Geo-astro shuttle powder metal fuel rotating detonation rocket ram combined cycle engine

Abstract

The application discloses a kind of earth Mars round trip powder metal fuel rotating detonation rocket ram combined cycle engine, belong to aerospace engine technical field, combined engine includes: rocket rotating detonation engine and ram rotating detonation engine, whole engine system uses powder metal as main fuel, by rocket rotating detonation engine and ram rotating detonation engine respectively organize combustion and jointly generate thrust.The application can give full play to rocket engine, ram engine and rotating detonation combustion mode respective advantage, utilize the advantages that powder metal fuel stability is good, energy density is high and can occur combustion reaction with multiple oxidizing agents, can satisfy future reusable aerospace vehicle, earth Mars round trip interplanetary spacecraft etc combined power propulsion demand.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aerospace engines, and more particularly relates to a powder metal fuel rotating detonation rocket ram combined cycle engine for earth-mars round trip. BACKGROUND

[0002] For half a century, with the increase of human space exploration activities in outer space, people yearn to explore deep space, and Mars is one of them. Many countries have launched spacecraft to Mars to survey its surface environment. The atmosphere of Mars is very thin, including 96% carbon dioxide, 1.93% argon and 1.89% nitrogen, with trace amounts of oxygen and water. For traditional launch vehicles, a large amount of fuel is needed to reach the surface of Mars and complete the Mars surface exploration, while powder detonation engines such as Mg / CO2 can well solve this problem.

[0003] The spacecraft launched from the earth carries magnesium powder and other powder metal fuels to fly to Mars. During the flight, the O2 in the oxidizer tank is consumed until it is exhausted. After the spacecraft lands on Mars, it collects CO2 in the Martian atmosphere using the day-night temperature difference of Mars and stores it in the form of liquid in the empty oxidizer tank, realizing the in-situ resource utilization of propellant materials and the reuse of the tank, and using Mg / CO2 and other propulsion systems as the power for Mars surface exploration and return orbit, completing the Mars exploration mission. Not only that, the storage form of powder metal propellant is solid particles, which has strong environmental temperature adaptability and does not have problems such as low-temperature vitrification and low-temperature condensation. Powder metal delivery and ignition do not require preheating, which enables the propulsion system to achieve long-term storage and timely response in high-cold environments such as near-earth space and outer space. In addition, the general energy density of powder metal is higher than that of traditional petrochemical fuels, which can generate more powerful thrust, so the engine using this fuel has very good prospects.

[0004] Rotating detonation engine refers to a new concept engine based on detonation combustion mode, which has the advantages of one-time detonation, fast combustion speed, high thermal efficiency, compact structure and the like, and is expected to bring a leap-forward development of aerospace propulsion technology. It uses the high-temperature and high-pressure gas generated by continuous rotating detonation wave to generate thrust, and has received high attention from countries around the world in recent years, and has become a research hotspot in the field of domestic and foreign scholars and industrial departments. It can be used as commercial space rocket power, high-speed unmanned aerial vehicle power, gas turbine power, and applied to various rockets and missiles, near-space vehicles, military aircraft, unmanned aerial vehicles and other fields, and has very good development prospects.

[0005] The future aerospace engine has the requirements of compact structure, high thermal efficiency and reusability, and the powder metal material detonation engine is a good choice. The detonation problem of powder metal fuel has been studied for a long time, and early research mainly involves explosive explosion, cloud bomb and safety explosion prevention. The fuels currently used in the detonation engine are mainly gas (such as hydrogen, methane, etc.) and liquid (such as gasoline, kerosene, etc.), but the volumetric heat value of these fuels is generally low. The development of condensate phase energetic material detonation technology, computer simulation technology and experimental measurement technology makes the detonation engine technology make great progress. The powder metal fuel detonation engine has attracted people's attention due to its high mass heat value, high storage and use safety, and no need to consider atomization. The powder metal fuel detonation engine can produce large thrust, which can meet the use requirements of aerospace vehicles for power devices, such as free shuttle across the atmosphere, long time work in the atmosphere and space, reusability and low cost, and represents the development direction of new aerospace power technology and is the strategic competition highland in the future aerospace field.

[0006] How to combine the advantages of various engines, fuels and combustion modes to design a combined engine with compact structure, reusability and high efficiency performance becomes the key problem. SUMMARY

[0007] In view of the defects of the prior art or the improvement requirements, the present application provides a kind of ground fire round trip powder metal fuel rotary detonation rocket ram combined cycle engine, its purpose is to arrange annular cavity type ramjet rotary detonation combustion chamber outside rocket rotary detonation combustion chamber, so that the thrust of combined cycle engine is generated by rocket rotary detonation engine and ramjet rotary detonation engine, and the combustion mode of rotary detonation is used to provide thrust, thereby solving the technical problem of low performance of engine combustion mode in the prior art.

[0008] To achieve the above purpose, according to one aspect of the present application, a kind of ground fire round trip powder metal fuel rotary detonation rocket ram combined cycle engine is provided, including engine shell, the inside of the engine shell is provided with ramjet center cone, ramjet rotary detonation combustion chamber, rocket rotary detonation combustion chamber, engine tail cone, oxidant tank and fuel tank;

[0009] The outer wall surface of the ramjet center cone is formed with the inner wall surface of the engine shell to form an adjustable inlet duct;The ramjet rotary detonation combustion chamber is arranged in the annular outside of the rocket rotary detonation combustion chamber, and the ramjet rotary detonation combustion chamber is communicated with the adjustable inlet duct;

[0010] The fuel tank is arranged at the middle part of the engine, and is used to provide metal powder fuel to the ramjet rotary detonation combustion chamber and the rocket rotary detonation combustion chamber respectively;

[0011] The oxidizer tank is arranged at the periphery of the middle part of the engine, and is used for providing oxidizer to the rocket rotating detonation combustion chamber;

[0012] The engine tail cone is arranged at one end of the rocket rotating detonation combustion chamber, and the adjustable tail nozzle blade is arranged outside the engine tail cone, the inner wall surface of the adjustable tail nozzle blade and the outer wall surface of the engine tail cone form the rocket rotating detonation combustion chamber nozzle, and the outer wall surface of the adjustable tail nozzle blade and the inner wall surface of the engine shell form the ramjet rotating detonation combustion chamber nozzle.

[0013] Preferably, the air inlet is an axisymmetric structure.

[0014] Preferably, the air flow is adjusted by adjusting the relative position between the ramjet center cone and the shell.

[0015] Preferably, the rocket rotating detonation combustion chamber nozzle and the ramjet rotating detonation combustion chamber nozzle are simultaneously adjusted by the adjustable tail nozzle blade, the adjustable tail nozzle blade is in the shape of an umbrella, and the adjustable tail nozzle blade is expanded and contracted by electromagnetic drive, so as to adjust the flow channels of the rocket rotating detonation combustion chamber nozzle and the ramjet rotating detonation combustion chamber nozzle.

[0016] Preferably, the fuel tank stores powder metal fuel such as magnesium powder, and the powder metal fuel such as magnesium powder is provided to the ramjet rotating detonation combustion chamber and the rocket rotating detonation combustion chamber through the fuel nozzles of the ramjet rotating detonation combustion chamber and the rocket rotating detonation combustion chamber respectively.

[0017] Preferably, the fuel nozzles of the ramjet rotating detonation combustion chamber are uniformly distributed on the wall surface of the ramjet rotating detonation combustion chamber, and the fuel nozzles of the rocket rotating detonation combustion chamber are uniformly distributed on the wall surface of the rocket rotating detonation combustion chamber.

[0018] Preferably, the oxidizer tank stores different oxidizers in the two stages of the earth-mars round trip, carries oxygen when starting from the earth, and collects carbon dioxide in the atmosphere of Mars after arriving at Mars.

[0019] Preferably, the fixed support plate is further arranged, and the fixed support plate is used for connecting the engine shell and the internal structure of the engine.

[0020] Compared with the prior art, the above technical scheme conceived by the present application can achieve the following beneficial effects:

[0021] 1. The ground-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine provided by the application, which comprises a rocket rotating detonation engine and a ramjet rotating detonation engine, and a ring cavity type ramjet rotating detonation combustion chamber is arranged outside the rocket rotating detonation combustion chamber, the thrust of the combined cycle engine is generated by the rocket rotating detonation engine and the ramjet rotating detonation engine and provided by the rotating detonation combustion mode, compared with the traditional constant pressure combustion propulsion mode, the detonation combustion has the advantages of fast energy release rate and self-pressurization, and is expected to simplify the combustion chamber structure, improve the thermal cycle efficiency and reduce the engine oil consumption, and is expected to have a revolutionary impact on the existing combustion propulsion mode, and theoretically can adapt to the air-breathing working mode in the Mach number range of 0-12+, thereby providing a new possible way for the research and development of a new type of space-air combined cycle power scheme.

[0022] 2. The ground-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine provided by the application, which ingeniously utilizes a control system to adjust and match the coordinated working mechanism of the two rotating detonation engines in the full speed range, meets the flexibility and high efficiency requirements of the rocket-ramjet-detonation combined cycle working in different working stages and modes, can improve the average acceleration and effective specific impulse performance of the rocket injection mode stage in the Ma0-2 rocket injection mode, reduce the fuel consumption, improve the entry orbit thrust and entry orbit efficiency, effectively alleviate the mutual restriction problem of the integrated design of the flow passage of the traditional RBCC engine, the structure of the embedded rocket and the working parameters, can effectively exert the advantages of air-breathing combined cycle and the performance of a large-thrust rocket engine, make the space-air flight mission more free, flexible and convenient, and realize horizontal take-off and landing and ground-to-fire round-trip interplanetary flight missions.

[0023] 3. The ground-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine provided by the application adopts a scheme of using metal powder as the main fuel, can adapt to different temperature states, and the energy density of the metal powder is generally higher than that of the traditional petrochemical fuel, so that a stronger thrust can be generated, and the scheme can save space to the greatest extent, optimize the tank structure and maximize the propulsion performance of the combined engine in the full speed range.

[0024] 4. The ground-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine provided by the application ingeniously utilizes the feature that the surface of Mars is rich in CO2, adopts powder metal such as Mg powder as the main fuel, greatly saves the oxidizing agent during the flight of the spacecraft in the Mars atmosphere, and lays a better foundation for the Mars exploration plan. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a structural schematic view of the ground-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine.

[0026] Figure 2 is a schematic diagram of the rocket rotary detonation engine working alone in the embodiment of the present application when Ma=0-2 and 10 or above until entering orbit;

[0027] Figure 3 is a schematic diagram of the rocket rotary detonation engine and ramjet rotary detonation engine working together in the embodiment of the present application when Ma=2-4;

[0028] Figure 4 is a schematic diagram of the ramjet rotary detonation engine working alone in the embodiment of the present application when Ma=4-10;

[0029] Figure 5 is a schematic diagram of the engine when the aircraft is flying in outer space without power in the embodiment of the present application;

[0030] Figure 6 is a schematic diagram of the orbit when the aircraft is flying from the earth to Mars in the embodiment of the present application;

[0031] Figure 7 is a schematic diagram of the orbit when the aircraft is flying from Mars to the earth in the embodiment of the present application.

[0032] In all the drawings, the same reference signs are used to represent the same elements or structures, in which: 1 - ramjet center cone; 2 - engine shell; 3 - fixed support plate; 4 - ramjet rotary detonation combustion chamber; 5 - rocket rotary detonation combustion chamber; 6 - engine tail cone; 7 - air inlet; 8 - oxidizer tank; 9 - fuel tank; 10 - fuel nozzle of the ramjet rotary detonation combustion chamber; 11 - fuel nozzle of the rocket rotary detonation combustion chamber; 12 - adjustable tail nozzle blade; 13 - rocket rotary detonation combustion chamber nozzle; 14 - ramjet rotary detonation combustion chamber nozzle. DETAILED DESCRIPTION

[0033] In order to make the objectives, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and do not limit the present application. In addition, the technical features involved in each embodiment of the present application described below can be combined with each other as long as there is no conflict.

[0034] As Figure 1As shown, the present application proposes a ground-to-space round trip powder metal fuel rotating detonation rocket ram combined cycle engine, which comprises a rocket rotating detonation engine and a ram rotating detonation engine, and adopts rotating detonation combustion mode to provide thrust. Specifically, the annular cavity type ram rotating detonation combustion chamber is arranged outside the rocket rotating detonation combustion chamber, and the thrust of the combined engine is generated by both the rocket rotating detonation engine and the ram rotating detonation engine.

[0035] Further, the engine comprises a ramjet center cone 1, an oxidizer tank 8, a fuel tank 9, an engine shell 2, a rocket rotating detonation combustion chamber 5, a ram rotating detonation combustion chamber 4, a tail nozzle, an engine tail cone 6 connected in sequence, the ramjet center cone 1 and the inner wall of the engine shell 2 form an adjustable inlet 7, the rocket rotating detonation combustion chamber 5 is surrounded by the annular cavity type ram rotating detonation combustion chamber 4, the tail nozzle is connected with the rocket rotating detonation engine, the inner passage formed by the adjustable tail nozzle blade 12 inner wall of the tail nozzle and the wall of the engine tail cone 6 is the nozzle of the rocket rotating detonation engine, the outer ring passage formed by the adjustable tail nozzle blade 12 outer wall of the tail nozzle and the inner wall of the engine shell 2 is the nozzle of the ram rotating detonation engine, and the adjustable inlet 7, the ram rotating detonation combustion chamber 4 and the ram rotating detonation combustion chamber nozzle 14 are connected in sequence.

[0036] Further, the engine shell 2 and the ramjet center cone 1 inside the engine shell 2 constitute the adjustable inlet 7, the inlet 7 is an axisymmetric structure, the ramjet center cone 1 is driven by hydraulic pressure to move forward and backward, the inlet cross-sectional area is changed, and thus the air flow is adjusted.

[0037] Further, the fuel nozzle 11 of the rocket rotating detonation combustion chamber and the fuel nozzle 10 of the ram rotating detonation combustion chamber are uniformly arranged in the circumferential direction.

[0038] Further, the rocket rotating detonation combustion chamber nozzle 13 and the ram rotating detonation combustion chamber nozzle 14 are simultaneously adjusted by the adjustable tail nozzle blade 12, the adjustable tail nozzle blade 12 is in the shape of an umbrella, is expanded and contracted by electromagnetic drive, and thus the flow channels of the rocket rotating detonation combustion chamber nozzle 13 and the ram rotating detonation combustion chamber nozzle 14 are adjusted.

[0039] Further, the rocket rotating detonation combustion chamber 5 and the ram rotating detonation combustion chamber 4 of the combined cycle engine both use powder metal such as magnesium powder as fuel, the rocket rotating detonation combustion chamber 5 uses O2 and CO2 as oxidants in the earth departure and Mars return stages respectively, and the ram rotating detonation combustion chamber 4 uses the earth atmosphere and the Mars atmosphere as oxidants respectively.

[0040] Further, the oxidizer tank 8 stores different oxidizers in two stages of the earth-mars round trip, carries O2 when starting from the earth, and collects Mars atmosphere CO2 for return power propulsion after reaching Mars.

[0041] The technical solutions of the present application are further illustrated below by specific embodiments, as shown in Figures 1-7

[0042] The earth-mars round trip powder metal fuel rotating detonation rocket ram combined cycle engine provided by the present application is used in an interplanetary spacecraft. In the process of earth-mars round trip flight, the working mode of the combined cycle engine is divided into the following stages:

[0043] Stage 1: The spacecraft takes off from the earth, the flight Mach number is 0-2, the ramjet center cone is located at the top, the adjustable inlet is at the maximum closed state, the tail nozzle is at the set opening, the solid fuel nozzle is opened, magnesium powder and other powder metals are injected into the rocket combustion chamber, the liquid oxidizer tank injects oxygen into the rocket rotating detonation combustion chamber, and the rocket rotating detonation engine works.

[0044] Stage 2: The flight Mach number is 2-4, the ramjet center cone moves backward, the adjustable inlet opens to a higher degree, the solid fuel nozzle injects fuel into the ramjet rotating detonation combustion chamber, and the ramjet rotating detonation engine works in mode.

[0045] Stage 3: The flight Mach number is 4-10, the ramjet center cone moves backward to the bottom, the adjustable inlet is fully opened, the ramjet rotating detonation combustion chamber works, the tail nozzle blades are closed, the liquid oxidizer tank nozzle is closed, and the rocket rotating detonation engine is closed.

[0046] Stage 4: The flight Mach number is above 10 until entering the earth parking orbit, the ramjet center cone moves forward to the top, the adjustable inlet is closed, the liquid oxidizer tank nozzle is opened, the tail nozzle blades are expanded, the detonation rocket nozzle is at the maximum opening, the detonation ramjet nozzle is closed, the rocket rotating detonation engine works, and the detonation ramjet combustion chamber is closed.

[0047] Stage 5: The spacecraft adjusts the orbit, the detonation rocket engine works continuously, the spacecraft accelerates to the second cosmic speed to escape the earth's gravity, and then enters the earth-mars double tangent orbit, which is the most energy-saving flight path of the interplanetary spacecraft.

[0048] Stage 6: The spacecraft uses the sun's gravity to fly towards Mars on the double tangent orbit, the tail nozzle is closed, the detonation rocket nozzle opening is reduced, the rocket rotating detonation engine is closed, and the spacecraft flies without power. ​

[0049] Stage 7, the vehicle approaches Mars, the liquid oxidizer tank nozzles are opened, the solid fuel nozzles inject fuel into the rocket-type rotating detonation combustion chamber, the detonation rocket engine works, and the vehicle accelerates into a Mars parking orbit;

[0050] Stage 8, the vehicle lands on Mars, the flight direction is reversed using the jet thruster, the engine end faces the Earth, the detonation rocket combustion chamber works, the engine performs reverse thrust deceleration, the vehicle flaps open for attitude control, and vertical landing on the surface of Mars is achieved.

[0051] Stage 9, the vehicle is parked on the surface of Mars, the oxygen in the liquid oxidizer tank is almost depleted, and after being emptied, it collects carbon dioxide using the day and night temperature difference on Mars, and stores it in liquid form, preparing for the next step of the vehicle returning to Earth;

[0052] Stage 10, the vehicle takes off from Mars, the flight Mach number is 0-2, the adjustable inlet is in the closed state, the detonation rocket nozzle is in the set opening, the solid fuel nozzle is opened, and the magnesium powder and other powdered metals are injected into the rocket-type rotating detonation combustion chamber, the liquid oxidizer tank nozzle is opened, and the carbon dioxide is injected into the detonation rocket combustion chamber, and the rocket-type rotating detonation engine works;

[0053] Stage 11, the flight Mach number is 2-4, the center cone of the ramjet moves backward, the adjustable inlet gradually opens, the inlet of the Mars atmosphere carbon dioxide is supplied to the detonation ram combustion chamber, the solid fuel nozzle injects fuel into the detonation ram combustion chamber, and the ram-type rotating detonation engine works in mode;

[0054] Stage 12, the flight Mach number is 4-10, the center cone moves to the bottom, the adjustable inlet is fully opened, the detonation ram combustion chamber works at full capacity, the tail nozzle blades are closed, the detonation ramjet nozzle is at the maximum opening, the liquid oxidizer tank nozzle is closed, the detonation rocket combustion chamber fuel nozzle is closed, and the rocket-type rotating detonation engine is closed;

[0055] Stage 13, the vehicle continues to accelerate until it enters a Mars parking orbit, the center cone of the ramjet moves forward to the top, the adjustable inlet is closed, the liquid oxidizer tank nozzle is opened, the tail nozzle blades are expanded, the detonation rocket nozzle is at the maximum opening, the rocket-type rotating detonation engine works, and the detonation ram engine stops running;

[0056] Stage 14, the rocket-type rotating detonation engine continues to work, the vehicle accelerates to escape the gravity of Mars, enters a geosynchronous orbit, and then decelerates to a set speed, the detonation rocket engine is closed, and the vehicle flies without power;

[0057] Stage 15, the vehicle approaches the Earth, uses the jet thruster to decelerate to the first cosmic speed, and enters a geosynchronous orbit;

[0058] Stage 16, the aircraft lands on the earth, experiences two stages of unpowered glide deceleration and powered controlled landing, and achieves a horizontal landing on the earth's surface.

[0059] Those skilled in the art can easily understand that the above description is only the preferred embodiment of the present application, and is not intended to limit the present application. Any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A ramjet combined cycle engine for a ground-to-fire reciprocating powder metal fuel rotary detonation rocket, comprising an engine casing (2), characterized in that, The engine housing (2) is provided with a ramjet engine center cone (1), a ramjet rotary detonation combustion chamber (4), a rocket-type rotary detonation combustion chamber (5), an engine tail cone (6), an oxidizer tank (8), and a fuel tank (9). The outer wall of the ramjet engine center cone (1) and the inner wall of the engine housing (2) form an adjustable air intake (7); the rocket-type rotary detonation combustion chamber (5) is surrounded by a ramjet rotary detonation combustion chamber (4), which is connected to the air intake (7). The fuel tank (9) is located in the middle of the engine and is used to supply powdered metal fuel to the ramjet rotary detonation combustion chamber (4) and the rocket rotary detonation combustion chamber (5), respectively. The oxidizer tank (8) is located in the middle of the engine and is used to supply oxidizer to the rocket-type rotating detonation combustion chamber (5); The engine tail cone (6) is located at one end of the rocket-type rotary detonation combustion chamber (5). An adjustable tail nozzle blade (12) is arranged around the outside of the engine tail cone (6). The inner wall surface of the adjustable tail nozzle blade (12) and the outer wall surface of the engine tail cone (6) form a rocket-type rotary detonation combustion chamber nozzle (13). The outer wall surface of the adjustable tail nozzle blade (12) and the inner wall surface of the engine casing (2) form a ram-type rotary detonation combustion chamber nozzle (14). The rocket-type rotating detonation combustion chamber nozzle (13) and the ramjet-type rotating detonation combustion chamber nozzle (14) are simultaneously adjusted by the adjustable tail nozzle blades (12). The adjustable tail nozzle blades (12) have an umbrella-shaped structure and are expanded and contracted by electromagnetic drive, thereby adjusting the flow channels of the rocket-type rotating detonation combustion chamber nozzle (13) and the ramjet-type rotating detonation combustion chamber nozzle (14).

2. The ramjet combined cycle engine for a ground-to-fire reciprocating powdered metal fuel rotary detonation rocket according to claim 1, characterized in that, The air intake (7) has an axisymmetric structure.

3. The ramjet combined cycle engine for a ground-to-fire reciprocating powdered metal fuel rotary detonation rocket according to claim 2, characterized in that, The airflow is adjusted by regulating the relative position between the central cone (1) of the ramjet engine and the housing (2).

4. The ramjet combined cycle engine for a reciprocating ground-to-fire powder metal fuel rotary detonation rocket according to claim 1, characterized in that, The fuel tank (9) stores magnesium powder metal fuel, which is supplied to the ram-type rotary detonation combustion chamber (4) and the rocket-type rotary detonation combustion chamber (5) through the fuel nozzle (10) of the ram-type rotary detonation combustion chamber and the fuel nozzle (11) of the rocket-type rotary detonation combustion chamber, respectively.

5. The ramjet combined cycle engine for a reciprocating ground-to-fire powder metal fuel rotary detonation rocket according to claim 1, characterized in that, The fuel nozzles (10) of the ram-type rotary detonation combustor are evenly distributed around the circumference of the wall of the ram-type rotary detonation combustor (4), and the fuel nozzles (11) of the rocket-type rotary detonation combustor are evenly distributed around the head of the rocket-type rotary detonation combustor (5).

6. The ramjet combined cycle engine for a reciprocating ground-to-fire powdered metal fuel rotary detonation rocket according to claim 1, characterized in that, The oxidant tank (8) stores different oxidants in the two stages of the round trip between Earth and Mars. It carries oxygen when it departs from Earth and collects carbon dioxide from the Martian atmosphere after arriving at Mars.

7. The ramjet combined cycle engine for a reciprocating ground-to-fire powder metal fuel rotary detonation rocket according to claim 1, characterized in that, It also includes a fixed support plate (3), which is used to connect the engine housing (2) to the internal structure of the engine.

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