CN210317475U

CN210317475U - Novel power device for military gyroplane

Info

Publication number: CN210317475U
Application number: CN201921237219.8U
Authority: CN
Inventors: 郝志宏; 郝振英; 蔡志玮; 乔拓
Original assignee: Shenzhen Tianying Aircraft Equipment Technology Co Ltd
Current assignee: Shenzhen Tianying Aircraft Equipment Technology Co Ltd
Priority date: 2019-08-02
Filing date: 2019-08-02
Publication date: 2020-04-14
Anticipated expiration: 2029-08-02

Abstract

The utility model discloses a novel power device for military gyroplane, which comprises a crankshaft, a star-shaped four-stroke engine, an igniter, a spark plug, an ignition sensor, a starting motor, a carburetor, a turbocharger, a silencer, an electronic injection system and a lubricating oil pump, wherein the crankshaft passes through the star-shaped four-stroke engine, the front end of the crankshaft is meshed with the starting motor through a gear, the lubricating oil pump is in extrusion contact with a cam, and the carburetor is communicated with an air inlet channel at the back of the star-shaped four-stroke engine; the electronic fuel injection system controls fuel injection quantity to the air inlet pipe, the turbocharger is communicated with an air inlet channel on the back of the star-shaped four-stroke engine, and a waste gas exhaust port of the turbocharger is fixed with the silencer; the ignition sensor is positioned at the front end of the crankshaft, and the igniter is connected with a spark plug high-voltage ignition wire. The utility model discloses a bent axle is shorter, and the accurate fuel economy of electricity injection fuel injection quantity has adopted turbocharging system, promotes fuel economy, can provide range and the region that extra power extension power used.

Description

Novel power device for military gyroplane

Technical Field

The utility model relates to a for military use gyroplane field especially indicates a novel power device for military use gyroplane.

Background

The piston type aircraft engine is mostly designed in a star shape, and is widely used by ship-based aircraft due to short crankshaft, strong battlefield survivability, compact structure and small occupied aircraft space. Compared with the traditional engine, the engine has the advantages of high reliability, light weight, high efficiency, good maintainability and strong survivability.

At present, a star-type piston four-stroke engine is not used in a military rotorcraft, the crankshaft of the star-type piston four-stroke engine is short, the structural space is small, the weight is light, and the engine with the star-type structure can stably rotate and has extremely small vibration.

The traditional engine adopts a carburetor to accurately control the air-fuel ratio of the engine under various working conditions, so that the running reliability and the economical efficiency of the engine are influenced. When the plateau is used for performing tasks, the atmospheric pressure and the air density gradually decrease due to the change of the altitude, and as a result, the air charge amount entering the engine decreases, and the maximum power of the engine decreases. Meanwhile, due to the reduction of the air density, the air-fuel ratio of the mixed gas improved by the carburetor is also made to be rich, so that the maximum power of the engine is further reduced. Rotorcraft using non-supercharged engines therefore typically fly at heights not exceeding 6000 metres.

SUMMERY OF THE UTILITY MODEL

The utility model provides a novel power device for military use gyroplane has solved for military use gyroplane and has not used star type piston four-stroke engine at present among the prior art, and wearing and tearing and fatigue degree are high, vibrate greatly, the gyroplane flight height not enough problem of non-supercharged engine.

The technical scheme of the utility model is realized like this:

a novel power device for a military gyroplane comprises a crankshaft, a star-shaped four-stroke engine, an igniter, a spark plug, an ignition sensor, a starting motor, a carburetor, a turbocharger, a silencer, an electronic injection system and a lubricating oil pump, wherein the crankshaft penetrates through the star-shaped four-stroke engine, the front end of the crankshaft is meshed with the starting motor through a gear, the front end of the crankshaft is in extrusion contact with the lubricating oil pump through a cam, and the lubricating oil pump is communicated with the interior of the star-shaped four-stroke engine through a pipeline; the carburetor is communicated with an air inlet channel on the back of the star-shaped four-stroke engine; the electronic injection system comprises a sensor, an electronic control unit and an oil injector, wherein the sensor acquires the operating parameters of the power device and sends the operating parameters to the electronic control unit, the electronic control unit controls the oil injector to inject oil into an air inlet pipe, and injected oil gas enters the star-shaped four-stroke engine through the carburetor; the turbocharger is communicated with an air inlet channel on the back of the star-shaped four-stroke engine, and an exhaust gas outlet of the turbocharger is fixedly connected with the silencer; the ignition sensor is positioned at the front end of the crankshaft, detects the rotation angle of the crankshaft, and sends a pulse signal to the igniter, the igniter is connected with the spark plug through a high-voltage ignition wire, the spark plug is fixed on the cylinder head and used for igniting the mixed gas of the star-shaped four-stroke engine, and the exhaust pipe of the star-shaped four-stroke engine is connected with the air inlet of the turbocharger.

As the preferred embodiment of the present invention, the star-type four-stroke engine includes a star-type casing, a gas distribution casing, a cylinder, a star-type main connecting rod, a articulated connecting rod and a piston, the gas distribution casing is fixed at the front end of the star-type casing, the cylinder is fixed on the side of the star-type casing, the star-type main connecting rod is fixed in the star-type casing, the articulated connecting rod is fixed at one end thereof to the star-type main connecting rod, the other end thereof is penetrated out of the gas distribution casing and is fixedly connected to the piston, and the piston is in reciprocating motion in the cylinder.

As the preferred embodiment of the present invention, the star-type four-stroke engine employs a dual spark plug ignition system.

As the utility model discloses a preferred embodiment, the sensor includes cylinder head temperature sensor, temperature sensor and bent axle position sensor admits air, cylinder head temperature sensor is located star type four-stroke engine's cylinder head, temperature sensor admits air is located star type four-stroke engine's admission line department, bent axle position sensor is located inside star type four-stroke engine.

As the utility model discloses a preferred embodiment still includes the installing support, the installing support includes loop forming element and horizontal component, horizontal component one end is fixed on the loop forming element, the other end is fixed star type receiver surface.

As the preferred embodiment of the present invention, the front end of the air distribution casing is fixed with the motor gear and the cam, the center of the motor gear and the cam is fixed at the front end of the crankshaft, the casing shell is fixed with the air distribution casing, wrapping the motor gear and the cam, and the starting motor is fixed on the casing shell.

As a preferred embodiment of the present invention, the front end of the casing housing is fixed with a thrust three-blade paddle and a cowling.

As a preferred embodiment of the present invention, the turbocharger includes a compressor wheel and a turbine, which are mounted on the same horizontal shaft in the turbocharger chamber.

The beneficial effects of the utility model reside in that:

the star piston four stroke engine crankshaft is shorter, thereby reducing wear and fatigue and producing less vibration.

The electric injection system is adopted, the electric injection oil injection quantity is accurate, the oil is saved, the atomization is good, the combustion is good, the power is strong, the discharge is good, and the adaptability is good.

By adopting the turbocharging system, the turbocharger can improve the output power of the engine or improve the fuel economy under the same output power by utilizing the heat and the flow of the discharged waste gas, and can provide 20 to 30 percent of additional power.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.

FIG. 1 is an exploded view of a novel power plant for a military rotorcraft in accordance with the present invention;

FIG. 2 is an assembly view of the novel power plant for a military rotorcraft of the present invention;

fig. 3 is an isometric view of a novel power plant for a military rotorcraft according to the present invention;

fig. 4 is a left side view of a novel power plant for a military rotorcraft in accordance with the present invention;

fig. 5 is a diagram of an electric injection system of the novel power plant for a military rotorcraft according to the present invention.

In the figure, 1-fairing; 2-thrust three-blade paddle; 3-lubricating oil pump; 4-starting the motor; 5-a gas distribution casing; 6-crankshaft; 7-cylindrical pins; 8-a cylinder head; 9-cylinder head temperature sensor; 10-a piston; 11-a spark plug; 12-an articulated connecting rod; 13-a silencer; 14-a carburetor; 15-a turbocharger; 16-a fuel injector; 17-mounting a bracket; 18-an igniter; 19-a star-shaped case; 20-a cylinder head; 21-star-shaped main link; 22-a cylinder; 23-an ignition sensor; 24-a motor gear; 25-a casing housing; 26-an intake passage; 27-an exhaust pipe; 28-an air inlet pipe; 29-cylinder liner; 30-an intake air temperature sensor; 31-a crankshaft position sensor; 32-an electronic control unit; 33-high pressure fuel pool; 34-a voltage regulator; 35-fuel filter.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

As shown in fig. 1-5, the utility model provides a novel power device for military gyroplane, including bent axle 6, star type four-stroke engine, some firearm 18, spark plug 11, ignition sensor 23, starter motor 4, carburetor 14, turbo charger 15, muffler 13, electronic fuel injection system, lubricating oil pump 3, bent axle 6 passes star type four-stroke engine, the front end passes through the gear and meshes with starter motor 4, the front end passes through cam extrusion contact lubricating oil pump 3, lubricating oil pump 3 communicates with each other through the inside of pipeline and star type four-stroke engine; the carburetor 14 is communicated with an air inlet channel on the back of the star-shaped four-stroke engine; the electronic injection system comprises a sensor, an electronic control unit 32 and an oil injector 16, wherein the sensor acquires the operating parameters of the power device and sends the operating parameters to the electronic control unit 32, the electronic control unit 32 controls the oil injector 16 to inject oil into an air inlet pipe, and the injected oil gas enters the star-shaped four-stroke engine through the carburetor 14; the turbocharger 15 is communicated with an air inlet channel on the back of the star-shaped four-stroke engine, and an exhaust gas outlet of the turbocharger 15 is fixedly connected with the silencer 13; the ignition sensor 23 is located at the front end of the crankshaft 6, detects the rotation angle of the crankshaft 6, and sends a pulse signal to the igniter 18, the igniter 18 is connected with the spark plug 11 through a high-voltage ignition wire, the spark plug 11 is fixed on the star-shaped four-stroke engine and used for igniting the mixed gas of the star-shaped four-stroke engine, and the exhaust pipe of the star-shaped four-stroke engine is connected with the air inlet of the turbocharger 15.

The crankshaft 6 is connected with the star-shaped case 19 through a bearing shaft hole; the front end of the crankshaft 6 is connected with the central hole of the star-shaped main connecting rod 21 through a bearing shaft hole; the lower end holes of the five articulated connecting rods 12 and the star-shaped main connecting rod 21 are connected with the shaft holes of the hole positions through cylindrical pins; the lower ends of the five articulated connecting rods 12 are respectively connected with five pistons 10 through the shaft holes of the cylindrical pins 7; the piston 10 is positioned in the cylinder sleeve 29 and can reciprocate; the cylinder sleeve 29 is positioned in the cylinder 22 and is coaxially matched with the cylinder; the lower end of the cylinder 22 is connected with a positioning hole on the surface of the star-shaped casing 19 through a screw, and the cylinder is fixed on the surface of the star-shaped casing; the cylinder head 8 is positioned on the cylinder 22, and the lower end of the cylinder head 8 is connected with the upper end of the cylinder 22 by a screw; the cylinder cover 20 is positioned on the cylinder head, and the lower end of the cylinder cover 20 is connected with the upper end of the cylinder head 8 by screws; the cylinder head temperature sensor 9 is arranged on the upper surface of the cylinder head 8 by screws; the crankshaft position sensor 31 is positioned in the star-shaped casing 19 and is mounted on the star-shaped casing by screws; the air inlet temperature sensor 30 is positioned on the air inlet pipe 28 and is connected with the air inlet pipe by screws; the spark plug 11 is positioned in the cylinder head 8, and the cylinder head 8 is in threaded connection with the spark plug 11; the air inlet end of the cylinder head 8 is connected with one end of an air inlet pipe 28 through a screw; the other end of the air inlet pipe 28 is screwed with the air inlet passage 26; the motor gear 24 is positioned on the crankshaft 6 and transmits torque by using a flat key; the starting motor 24 is positioned on one side of the casing shell 25, the starting motor 4 is fixed on the casing shell 25 through an L-shaped support and a screw, and the L-shaped support is convenient for mounting and debugging the meshing of the starting motor and the motor gear 24; the carburetor 14 is positioned at the upper end of the air inlet channel 26 at the back of the star-shaped casing 19 and is in threaded connection with the upper end of the air inlet channel at the back of the star-shaped casing 19; the oil injection end of the electronic injection element 16 is arranged in the carburetor 14, and the wiring end is arranged outside; the turbocharger 15 is located behind the intake passage on the back surface of the star type casing 19, and is screwed with the intake passage on the back surface of the star type casing 19. The air with increased pressure and density can be directly introduced into the air inlet channel at the back of the star-shaped casing, and the two ends are not required to be connected by pipes, so that the distance is shortened; the silencer 13 is connected with the exhaust gas outlet at the left end of the turbocharger 15 through screws; the exhaust pipe 27 is positioned at the lower end of the turbocharger 15 and is connected with the lower end of the turbocharger 15 through a screw; the lubricating oil pump 3 is positioned below the casing shell 25 and is connected with the casing shell 25 through screws; the gas distribution casing 5 is positioned on the right side of the star-shaped casing 19 and is connected with the star-shaped casing 19 through bolts; the igniter 18 is positioned on the mounting bracket 17 and is connected with the mounting bracket by a sheet metal bracket and a screw; the ignition sensor 23 is positioned on the casing shell 25 and is connected by screws, and the installation is convenient for the sensor to sense the rotation angle of the crankshaft; the mounting bracket 17 is positioned on the left side of the star-shaped casing 19 and is connected with the star-shaped casing through screws; the thrust three-blade propeller 2 is connected with a shaft hole of a crankshaft 6; the fairing 1 is connected with a shaft hole of a crankshaft 6 and is in screw connection with the thrust three-blade propeller 2; electronic control unit 32 may be installed in the cockpit console of the rotorcraft to facilitate the control of the operation of the electronic fuel injection system; the high-pressure fuel pool 33 is arranged at the tail part of the rotorcraft close to the engine, so that fuel can be supplied conveniently; the pressure regulator is positioned on the mounting bracket 17 and is connected by a screw; the fuel filter is positioned on the mounting bracket 17 and is connected with the pressure regulator and the high-pressure fuel tank through an oil pipe; the compressor wheel 36 and the turbine wheel 37 are mounted in the turbocharger chamber and need to be on the same horizontal axis.

When the engine reaches 1500 revolutions, the turbocharging system pushes the exhaust gas generated in the power stroke of the engine to the turbine and drives the compressor impeller on the other side to synchronously operate, the compressor impeller enters air from the air inlet of the air filter pipeline, and the air enters the channel for secondary compression after being compressed by the rotation of the blades and is injected into the cylinder for combustion. Increasing the air flow into the engine cylinders, the pressure and density of the air increases, which may allow more fuel to be fully combusted, thereby increasing combustion efficiency. By utilizing the heat and flow of the exhaust gas, the turbocharger can increase the output power of the engine or increase the fuel economy under the same output power, and can provide 20% -30% of additional power.

The electronic fuel injection system is adopted in the aspect of power, an Electronic Control Unit (ECU) is used as a control center, various running parameters (cylinder head temperature, air inlet temperature and engine rotating speed) of an engine are measured by various sensors (a cylinder head temperature sensor, an air inlet temperature sensor and a crankshaft position sensor) arranged on the engine, and fuel injection quantity of a fuel injector is accurately controlled according to a control program prestored in a computer, so that the engine can obtain combustible mixed gas with the optimal air-fuel ratio of 14.7:1 under various working conditions, and after the fuel injection concentration is adjusted to be the optimal fuel injection concentration, the atomization effect is good, combustion is more sufficient, and higher power is released. When the altitude rises, still can reduce the fuel injection quantity automatically and adjust ignition time, can navigate in the place of altitude. The electric injection fuel injection quantity is accurate, the fuel is saved, the atomization is good, the combustion is good, the power is strong, the discharge is good, and the adaptability is good.

When the engine starts, the electronic fuel injection system starts to work. The oil injector of the electronic injection system is equivalent to an electromagnetic control switch, and when an electromagnetic coil in the oil injector is controlled to be electrified and opened, the oil injector is opened to inject oil; when the control cuts off the solenoid current in the injector, the injector is closed. The electronic control unit can freely and accurately control the fuel injection quantity. The fuel injector directly injects fuel into the air inlet pipe to form mixed gas.

The utility model provides a novel power device of for military use gyroplane still includes high-pressure fuel oil pool, fires oil filter, voltage regulator, fires oil filter and is linked together with voltage regulator and high-pressure fuel oil pool respectively through the pipeline, and the voltage regulator still is linked together through pipeline and high-pressure fuel oil pool and sprayer.

The working principle of the utility model is as follows:

the power output gear of the starting motor 4 is meshed with the motor gear 24 to drive the crankshaft 6 to rotate, so that the engine is started. After the engine is started, the cam on the crankshaft extrudes the plunger of the lubricating oil pump 3 to spray oil to the star-shaped case 19, so that the aims of lubricating the crankshaft, the star-shaped main connecting rod and the articulated connecting rod are fulfilled.

The engine works in four strokes, the first suction (intake) stroke, the crankshaft 6 drives the star-shaped main connecting rod 21 to rotate, five shaft holes of the star-shaped main connecting rod 21 drive the five articulated connecting rods 12 to rotate, the articulated connecting rods drive the piston 10 to move from the top dead center to the bottom dead center, the intake valve is opened, and the mixture of gasoline and air enters the cylinder through the carburetor 14. The intake stroke ends when the piston reaches bottom dead center.

When the gyroplane flies to a plateau to execute a task, the altitude changes, the atmospheric pressure and the air density are gradually reduced, the air inflation quantity entering the engine is reduced, and the maximum power of the engine is reduced. The reduction of the air density makes the air-fuel ratio of the mixed gas in the carburetor rich, so that the maximum power of the engine is further reduced. Under standard conditions, the air-fuel ratio is approximately enriched by 4% for every 1000 meters increase in altitude. Considering the fluctuation of the actual temperature and pressure, the maximum air-fuel ratio can be enriched by about 6 percent when the actual altitude is increased by 1000 meters.

The cylinder head temperature sensor 9, the intake air temperature sensor 30 and the crankshaft position sensor 31 measure various operating parameters (cylinder head temperature, intake air temperature and engine speed) of the engine, and then accurately control the fuel injection amount of the fuel injector 16 according to a control program prestored in the electronic control unit 32. The fuel oil from the fuel pump 33 passes through the fuel filter 35 and the pressure regulator 34 to supply the oil with different oil pressures, so that the engine can obtain combustible mixture gas with the optimal air-fuel ratio of 14.7:1 under various working conditions.

When the engine reaches 1500 revolutions, the turbocharger 15 pushes the turbine 37 by the waste gas generated in the power stroke of the engine and drives the compressor impeller 36 on the other side to synchronously operate, the compressor impeller enters the air from the air inlet of the air filter pipeline, and the air enters the channel for secondary compression after being compressed by the rotation of the blades and then is injected into the cylinder for combustion. Increasing the air flow into the engine cylinders, the pressure and density of the air increases, which may allow more fuel to be fully combusted.

In the second compression stroke, the inlet valve and the exhaust valve are both closed, the crankshaft 6 continues to drive the piston 10 to move from the bottom dead center to the top dead center, the mixed gas of fuel oil and air is compressed, when the piston moves to the top, the pressure and the temperature are increased, the compression stroke is ended, and the mechanical energy is converted into the internal energy.

In the third power stroke, i.e. the compression stroke is about to end, at a moment before the piston 10 reaches the top dead center, the ignition sensor 23 sends out a pulse signal, and the igniter 18 of the ignition system receives the pulse signal and provides high-voltage electricity to the spark plug 11. The spark plug jumps to ignite the gas mixture in the cylinder, the piston operates at a very high speed to quickly cross the top dead center, and the gas mixture burns and expands quickly to do work, so as to push the piston to move downwards, drive the crankshaft 6 to output power to reach the bottom dead center, and convert the internal energy into mechanical energy after the power stroke is finished. The power device ignition system adopts double-piston ignition, and each cylinder head 8 is provided with two spark plugs, so that the flameout probability of an engine is reduced. The firing sequence fires in sequence counterclockwise, with 72 degrees difference for each cylinder.

And in the fourth exhaust stroke, after the power stroke is finished, the piston 10 reaches a bottom dead center, the crankshaft 6 drives the piston to move from the bottom dead center to the top dead center, at the moment, the exhaust valve is opened, and the combusted waste gas is exhausted through the exhaust valve. The exhaust gas generated in the power stroke pushes the turbine 37 and drives the compressor impeller 36 on the other side to synchronously operate, and is discharged to the outside through the silencer 13, so that the silencer can reduce the noise generated by exhaust. The compressor impeller 36 is used for introducing air from an air filter pipeline from an air inlet, performing rotary compression on the air by the blades, then introducing the air into the channel for secondary compression, and injecting the air into the cylinder for combustion. Increasing the air flow into the engine cylinders so that the air pressure and density increases during the intake (intake) stroke allows more fuel to be fully combusted, thereby increasing combustion efficiency. A part of the exhaust gas is discharged to the outside through the muffler 13, and the muffler reduces the howling sound generated by the exhaust gas. The exhaust is complete, the piston is at top dead center, the exhaust valve is closed, and the next intake stroke begins.

The size of the mechanism can be scaled according to a certain proportion according to actual conditions.

The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A novel power device for military gyroplanes, characterized in that: the engine comprises a crankshaft, a star-shaped four-stroke engine, an igniter, a spark plug, an ignition sensor, a starting motor, a carburetor, a turbocharger, a silencer, an electronic injection system and a lubricating oil pump, wherein the crankshaft penetrates through the star-shaped four-stroke engine, the front end of the crankshaft is meshed with the starting motor through a gear, the front end of the crankshaft is in extrusion contact with the lubricating oil pump through a cam, and the lubricating oil pump is communicated with the interior of the star-shaped four-stroke engine through a pipeline; the carburetor is communicated with an air inlet channel on the back of the star-shaped four-stroke engine; the electronic injection system comprises a sensor, an electronic control unit and an oil injector, wherein the sensor acquires the operating parameters of the power device and sends the operating parameters to the electronic control unit, the electronic control unit controls the oil injector to inject oil into an air inlet pipe, and injected oil gas enters the star-shaped four-stroke engine through the carburetor; the turbocharger is communicated with an air inlet channel on the back of the star-shaped four-stroke engine, and an exhaust gas outlet of the turbocharger is fixedly connected with the silencer; the ignition sensor is positioned at the front end of the crankshaft, detects the rotation angle of the crankshaft, and sends a pulse signal to the igniter, the igniter is connected with the spark plug high-voltage ignition wire, the spark plug is fixed on the star-shaped four-stroke engine and used for igniting mixed gas, and an exhaust pipe of the star-shaped four-stroke engine is connected with an air inlet of the turbocharger.

2. The novel power plant for military rotorcraft according to claim 1, characterized in that: the star-type four-stroke engine comprises a star-type casing, a gas distribution casing, a cylinder, a star-type main connecting rod, a articulated connecting rod and a piston, wherein the gas distribution casing is fixed at the front end of the star-type casing, the cylinder is fixed on the side surface of the star-type casing, the star-type main connecting rod is fixed in the star-type casing, one end of the articulated connecting rod is fixedly connected with the star-type main connecting rod, the other end of the articulated connecting rod penetrates out of the gas distribution casing and is fixedly connected with the piston, and the piston moves back and forth in the cylinder.

3. The novel power plant for military rotorcraft according to claim 1, characterized in that: the star four-stroke engine adopts a double-spark-plug ignition system.

4. The novel power plant for military rotorcraft according to claim 1, characterized in that: the sensor comprises a cylinder head temperature sensor, an air inlet temperature sensor and a crankshaft position sensor, wherein the cylinder head temperature sensor is positioned at the cylinder head of the star-shaped four-stroke engine, the air inlet temperature sensor is positioned at an air inlet pipeline of the star-shaped four-stroke engine, and the crankshaft position sensor is positioned inside the star-shaped four-stroke engine.

5. The novel power plant for a military rotorcraft according to claim 2, wherein: the mounting bracket comprises a ring-shaped piece and a horizontal piece, one end of the horizontal piece is fixed on the ring-shaped piece, and the other end of the horizontal piece is fixed on the outer surface of the star-shaped casing.

6. The novel power plant for a military rotorcraft according to claim 2, wherein: the gas distribution case is characterized in that a motor gear and a cam are fixed at the front end of the gas distribution case, the centers of the motor gear and the cam are fixed at the front end of a crankshaft, a case shell is fixed with the gas distribution case and wraps the motor gear and the cam, and the starting motor is fixed on the case shell.

7. The novel power plant for a military rotorcraft according to claim 6, wherein: and the front end of the casing shell is fixedly provided with a thrust three-blade paddle and a fairing.

8. The novel power plant for military rotorcraft according to claim 1, characterized in that: the turbocharger comprises a compressor impeller and a turbine, wherein the compressor impeller and the turbine are arranged on the same horizontal shaft in a turbocharger cavity.