Hybrid power system, control method and patrolling bomb

Abstract

The invention relates to the technical field of patrolling bombs, in particular to a hybrid power system, a control method and a patrolling bomb. The hybrid power system comprises a rotor engine, a rocket engine, a motor, a battery and a control unit; the rotor engine is connected with the propeller; the rocket engine is arranged at the tail of the patrolling bomb, comprises a powder supply cabin, an ignition device, a flameout device and a Laval nozzle, and can selectively ignite sub-combustion cabins with different sections or different dosages, so that the thrust of the rocket engine is accurately adjusted. The battery and the control unit respectively provide power supply and accurate control for each electromechanical structure, and power combination of the rotor engine and the rocket engine is realized, so that the patrolling bomb not only can realize long-time, long-distance and different-route patrolling and investigation flight, but also can quickly and accurately strike. The problem that in the prior art, a power system cannot meet the requirements of long-distance patrol investigation and rapid strike of the patrol projectile at the same time is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of cruise missiles, and specifically to a hybrid power system, a control method and a cruise missile, in particular to a rotary engine-solid rocket engine hybrid power system, a control method and a cruise missile. Background Art

[0002] Loitering Munition, also known as "wandering munitions", is an advanced unmanned combat weapon that combines the characteristics of drones and ammunition technology. It can cruise over the target area and mainly undertake combat missions such as battlefield reconnaissance, target indication, precision strikes, damage assessment, communication relay, electronic countermeasures, air alert and special payload delivery. Its biggest feature is that it can fly in the target area for a period of time and conduct reconnaissance. After determining the target, it can perform precision strike missions against ground targets and has the ability to search and identify the target and then quickly and accurately strike.

[0003] Rocket engines have extremely high thrust and can provide strong acceleration force in a short period of time, which is suitable for striking fast targets or long-range strike missions. Due to its instantaneous high thrust, rocket engines can quickly deliver cruise missiles to the target area or reach a higher flight speed at a certain stage. However, due to the space constraints of drones and the energy density of fuel, the flight time is limited, and solid fuel is difficult to control after ignition and the thrust cannot be switched. In addition, rocket engines are mostly suitable for simple straight flight or large-arc turning flight modes, and are not suitable for cruise missiles that hover and conduct long-term air endurance reconnaissance.

[0004] The rotary engine is light and small, suitable for aircraft with limited size. It has high fuel efficiency and is suitable for long-term cruising flight. It can provide stable high-speed operation and is suitable for electric propulsion or direct drive propellers. By using a rotary engine, the endurance and flight distance of cruise missiles can be significantly increased, and fuel consumption can be reduced. However, it is difficult to approach strike and reconnaissance targets at high speed, and it cannot meet the working conditions required for rapid battlefield strikes. It is costly and difficult to maintain.

[0005] Therefore, how to combine the short-term high-thrust capability of the rocket engine with the efficient endurance of the rotor engine is the basis for realizing the long-range cruise reconnaissance and rapid strike of cruise missiles. Summary of the invention

[0006] In view of the problem that the power system in the prior art cannot simultaneously meet the long-distance cruising reconnaissance and rapid strike requirements of a cruise missile, the present invention provides a hybrid power system, a control method and a cruise missile.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions: The present invention provides a hybrid power system, including a rotary engine, a rocket engine, a motor, a battery and a control unit; The rotor engine is connected to the propeller to drive the propeller to rotate and provide pulling force for the cruise missile's cruise reconnaissance; The rocket engine is arranged at the tail of the cruise missile to provide impulse for the acceleration of the cruise missile; the rocket engine includes a propellant supply cabin, an ignition device, a flameout device and a Laval nozzle, the propellant supply cabin is rotatably connected to the interior of the cruise missile, and a plurality of sub-combustion cabins with different cross-sections are arranged in the propellant supply cabin, and propellant columns are arranged in the sub-combustion cabins; the ignition device is arranged in the position of the sub-combustion cabin in the cruise missile; the flameout device is connected to the propellant supply cabin and is used to flameout the rocket engine; the Laval nozzle is connected to the propellant supply cabin; The moving end of the motor is connected to the propellant supply cabin and is used to drive the propellant supply cabin to rotate so that the corresponding sub-combustion cabin rotates to the ignition device for ignition; The battery is electrically connected to the motor, the ignition device and the flameout device; The control unit is electrically or communicatively connected with the rotary engine, the motor, the ignition device, the battery and the flameout device for controlling the switching of the power modes.

[0008] Optionally, a first gear is disposed at the moving end of the motor, a second gear is disposed at the front end of the medicine supply cabin, and the first gear is meshed with the second gear.

[0009] Optionally, the flameout device includes a vacuum pump, a flameout motor and an air baffle; the vacuum pump is arranged inside the propellant supply cabin, and is used to evacuate the air inside the sub-combustion cabin; the air baffle is hinged to the propellant supply cabin, and is used to block the air from entering the sub-combustion cabin from the Laval nozzle inlet; the moving end of the flameout motor is connected to the air baffle, and is used to drive the air baffle to rotate to block the air from entering the sub-combustion cabin; the vacuum pump and the flameout motor are both electrically connected to the battery, and are both electrically connected or communicatively connected to the control unit.

[0010] Optionally, the number of the sub-combustion chambers is set to 3.

[0011] Optionally, a preheating plug is also included, which is arranged on the rocket engine and connected to the tail end of the rotary engine, and is used to transfer the exhaust gas of the rotary engine to the rocket engine to preheat the propellant inside the propellant cabin.

[0012] Optionally, both ends of the medicine supply cabin are rotatably connected to the interior of the cruise missile via bearings.

[0013] The present invention also provides a cruise missile, comprising a warhead, a main wing, an auxiliary wing, a propeller, a cruise missile body and the above-mentioned hybrid power system; the propeller is arranged at the front end of the cruise missile body and connected to the moving end of the rotor engine; the hybrid power system is arranged inside the cruise missile body; the warhead is located inside the cruise missile body and between the rotor engine and the rocket engine; the main wing is arranged on both sides of the cruise missile body; the auxiliary wing is arranged at the tail end of the cruise missile body and is arranged on both sides of the cruise missile body.

[0014] Optionally, a fairing is provided on the outside of the propeller.

[0015] Optionally, the main wing is a foldable wing.

[0016] A method for controlling power of a cruise missile using the hybrid power system comprises: During the air delivery or ground launch phase of the cruise missile, the rocket engine is started, and the corresponding charge column in the subcombustion chamber is ignited according to the delivery target or launch target, so as to push the cruise missile to quickly approach the target; after reaching the designated position, the rocket engine is turned off; During the cruise flight phase: after the rocket engine is shut down, the rotor engine is started to provide traction for the cruise missile to hover and conduct reconnaissance and surveillance near the target; When locking onto a target, a rapid strike phase is required; the rotor engine is shut down, and the rocket engine is ignited again to propel the cruise missile toward the target and achieve a self-destructive strike.

[0017] Compared with the prior art, the present invention has the following beneficial effects: The present invention discloses a hybrid power system, comprising a rotor engine, a rocket engine, a motor, a battery and a control unit; the rotor engine is connected to a propeller to drive the propeller to rotate, and provide pulling force for the cruise reconnaissance of a cruise missile, and is suitable for the long-term cruise reconnaissance mission of the cruise missile, and ensures its endurance and stability. The rocket engine is arranged at the tail of the cruise missile, and can quickly provide a strong impulse when needed, accelerate the cruise missile to the required speed, or perform emergency maneuvers, thereby improving the flexibility and response speed of the cruise missile. By setting the rocket engine supply capsule, ignition device, flameout device and Laval nozzle structure, sub-combustion capsules with different cross-sections or different amounts of medicine can be selectively ignited, thereby achieving precise adjustment of the thrust of the rocket engine. This design enables the hybrid power system to flexibly adjust the power output according to the mission requirements, and improves the energy utilization efficiency; the setting of the flameout device allows the thrust of the rocket engine to be quickly cut off when necessary, ensuring the safety during the flight, and providing a technical basis for the switching of the power system. The electrical connection or communication connection between the control unit and each power component enables the system to monitor and control the power state in real time, realize the hardware coordination under different working modes of the cruise missile, and prevent the occurrence of unexpected situations. The hybrid power system proposed by the present invention realizes power regulation and reliable safety control in different scenarios through the combination of two power sources, the efficient rotor engine and the rocket engine, so that the cruise missile can realize long-term, long-distance, and different-route cruise reconnaissance flight, with a more flexible flight mode, and can also achieve rapid and accurate strikes, with more accurate and rapid strikes.

[0018] The moving end of the motor is provided with a first gear, and the front end of the medicine supply cabin is provided with a second gear, and the first gear is meshed with the second gear. Through the meshing of the first gear and the second gear, the motor can accurately adjust the angle and speed of the medicine supply cabin rotation, ensuring that the motor power can be stably and efficiently transmitted to the medicine supply cabin.

[0019] The flameout device includes a vacuum pump, a flameout motor and an air baffle; the vacuum pump is arranged inside the medicine supply cabin, and is used to evacuate the air inside the sub-combustion cabin; the air baffle is hinged to the medicine supply cabin, and is used to block the air from entering the sub-combustion cabin from the Laval nozzle inlet; the moving end of the flameout motor is connected to the air baffle, and is used to drive the air baffle to rotate to block the air from entering the sub-combustion cabin; the vacuum pump and the flameout motor are both electrically connected to the battery, and are both electrically or communicatively connected to the control unit; the vacuum pump is arranged inside the medicine supply cabin, and can quickly evacuate the air inside the sub-combustion cabin, thereby cutting off the oxygen supply required for combustion. This physical isolation method is more direct and effective than chemical fire extinguishing, and can quickly reduce the temperature and pressure in the combustion chamber to achieve rapid flameout.

[0020] The number of the sub-combustion chambers is three, which can provide the rocket engine with three different mode switchings, making the flight more flexible.

[0021] The glow plug is arranged on the rocket engine and connected to the tail end of the rotary engine, and is used to transfer the exhaust gas of the rotary engine to the rocket engine to preheat the grain inside the supply capsule, provide assistance for the re-ignition of the rocket engine, and be ready for its re-ignition at any time, thereby reducing the ignition delay time of the rocket engine, allowing the hybrid power system to provide thrust faster when a quick response is required, and improving the overall performance of the system. The design of the glow plug realizes the reuse of the exhaust gas of the rotary engine, converting the heat that might have been wasted into the preheating of the rocket engine grain, which not only improves the energy utilization efficiency, but also reduces energy consumption and environmental pollution.

[0022] The two ends of the medicine supply cabin are rotatably connected to the interior of the cruise missile through bearings, and the structure is simple and the stability is good.

[0023] The present invention also provides a cruise missile, including a warhead, a main wing, an auxiliary wing, a propeller, a cruise missile body and the above-mentioned hybrid power system; the propeller is arranged at the front end of the cruise missile body and connected to the moving end of the rotor engine; the hybrid power system is arranged inside the cruise missile body; the warhead is located inside the cruise missile body and between the rotor engine and the rocket engine; the main wing is arranged on both sides of the cruise missile body; the auxiliary wing is arranged at the tail end of the cruise missile body and is arranged on both sides of the cruise missile body. The cruise missile combines the advantages of the rotor engine power system and the rocket engine power, and has the advantages of superior flight performance, strong strike capability, high survivability, and adaptability to a variety of launch and combat methods, which promotes the development and application of cruise missile technology and provides a more efficient and reliable weapon option for future military operations.

[0024] The outer side of the propeller is provided with a fairing, which can significantly reduce wind resistance, thereby reducing the resistance encountered by the propeller during rotation, helping to reduce energy loss and improve the flight efficiency of the cruise missile.

[0025] The main wing is a foldable wing. During flight, the foldable wing can be adjusted in real time according to the flight status and mission requirements. When the lift-to-drag ratio needs to be improved to extend the airborne time, the wing can be fully unfolded to obtain a larger wing area. During high-speed or maneuvering flight, the wing can be partially or fully folded to reduce flight resistance and increase sprint speed. This makes the cruise missile more maneuverable in complex flight environments, better adapt to different flight postures and trajectories, and improve mission execution efficiency.

[0026] The present invention also provides a method for controlling the power of a cruise missile using the hybrid power system. The method starts the rocket engine during the air delivery or ground launch of the cruise missile, and selects to ignite the corresponding charge in the subcombustion chamber according to the delivery target or the launch target, so as to push the cruise missile to quickly approach the target. After reaching the designated position, the rocket engine is turned off. During the air delivery or ground launch of the cruise missile, the rocket engine can be started to quickly provide a powerful thrust for the cruise missile. This ability to quickly approach the target enables the cruise missile to reach the designated position in a short time, thus winning precious time for subsequent reconnaissance and strike missions. During the cruise flight stage: after the rocket engine is turned off, the rotor engine is started to provide traction for the cruise missile, so that it can hover and conduct reconnaissance and surveillance near the target. During the cruise flight stage, the rotor engine provides traction for the cruise missile, and the continuous operation of the rotor engine enables the cruise missile to hover and conduct reconnaissance and surveillance near the target for a long time, thereby collecting important battlefield information. During the stage of rapid strike after locking onto the target, the rotor engine is turned off and the rocket engine is ignited again to propel the cruise missile toward the target and achieve a self-destructive strike. At this time, the rocket engine plays its advantages and can strike the target quickly and powerfully. The method is simple and easy to operate, which not only enables rapid response and precise strikes, and enhances reconnaissance and surveillance capabilities, but also optimizes energy utilization and promotes the development and application of cruise missile technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 The figure is a schematic assembly diagram of a hybrid power system of the present invention.

[0028] Figure 2 It is a schematic diagram of the medicine supply cabin structure of the present invention.

[0029] Figure 3 It is a schematic diagram of the cross-sectional structure of the medicine supply cabin of the present invention.

[0030] Figure 4 It is a schematic diagram of the cross section of the Laval nozzle of the present invention.

[0031] Figure 5 The figure is a schematic diagram of the structure of the cruise missile of the present invention.

[0032] Figure 6 The present invention is a simplified flowchart of the power control method of the cruise missile.

[0033] Among them, 1-rotor engine, 2-rocket engine, 3-motor, 4-battery, 5-control unit, 6-propeller, 7-heat plug, 8-warhead, 9-main wing, 10-auxiliary wing, 11-cruise missile body, 12-fairing, 21-medicine supply cabin, 22-Laval nozzle, 23-sub-combustion cabin, 24-second gear, 25-vacuum pump, 26-air baffle, 27-bearing, 28-third gear, 29-fourth gear, 31-first gear. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0035] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0037] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0038] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0039] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" 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 or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] The present invention is further described in detail below in conjunction with specific embodiments, which are intended to explain the present invention rather than to limit it.

[0041] See also Figure 1 , the present invention provides a hybrid power system, comprising a rotary engine 1, a rocket engine 2, a motor 3, a battery 4, a control unit 5 and a glow plug 7; The rotary engine 1 is connected to the propeller 6 to drive the propeller 6 to rotate and provide pulling force for the cruise missile's cruise reconnaissance; See also Figures 1 to 4 The rocket engine 2 is arranged at the tail of the cruise missile to provide impulse for the acceleration of the cruise missile; the rocket engine 2 includes a propellant supply cabin 21, an ignition device, a flameout device and a Laval nozzle 22, both ends of the propellant supply cabin 21 are rotatably connected to the inside of the cruise missile through bearings 27, and the Laval nozzle 22 is connected to the propellant supply cabin 21; a plurality of sub-combustion cabins 23 with different cross-sections are arranged in the propellant supply cabin 21, and propellant columns are arranged in the sub-combustion cabins. Preferably, the sub-combustion cabins 23 are arranged in three; the ignition device is arranged in the position of the sub-combustion cabin 23 in the cruise missile; the flameout device and The propellant supply cabin 21 is connected to the rocket engine 2 for flameout, and comprises a vacuum pump 25, a flameout motor and an air baffle 26; the vacuum pump 25 is arranged inside the propellant supply cabin 21, and is used to evacuate the air inside the sub-combustion cabin 23; the air baffle 26 is hinged to the propellant supply cabin 21, and is used to block the air from entering the sub-combustion cabin 23 from the inlet of the Laval nozzle 22; the moving end of the flameout motor is provided with a third gear 28, and the air baffle 26 is provided with a fourth gear 29, and the third gear 28 is meshed with the fourth gear 29, and is used to drive the air baffle 26 to rotate to block the air from entering the sub-combustion cabin 23.

[0042] The moving end of the motor 3 is provided with a first gear 31, and the front end of the medicine supply cabin 21 is provided with a second gear 24. The first gear 31 is meshed with the second gear 24 to drive the medicine supply cabin 21 to rotate, so that the corresponding sub-combustion cabin 23 is turned to the ignition device for ignition; The battery 4 is electrically connected to the motor 3, the ignition device, the vacuum pump 25 and the flameout motor, and is used to provide power for the motor 3, the ignition device and the flameout device; the rotary engine 1 is connected to the battery 4, so that the rotary engine 1 not only outputs power to the propeller 6, but also ensures the storage of power in the battery 4.

[0043] The control unit 5 is an electronic control unit, which is electrically or communicatively connected to the rotary engine 1, the motor 3, the ignition device, the battery 4, the vacuum pump 25 and the flameout motor, and is used to control the power mode switching.

[0044] The preheat plug 7 is arranged on the rocket engine 2 and connected to the tail end of the rotary engine 1, and is used to transfer the exhaust gas of the rotary engine 1 to the rocket engine 2 to preheat the propellant column inside the propellant chamber 21; the preheat plug 7 is electrically connected to the battery 4, and is electrically connected or communicatively connected to the control unit 5.

[0045] This hybrid power system, through the combination of efficient rotary engines and rocket engines, achieves power regulation and reliable safety control in different scenarios. It enables the cruise missile to carry out long-term, long-distance, and different-route cruise reconnaissance flights with a more flexible flight mode, and can also achieve rapid and precise strikes, making the strikes more accurate and rapid.

[0046] See also Figure 5 The present invention provides a cruise missile, comprising a warhead 8, a main wing 9, an auxiliary wing 10, a propeller 6, a cruise missile body 11 and the above-mentioned hybrid power system; the propeller 6 is arranged at the front end of the cruise missile body 11 and connected to the moving end of the rotor engine 1, the propeller 6 is a spiral folding propeller, and a fairing 12 is arranged on the outer side of the propeller 6; the hybrid power system is arranged inside the cruise missile body 11; the warhead 8 is filled with gunpowder, located inside the cruise missile body 11, and located between the rotor engine 1 and the rocket engine 2; the main wing 9 is arranged on both sides of the cruise missile body 11 and is hinged to the cruise missile body 11; the main wing 9 is a foldable wing, when the rotor engine 1 stops rotating, the main wing 9 automatically folds back under the action of the cruise missile's oncoming air resistance, and is thrown away and works under the action of centrifugal force when the rotor engine 1 rotates; the auxiliary wing 10 is arranged at the tail end of the cruise missile body 11, and is arranged on both sides of the cruise missile body 11, to help the cruise missile maintain balance in flight.

[0047] Working Mode: During the air delivery or ground launch phase of the cruise missile, the main wing 9 is folded under the action of air resistance, the propeller 6 is folded, and the rocket engine 2 is started, pushing the cruise missile to approach the target at high speed; after reaching the designated position, the control unit 5 is used to control the flameout motor to operate, so that the air baffle 26 is closed, the inlet of the Laval nozzle 22 is blocked, and the air is blocked; the vacuum pump 25 is controlled to work and the rocket engine 2 is quickly turned off. The main wing 9 is opened, the rotor engine 1 is started, and the propeller 6 is driven to rotate and automatically open, providing thrust for the cruise missile, and performing long-term hovering and reconnaissance surveillance near the target. At the same time, the exhaust gas generated by the rotor engine 1 preheats the rocket engine 2 supply capsule 21 through the preheat plug 7, and is ready to ignite the rocket engine 2 at any time. When the target is locked and a rapid strike is required, the main wing 9 is folded, the rotor engine 1 is turned off, the propeller 6 automatically turns back after receiving air resistance, and the rocket engine 2 is quickly ignited, pushing the cruise missile to rush to the target at high speed and achieve a self-destructive strike; when the cruise missile needs to return, the rotor engine 1 or the rocket engine power 2 system can be selected according to the situation. During the operation of the rocket engine 2, the rocket engine supply capsule 21 can be rotated and the power gear can be switched according to the required thrust, providing different thrust sizes, thereby realizing power mode switching of different gears.

[0048] The cruise missile combines the advantages of a rotary engine power system and a rocket engine power system. It has the advantages of superior flight performance, strong strike capability, high survivability, and adaptability to a variety of launch and combat methods. It has promoted the development and application of cruise missile technology and provided a more efficient and reliable weapon option for future military operations.

[0049] See also Figure 6 The present invention provides a method for controlling the power of a cruise missile using the hybrid power system according to any one of claims 1 to 5, characterized in that it includes: S1: In the stage of air delivery or ground launch of the cruise missile, the rocket engine 2 is started, and the corresponding charge in the sub-combustion chamber 23 is ignited according to the delivery target or the launch target, so as to push the cruise missile to quickly approach the target; after reaching the designated position, the rocket engine 2 is turned off; S2: During the cruise flight phase: after the rocket engine 2 is shut down, the rotor engine 1 is started to provide traction for the cruise missile to hover and conduct reconnaissance and surveillance near the target; S3: When the target is locked, a rapid strike is required; the rotor engine 1 is turned off and the rocket engine 2 is ignited again to push the cruise missile towards the target and achieve a self-destructive strike.

[0050] This method fully utilizes the advantages of different power units by starting different power units for different mission modes. The method is simple and easy to operate. It can not only achieve rapid response and precision strikes, enhance reconnaissance and surveillance capabilities, but also optimize energy utilization and promote the development and application of cruise missile technology.

[0051] In summary, the present invention provides a hybrid power system, a control method and a cruise missile. The hybrid power system combines two kinds of power, a rotary engine and a rocket engine, and takes advantage of different power systems under different flight conditions. The high speed of the rocket engine is used when rapid acceleration is required on a long straight road, and the long endurance of the rotary engine is used when long-endurance low-speed flight is required. Different power sources are used accordingly through different flight missions, which not only enables the cruise missile to have long-time, long-distance, and different route cruising and reconnaissance capabilities, but also has the ability to quickly strike targets, has high survivability, and can adapt to a variety of launch and combat methods.

[0052] The above description is only a preferred embodiment of the present invention and is not intended to impose any limitation on the technical solution of the present invention. Those skilled in the art should understand that, without departing from the spirit and principles of the present invention, the technical solution can also be subjected to several simple modifications and substitutions, and these modifications and substitutions are also within the scope of protection covered by the claims.

Claims

1. A hybrid power system, characterized in that: It comprises a rotor engine (1), a rocket engine (2), a motor (3), a battery (4) and a control unit (5); The rotor engine (1) is connected to the propeller (6) and is used to drive the propeller (6) to rotate, thereby providing pulling force for the cruise missile's cruise reconnaissance; The rocket engine (2) is arranged at the tail of the cruise missile and is used to provide impulse for the acceleration of the cruise missile; the rocket engine (2) comprises a propellant supply cabin (21), an ignition device, a flameout device and a Laval nozzle (22); the propellant supply cabin (21) is rotatably connected to the interior of the cruise missile, and a plurality of sub-combustion cabins (23) with different cross-sections are arranged in the propellant supply cabin (21), and propellant columns are arranged in the sub-combustion cabins; the ignition device is arranged in the interior of the cruise missile at a position opposite to the sub-combustion cabins (23); the flameout device is connected to the propellant supply cabin (21) and is used to flameout the rocket engine (2); the Laval nozzle (22) is connected to the propellant supply cabin (21); The moving end of the motor (3) is connected to the propellant supply cabin (21) and is used to drive the propellant supply cabin (21) to rotate so that the corresponding sub-combustion cabin (23) rotates to the ignition device for ignition; The battery (4) is electrically connected to the motor (3), the ignition device and the flameout device; The control unit (5) is electrically or communicatively connected to the rotary engine (1), the motor (3), the ignition device, the battery (4) and the flameout device, and is used to control the switching of power modes.

2. The hybrid power system according to claim 1, characterized in that: A first gear (31) is provided at the moving end of the motor (3), a second gear (24) is provided at the front end of the medicine supply cabin (21), and the first gear (31) is meshed with the second gear (24).

3. The hybrid power system according to claim 1, characterized in that: The flameout device comprises a vacuum pump (25), a flameout motor and an air baffle (26); the vacuum pump (25) is arranged inside the propellant supply cabin (21) and is used to evacuate the air inside the sub-combustion cabin (23); the air baffle (26) is hingedly connected to the propellant supply cabin (21) and is used to block air from entering the sub-combustion cabin (23) from the inlet of the Laval nozzle (22); the moving end of the flameout motor is connected to the air baffle (26) and is used to drive the air baffle (26) to rotate and block air from entering the sub-combustion cabin (23); the vacuum pump (25) and the flameout motor are both electrically connected to the battery (4), and are both electrically connected or communicationally connected to the control unit (5).

4. The hybrid power system according to claim 1, characterized in that: The number of the sub-combustion chambers (23) is three.

5. The hybrid power system according to claim 1, characterized in that: It also includes a preheating plug (7), which is arranged on the rocket engine (2) and connected to the tail end of the rotor engine (1) and is used to transfer the exhaust gas of the rotor engine (1) to the rocket engine (2) to preheat the propellant column inside the propellant supply cabin (21).

6. The hybrid power system according to claim 1, characterized in that: Both ends of the medicine supply cabin (21) are rotatably connected to the interior of the cruise missile via bearings (27).

7. A cruise missile, characterized in that: The invention comprises a warhead (8), a main wing (9), an auxiliary wing (10), a propeller (6), a cruise missile body (11), and a hybrid power system according to any one of claims 1 to 6; the propeller (6) is arranged at the front end of the cruise missile body (11) and is connected to the moving end of the rotor engine (1); the hybrid power system is arranged inside the cruise missile body (11); the warhead (8) is located inside the cruise missile body (11) and between the rotor engine (1) and the rocket engine (2); the main wing (9) is arranged on both sides of the cruise missile body (11); the auxiliary wing (10) is arranged at the rear end of the cruise missile body (11) and is arranged on both sides of the cruise missile body (11).

8. The loitering missile according to claim 7, characterized in that: A fairing (12) is provided on the outside of the propeller (6).

9. The loitering missile according to claim 7, characterized in that: The main wing (9) is a foldable wing.

10. A method for controlling power of a cruise missile using the hybrid power system according to any one of claims 1 to 5, characterized in that: include: During the stage of air delivery or ground launch of the cruise missile, the rocket engine (2) is started, and the corresponding charge column in the sub-combustion chamber (23) is ignited according to the delivery target or the launch target, so as to push the cruise missile to quickly approach the target; after reaching the designated position, the rocket engine (2) is turned off; During the cruise flight phase: after the rocket engine (2) is shut down, the rotor engine (1) is started to provide traction for the cruise missile, so that it can hover and conduct reconnaissance and surveillance near the target; When a rapid strike is required after locking onto a target, the rotor engine (1) is turned off and the rocket engine (2) is ignited again to propel the cruise missile toward the target and achieve a self-destructive strike.

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