A three-mode combined detonation trigger mechanism

Abstract

This invention discloses a three-mode combined detonation engine configuration, arranged within an aircraft, including a fuel tank, an oxidizer tank, a rocket pulse detonation assembly, a rocket rotating detonation assembly, and a ramjet rotating detonation assembly. Specifically: the ramjet rotating detonation mode combustion chamber of the ramjet rotating detonation assembly is axially arranged at the rear of the aircraft, utilizing the air intake at the aircraft's chin; the rocket rotating detonation mode combustion chamber of the rocket rotating detonation assembly is arranged around the ramjet rotating detonation mode combustion chamber and shares a wall with it; the rocket pulse detonation assembly is distributed circumferentially around the isolation section of the ramjet rotating detonation assembly. This invention integrates multiple modes in a comprehensive design, fully leveraging the performance advantages of detonation engines and better meeting the actual power requirements of hypersonic vehicles.

Description

Technical Field

[0001] This invention belongs to the field of hypersonic vehicle propulsion technology, specifically relating to a three-mode combined detonation engine mechanism. Background Technology

[0002] As a form of power with self-pressurized combustion organization, the knock engine has higher cycle thermal efficiency and more concentrated combustion chemical reaction compared with the traditional isobaric combustion engine, which can improve the ultimate working performance of the power system and is a revolutionary supporting technology in the field of hypersonic power.

[0003] Detonation engines, based on their operating modes, mainly include ramjet rotary detonation engines, rocket rotary detonation engines, and rocket pulse detonation engines. Ramjet rotary detonation engines utilize air inhaled during high-speed flight as an oxidizer, which ignites and burns with injected fuel. The detonation wave rotates and propagates downstream, ultimately producing thrust as the exhaust gas is ejected from the nozzle. Rocket rotary detonation engines and rocket pulse detonation engines, on the other hand, require both oxidizer and fuel to be carried simultaneously. Rotary detonation engines operate through continuous detonation combustion, while pulse detonation engines operate through pulse ignition combustion according to a specific controlled timing sequence.

[0004] Currently, most research on detonation engines focuses on single-mode operation, with very few studies focusing on dual-mode operation, failing to fully utilize the advantages of various detonation engines. Summary of the Invention

[0005] The purpose of this invention is to provide a three-mode combined detonation engine design that integrates multiple modes to fully leverage the performance advantages of the detonation engine and better meet the actual power requirements of hypersonic vehicles.

[0006] To achieve the above objectives, the present invention employs the following technical solution: A three-mode combined detonation trigger mechanism is arranged inside an aircraft, including a fuel tank, an oxidizer tank, a rocket pulse detonation assembly, a rocket spinning detonation assembly, and a ramjet spinning detonation assembly, wherein: The ram-rotary detonation mode combustion chamber of the ram-rotary detonation assembly is axially arranged at the rear of the aircraft, and the ram-rotary detonation mode combustion chamber draws air from the air intake at the chin of the aircraft; the rocket rotary detonation mode combustion chamber of the rocket rotary detonation assembly is arranged around the ram-rotary detonation mode combustion chamber and shares a wall with the ram-rotary detonation mode combustion chamber; the rocket pulse detonation assembly is distributed circumferentially around the isolation section of the ram-rotary detonation assembly; The fuel tank supplies fuel to the rocket pulse detonation assembly, the rocket spin detonation assembly, and the ramjet spin detonation assembly via pipelines; the oxidizer tank supplies oxidizer to the rocket pulse detonation assembly and the rocket spin detonation assembly via pipelines.

[0007] Furthermore, the ram-rotary detonation assembly includes an air intake, an isolation section, a central cone, a ram-rotary detonation mode combustion chamber, and a ram-rotary detonation mode nozzle; The air intake is located at the chin of the aircraft to capture incoming airflow during flight; the ramjet rotating detonation mode nozzle is axially arranged at the tail of the aircraft, with its central cone coaxially fixed within the expansion section at the front end of the ramjet rotating detonation mode combustor; the ramjet rotating detonation mode combustor has a hollow barrel-shaped structure, and the air intake is connected to the expansion section at the front end of the ramjet rotating detonation mode combustor via an isolation section; the ramjet rotating detonation mode nozzle is located at the tail of the aircraft and connected to the rear end of the ramjet rotating detonation mode combustor.

[0008] Furthermore, when the three-mode combined detonation engine operates in ramjet-rotating detonation mode, the aircraft's flight process causes the air intake to capture incoming airflow. The airflow is rectified through the isolation section and enters the ramjet-rotating detonation mode combustion chamber along the wall under the action of the central cone. At the inlet of the ramjet-rotating detonation mode combustion chamber, fuel from the fuel tank is injected into the combustion chamber and interacts with the incoming airflow to ignite combustion. The rotating detonation wave rotates and propagates downstream in the ramjet-rotating detonation mode combustion chamber. Finally, the exhaust gas is ejected towards the tail of the aircraft through the ramjet-rotating detonation mode nozzle, generating positive thrust.

[0009] Furthermore, the rocket rotating detonation assembly includes a rocket rotating detonation mode combustion chamber and a rocket rotating detonation mode nozzle arranged at its rear. The rocket's rotating detonation mode combustion chamber has an annular structure; the rocket's rotating detonation mode nozzle is a Laval nozzle, arranged around the ramjet rotating detonation mode nozzle, and has an extension section; the rocket's rotating detonation mode nozzle exhausts exhaust gas to the rear of the spacecraft.

[0010] Furthermore, when the three-mode combined detonation engine operates in the rocket rotating detonation mode, the fuel in the fuel tank and the oxidizer in the oxidizer tank are mixed and injected into the rocket rotating detonation mode combustion chamber, causing detonation and combustion. The rotating detonation wave rotates and propagates downstream in the rocket rotating detonation mode combustion chamber, and finally the gas is ejected through the rocket rotating detonation mode nozzle to generate positive thrust.

[0011] Furthermore, the rocket pulse detonation assembly includes a rocket pulse mode injector, a rocket pulse mode combustion chamber, and a rocket pulse mode nozzle; The rocket pulse detonation assembly is evenly arranged around the rear end of the isolation section. The rocket pulse mode injector is connected to the fuel tank and oxidizer tank through pipelines. The rocket pulse mode combustion chamber is a spiral combustion chamber, with the rocket pulse mode injector and rocket pulse mode nozzle connected to its front and rear ends, respectively. The rocket pulse mode nozzle exhausts gas to the side of the spacecraft.

[0012] Furthermore, when the three-mode combined detonation engine operates in rocket pulse detonation mode, the fuel in the fuel tank and the oxidizer in the oxidizer tank are mixed and injected into the rocket pulse mode combustion chamber through the rocket pulse mode injector, causing detonation and generating pulse detonation waves; under the action of the pulse detonation waves, the fuel and oxidizer are fully combusted and ejected through the rocket pulse mode nozzle to generate the lateral thrust of the spacecraft.

[0013] Furthermore, the rocket pulse detonation assembly, the rocket rotary detonation assembly, and the ram-jet rotary detonation assembly can operate individually or simultaneously.

[0014] Furthermore, both the fuel tank and the oxidizer tank are located on the outer periphery of the rear end of the isolation section of the ram-rotary detonation assembly.

[0015] Furthermore, the central cone is made of refractory alloy material, and the rocket pulse mode combustion chamber, rocket rotary mode combustion chamber, and ramjet rotary mode combustion chamber are all made of high-temperature alloy material.

[0016] An aircraft whose engine employs the aforementioned three-mode combined detonation engine design.

[0017] Compared with the prior art, the present invention has the following technical features: 1. This invention organically combines three types of detonation engines: ramjet rotary detonation, rocket rotary detonation, and rocket pulse detonation, to achieve a three-mode combined detonation force on a single aircraft.

[0018] 2. This invention can operate in stamping rotational detonation mode, rocket rotational detonation mode, and rocket pulse detonation mode, or any two modes can operate simultaneously, or three modes can operate simultaneously, for a total of seven operating modes.

[0019] 3. Based on the different states of the aircraft during flight, this invention can intelligently switch between different working modes to meet the various performance requirements of the aircraft, greatly enrich the power forms of the aircraft, and effectively improve the working performance of the aircraft. Attached Figure Description

[0020] Figure 1 This is a structural diagram of the overall configuration of the three-mode combined detonation trigger mechanism; Figure 2 This is a structural diagram of a stamping rotary detonation assembly; Figure 3 This is a structural diagram of a rocket rotating detonation assembly. Figure 4 This is a structural diagram of the rocket pulse detonation assembly.

[0021] Explanation of reference numerals in the attached drawings: 1. Aircraft; 2. Fuel tank; 3. Oxidant tank; 4. Rocket pulse detonation assembly; 5. Rocket rotating detonation assembly; 6. Ram-jet rotating detonation assembly; 41. Rocket pulse mode injector; 42. Rocket pulse mode combustor; 43. Rocket pulse mode nozzle; 51. Rocket rotating detonation mode combustor; 52. Rocket rotating detonation mode nozzle; 61. Air intake; 62. Isolation section; 63. Center cone; 64. Ram-jet rotating detonation mode combustor; 65. Ram-jet rotating detonation mode nozzle. Detailed Implementation

[0022] To meet the actual power requirements of hypersonic vehicles, combining multiple modes of detonation engines and adjusting their operating status according to actual flight needs is of great significance for fully leveraging the performance advantages of detonation engines and improving the flight performance of hypersonic vehicles.

[0023] This invention provides a three-mode combined detonation engine configuration, achieving three detonation engine forms—ramjet rotary detonation, rocket rotary detonation, and rocket pulse detonation—within the limited volume constraints of the aircraft 1. It intelligently switches between different modes according to different states of the aircraft during flight, meeting various performance requirements of the aircraft. The outstanding advantage of this invention is that it achieves multiple mode combinations within the compact space constraints of the projectile body, greatly enriching the aircraft's power configurations and significantly improving its operational performance.

[0024] like Figures 1 to 4 As shown, the present invention provides a three-mode combined detonation trigger mechanism, arranged inside an aircraft 1, including a fuel tank 2, an oxidizer tank 3, a rocket pulse detonation assembly 4, a rocket spinning detonation assembly 5, and a ramjet spinning detonation assembly 6; wherein: The fuel tank 2 supplies fuel to the rocket pulse detonation assembly 4, the rocket rotary detonation assembly 5, and the ram-rotary detonation assembly 6 via pipelines; the oxidizer tank 3 supplies oxidizer to the rocket pulse detonation assembly 4 and the rocket rotary detonation assembly 5 via pipelines.

[0025] See Figure 2 The ram-rotary detonation assembly 6 includes an air intake 61, an isolation section 62, a central cone 63, a ram-rotary detonation mode combustion chamber 64, and a ram-rotary detonation mode nozzle 65.

[0026] Specifically, the inlet of the air intake 61 is located at the chin of the aircraft 1 to capture incoming airflow during flight; the ram-rotor detonation mode nozzle 65 is axially arranged at the tail of the aircraft 1, and the central cone 63 is coaxially fixed within the expansion section at the front end of the ram-rotor detonation mode combustor 64 via a flange; the ram-rotor detonation mode combustor 64 is a hollow barrel-shaped structure, and the air intake 61 is connected to the expansion section at the front end of the ram-rotor detonation mode combustor 64 via an isolation section 62; the ram-rotor detonation mode nozzle 65 is a thermal congestion nozzle, located at the tail of the aircraft 1, and connected to the rear end of the ram-rotor detonation mode combustor 64.

[0027] When the three-mode combined detonation engine operates in ram-rotary detonation mode, the high-speed flight of the aircraft 1 causes the air intake 61 to capture the incoming airflow. The airflow is rectified through the isolation section 62 and enters the ram-rotary detonation mode combustion chamber 64 along the wall under the action of the central cone 63. At the inlet of the ram-rotary detonation mode combustion chamber 64, the fuel in the fuel tank 2 is injected into the combustion chamber and interacts with the incoming airflow to ignite and burn. The rotating detonation wave rotates and propagates downstream in the ram-rotary detonation mode combustion chamber 64. Finally, the gas is ejected towards the tail of the aircraft 1 through the ram-rotary detonation mode nozzle 65 to generate positive thrust.

[0028] To ensure the working performance of the ramjet rotary detonation mode, the intake duct 61 should have a wide intake margin, and the isolation section 62 should have sufficient length to isolate the back pressure of the ramjet rotary detonation mode combustion chamber 64.

[0029] See Figure 3 The rocket rotating detonation assembly 5 includes a rocket rotating detonation mode combustion chamber 51 and a rocket rotating detonation mode nozzle 52 arranged at its rear.

[0030] Specifically, the rocket rotating detonation mode combustion chamber 51 is an annular structure, arranged around the ram-jet rotating detonation mode combustion chamber 64, and shares a wall with the ram-jet rotating detonation mode combustion chamber 64 (i.e., the wall surfaces in contact between the two are shared, and are also the walls of both); the rocket rotating detonation mode nozzle 52 is a Laval nozzle, arranged around the ram-jet rotating detonation mode nozzle 65, and has an extension section; the rocket rotating detonation mode nozzle 52 exhausts exhaust gas to the rear of the spacecraft 1.

[0031] When the three-mode combined detonation engine operates in the rocket rotating detonation mode, the fuel in the fuel tank 2 and the oxidizer in the oxidizer tank 3 are mixed and injected into the rocket rotating detonation mode combustion chamber 51, causing detonation and combustion. The rotating detonation wave rotates and propagates downstream in the rocket rotating detonation mode combustion chamber 51, and finally the gas is ejected through the rocket rotating detonation mode nozzle 52 to generate positive thrust.

[0032] See Figure 4The rocket pulse detonation assembly 4 includes a rocket pulse mode injector 41, a rocket pulse mode combustion chamber 42, and a rocket pulse mode nozzle 43.

[0033] Among them, the rocket pulse detonation assembly 4 is arranged around the rear end of the isolation section 62 of the ram-rotary detonation assembly 6 (near the end of the ram-rotary detonation mode combustion chamber 64), with one arranged every 90° along the circumference of the spacecraft 1, for a total of four; the rocket pulse mode injector 41 is connected to the fuel tank 2 and the oxidizer tank 3 through pipelines; the rocket pulse mode combustion chamber 42 is a spiral combustion chamber, with its front and rear ends connected to the rocket pulse mode injector 41 and the rocket pulse mode nozzle 43, respectively; the rocket pulse mode nozzle 43 exhausts to the side of the spacecraft 1.

[0034] When the three-mode combined detonation engine operates in rocket pulse detonation mode, the fuel in fuel tank 2 and the oxidizer in oxidizer tank 3 are mixed and injected into rocket pulse mode combustion chamber 42 through rocket pulse mode injector 41, causing detonation and generating pulse detonation wave; under the action of pulse detonation wave, the fuel and oxidizer are fully combusted and ejected through rocket pulse mode nozzle 43 to generate lateral thrust of spacecraft 1.

[0035] In this design, the rocket pulse detonation assembly 4, the rocket rotary detonation assembly 5, and the ram-jet rotary detonation assembly 6 can work individually or simultaneously.

[0036] In one embodiment of the present invention, both the fuel tank 2 and the oxidizer tank 3 are arranged around the rear end of the isolation section 62 of the ram-rotary detonation assembly 6.

[0037] To withstand the extremely high temperatures of detonation combustion, the central cone 63 is made of refractory alloy material, and the rocket pulse mode combustion chamber 42, the rocket rotating mode combustion chamber 51, and the ram-rotation mode combustion chamber 64 are all made of high-temperature alloy material.

[0038] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A three-mode combined detonation trigger mechanism, characterized in that, The engine mechanism is arranged inside the aircraft (1) and includes a fuel tank (2), an oxidizer tank (3), a rocket pulse detonation assembly (4), a rocket spin detonation assembly (5), and a ramjet spin detonation assembly (6), wherein: The ram-rotary detonation mode combustion chamber (64) of the ram-rotary detonation assembly (6) is arranged axially at the rear of the aircraft (1), and the ram-rotary detonation mode combustion chamber (64) draws air through the air intake (61) at the chin of the aircraft (1); the rocket rotary detonation mode combustion chamber (51) of the rocket rotary detonation assembly (5) is arranged around the ram-rotary detonation mode combustion chamber (64) and shares a wall with the ram-rotary detonation mode combustion chamber (64); the rocket pulse detonation assembly (4) is distributed circumferentially around the isolation section (62) of the ram-rotary detonation assembly (6); The fuel tank (2) supplies fuel to the rocket pulse detonation assembly (4), the rocket rotary detonation assembly (5), and the ram-rotary detonation assembly (6) through pipelines; the oxidizer tank (3) supplies oxidizer to the rocket pulse detonation assembly (4) and the rocket rotary detonation assembly (5) through pipelines.

2. The three-mode combined detonation trigger mechanism according to claim 1, characterized in that, The ram-rotary detonation assembly (6) includes an air intake (61), an isolation section (62), a central cone (63), a ram-rotary detonation mode combustion chamber (64), and a ram-rotary detonation mode nozzle (65); The inlet of the air intake (61) is located at the chin of the aircraft (1) to capture the incoming flow during the flight of the aircraft (1); the ramjet rotating detonation mode nozzle (65) is arranged axially at the tail of the aircraft (1), and the central cone (63) is coaxially fixed in the expansion section at the front end of the ramjet rotating detonation mode combustion chamber (64); the ramjet rotating detonation mode combustion chamber (64) has a hollow barrel structure, and the air intake (61) is connected to the expansion section at the front end of the ramjet rotating detonation mode combustion chamber (64) through the isolation section (62); the ramjet rotating detonation mode nozzle (65) is located at the tail of the aircraft (1) and is connected to the rear end of the ramjet rotating detonation mode combustion chamber (64).

3. The three-mode combined detonation trigger mechanism according to claim 2, characterized in that, When the three-mode combined detonation engine operates in ram-rotation detonation mode, the flight process of the aircraft (1) causes the air intake (61) to capture the incoming airflow. The airflow is rectified through the isolation section (62) and enters the ram-rotation detonation mode combustion chamber (64) along the wall under the action of the central cone (63). At the inlet of the ram-rotation detonation mode combustion chamber (64), the fuel in the fuel tank (2) is injected into the combustion chamber and interacts with the incoming airflow to ignite and burn. The rotating detonation wave rotates and propagates downstream in the ram-rotation detonation mode combustion chamber (64). Finally, the gas is ejected towards the tail of the aircraft (1) through the ram-rotation detonation mode nozzle (65) to generate positive thrust.

4. The three-mode combined detonation trigger mechanism according to claim 1, characterized in that, The rocket rotating detonation assembly (5) includes a rocket rotating detonation mode combustion chamber (51) and a rocket rotating detonation mode nozzle (52) arranged at its rear. The rocket rotating detonation mode combustion chamber (51) has an annular structure; the rocket rotating detonation mode nozzle (52) is a Laval nozzle, which is arranged around the ram-press rotating detonation mode nozzle (65) and has an extension section; the rocket rotating detonation mode nozzle (52) exhausts exhaust to the rear of the spacecraft (1).

5. The three-mode combined detonation trigger mechanism according to claim 4, characterized in that, When the three-mode combined detonation engine operates in the rocket rotating detonation mode, the fuel in the fuel tank (2) and the oxidizer in the oxidizer tank (3) are mixed and injected into the rocket rotating detonation mode combustion chamber (51) to initiate combustion. The rotating detonation wave rotates and propagates downstream in the rocket rotating detonation mode combustion chamber (51). Finally, the gas is ejected through the rocket rotating detonation mode nozzle (52) to generate positive thrust.

6. The three-mode combined detonation trigger mechanism according to claim 1, characterized in that, The rocket pulse detonation assembly (4) includes a rocket pulse mode injector (41), a rocket pulse mode combustion chamber (42), and a rocket pulse mode nozzle (43); The rocket pulse detonation assembly (4) is evenly arranged around the rear end of the isolation section (62). The rocket pulse mode injector (41) is connected to the fuel tank (2) and the oxidizer tank (3) through pipelines. The rocket pulse mode combustion chamber (42) is a spiral combustion chamber, and its front and rear ends are respectively connected to the rocket pulse mode injector (41) and the rocket pulse mode nozzle (43). The rocket pulse mode nozzle (43) exhausts gas to the side of the aircraft (1).

7. The three-mode combined detonation trigger mechanism according to claim 6, characterized in that, When the three-mode combined detonation engine operates in rocket pulse detonation mode, the fuel in the fuel tank (2) and the oxidizer in the oxidizer tank (3) are mixed and injected into the rocket pulse mode combustion chamber (42) through the rocket pulse mode injector (41), causing detonation and generating pulse detonation waves; under the action of the pulse detonation waves, the fuel and oxidizer are fully combusted and ejected through the rocket pulse mode nozzle (43) to generate the lateral thrust of the aircraft (1).

8. The three-mode combined detonation trigger mechanism according to claim 1, characterized in that, The rocket pulse detonation assembly (4), the rocket rotary detonation assembly (5), and the ram-rotary detonation assembly (6) can work individually or simultaneously.

9. The three-mode combined detonation trigger mechanism according to claim 1, characterized in that, Both the fuel tank (2) and the oxidizer tank (3) are located on the outer periphery of the rear end of the isolation section (62) of the ram-rotary detonation assembly (6).

10. An aircraft whose engine employs the three-mode combined detonation engine configuration described in any one of claims 1-9.

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