve respectively; the fuel preheating pipeline is arranged at the micro liquid rocket engine power system, and is used for heat exchange with the high-temperature exhaust gas in the tail nozzle to achieve fuel preheating and improve combustion efficiency.

6. A rotor-liquid rocket engine series combined power system for UAV according to claim 5, characterized in that: The supercharging device adopts a centrifugal supercharging structure, including a driving gear, a driven gear, a turbo pump main shaft, a supercharging turbine, a turbo pump housing, a turbo pump end cover and a supporting bearing; The turbine pump housing and the turbine pump end cover form an inner cavity. The support bearing is installed on the middle section of the cruiser and is used to position the turbine pump main shaft. The driven gear is installed on the turbine pump main shaft and meshes with the driving gear. The booster turbine is installed in the turbine pump housing and has an interference fit with the turbine pump main shaft. The turbine pump housing is provided with an inlet and an outlet, which are respectively connected to the oxygen supply pipeline, the oil supply pipeline and the fuel preheating pipeline.

7. A rotor-liquid rocket engine series combined power system for UAV according to claim 6, characterized in that: The power system of the inverse triangular rotary engine includes a carburetor, an intake manifold, a rotary engine body, a rotary engine igniter and an engine output spindle; The carburetor is connected to the oil supply pipeline, and the intake manifold is connected to the oxygen supply pipeline; the carburetor and the oxygen supply pipeline are both connected to the intake pipe of the rotary engine body; the rotary engine igniter is controlled by the engine control system; the engine output main shaft passes through the rotary engine body, is connected to the driving gear, and outputs torque outward through rotation.

8. The rotor-liquid rocket engine series combined power system for UAV according to claim 7, characterized in that: The micro liquid rocket engine power system includes an oxidizer injector, a fuel injector, a rocket engine igniter and a tail nozzle; The oxidizer injectors are dispersedly arranged and vertically installed at the head of the tail nozzle. The fuel injector is connected to the fuel preheating pipeline and is circumferentially installed at the front section of the tail nozzle. It is arranged at an angle of 45° backward along the airflow direction. The rocket engine igniter is circumferentially arranged at the front section of the tail nozzle and is controlled by the engine control system. The tail nozzle is installed on the tail of the patrol vehicle.

9. A rotor-liquid rocket engine series combined power system for UAV according to claim 8, characterized in that: The tail nozzle has a convergent-divergent shape.

10. The rotor-liquid rocket engine series combined power system for UAV according to claim 8, characterized in that: It includes a controller, an oxidant valve controller, a fuel supply valve control circuit and an ignition control circuit; The oxidizer valve controller and the fuel supply valve control circuit are respectively connected to the main supply valve, the rotor engine oxygen supply valve, the main fuel supply valve, and the rotor engine fuel supply valve. The valve opening is controlled by the controller electrical signal to control the fuel supply of the inverse delta rotor engine power system and the micro liquid rocket engine power system. The ignition control circuit is connected to the rotor engine igniter and the rocket engine igniter, and the ignition timing is controlled by the controller electrical signal.

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