A solid fuel ramjet rotating detonation combined power system

Abstract

The present invention belongs to the technical field of tactical weapon system layout and engine structure design, and specifically relates to a solid fuel ramjet rotating detonation combined power system, comprising: an air inlet, an isolation section, a main charge, a pre-detonator tube, and a rotating detonation combustion chamber. To address the current difficulty in organizing mixed combustion in the afterburner, the present invention proposes using a rotating detonation combustion chamber instead of a traditional isobaric combustion chamber, thereby improving the engine cycle thermal efficiency and making the engine structure more compact. Theoretical calculations show that this invention can increase the engine specific impulse by more than 5%. Furthermore, the present invention provides a systematic design solution in conjunction with a solid fuel ramjet rotating detonation combined engine.

Description

Technical Field

[0001] The present invention belongs to the technical field of tactical weapon system layout and engine structure design, and particularly relates to a solid fuel ramjet rotating detonation combined power system. Background Art

[0002] Currently, tactical weapon systems are gradually developing toward hypersonic speeds and long ranges. However, the solid rocket engines that traditional tactical missiles rely on are reaching a bottleneck, making it difficult to significantly increase their specific impulse. Replacing traditional solid rocket engines with solid ramjets is a key development direction for future tactical weapons. In solid-fuel ramjets, incoming air captured in the inlet carries the primary gas produced by the propellant combustion into the afterburner for mixing and combustion. The combustion efficiency directly determines the overall performance of the power system. In traditional isobaric afterburners, the primary gas and air burn via a diffusion flame in the shear layer. This combustion organization has low mixing efficiency, resulting in a larger afterburner size and a less compact engine structure. Summary of the Invention

[0003] (1) Technical issues to be solved

[0004] The technical problem to be solved by the present invention is: how to combine solid fuel ramjet, rotating detonation and solid rocket propulsion systems through a reasonable system layout to make the entire system structure more compact, improve the overall performance of the system, and achieve stable flight of the device while ensuring continuous thrust.

[0005] (2) Technical solution

[0006] In order to solve the above technical problems, the present invention provides a solid fuel ramjet rotating detonation combined power system, the power system comprising: an air inlet 1, an isolation section 3, a main charge 4, a pre-detonation tube 6, and a rotating detonation combustion chamber 7;

[0007] Among them, first, space is reserved in the nose cone of the air inlet 1 for installing the warhead and guidance elements;

[0008] Secondly, the booster-stage solid rocket engine is installed in the inner ring of the rotating detonation combustion chamber 7, which significantly shortens the length of the engine without affecting the operation of the rotating detonation combustion chamber 7;

[0009] The main charge 4 of the engine is installed behind the nose cone of the air inlet 1. When the flight Mach number increases to above 2, the main charge 4 ignites and burns. The rich primary gas generated by the main charge 4 is carried by the incoming air captured by the air inlet 1 and enters the rotating detonation combustion chamber 7.

[0010] In addition, after passing through the intake duct 1, the air needs to pass through an isolation section 3, and then pass through the choked flow channel to reach the sonic injection condition before entering the rotating detonation combustion chamber 7.

[0011] Among them, the isolation section 3 is set as a groove with flow directionality, which on the one hand reduces the total pressure loss of the forward airflow, and on the other hand effectively suppresses the back pressure transmission of the detonation wave of the rotating detonation combustion chamber 7, thereby avoiding the back pressure transmission from destroying the wave system structure of the intake duct 1.

[0012] Among them, the tail of the rotating detonation combustion chamber 7 adopts an expansion nozzle, and the booster-stage rocket engine adopts a Laval nozzle, ensuring that the two do not interfere with each other and can work normally.

[0013] The central components including the air intake duct 1 and the rotating detonation combustion chamber 7 are connected and fixed to the outer shell through the front end bracket 2 and the rear end bracket 5.

[0014] Among them, the control system circuit is arranged inside the front end bracket 2 and the rear end bracket 5, connecting the tail fin, the charge igniter and the booster rocket ignition system.

[0015] Among them, the rear end bracket 5, the booster rocket shell, and the rotating detonation combustion chamber shell are heat-bearing components, which are made of high-temperature alloy materials and adopt insulation measures.

[0016] Among them, the incoming air captured by the air inlet 1 passes through the isolation section 3, carrying the primary combustion gas generated by the solid propellant, and enters the rotating detonation combustion chamber 7 after passing through the choked flow channel. It is detonated with the help of the high-temperature and high-pressure gas generated by the pre-detonation tube 6, forming a rotating detonation wave. The high-temperature and high-pressure gas after the wave is discharged from the combustion chamber through the expansion nozzle, thereby generating continuous thrust to ensure stable flight of the device.

[0017] During the takeoff phase, the booster stage solid rocket engine continues to work, accelerating the flight device to above Mach 2. Then the booster stage propellant is exhausted, the main propellant 4 ignites and burns, and the engine enters the ramjet working mode.

[0018] The incoming air carries the primary combustion gas through the choked flow passage and enters the rotating detonation combustion chamber 7, thereby ensuring the sonic injection condition at the combustion chamber inlet.

[0019] Among them, the rear end bracket 5, pre-detonation tube 6, and rotating detonation combustion chamber 7 are made of nickel-based high-temperature alloy, the booster-stage rocket engine nozzle and the rotating detonation combustion chamber nozzle 11 are made of tungsten-molybdenum alloy, and the inner wall of the combustion chamber is pasted with carbon phenolic and epoxy resin insulation layers; the remaining components are made of heat-resistant stainless steel.

[0020] The main charge 4 uses hydrocarbon fuel-rich propellant, and the booster-stage rocket engine charge uses modified double-base propellant.

[0021] (3) Beneficial effects

[0022] As an advanced combustion organization method, rotating detonation has the advantages of high cycle thermal efficiency, compact structure, and continuous thrust. Using a rotating detonation combustion chamber instead of the traditional isobaric combustion chamber of a solid fuel ramjet engine can improve the engine's mixed combustion efficiency and shorten the engine's structural dimensions, thus offering potential performance advantages. This invention proposes a design for a solid fuel ramjet rotating detonation combined propulsion system, combining solid fuel ramjet, rotating detonation, and solid rocket propulsion systems to make the overall system design more compact. Theoretical calculations show that the use of this combined propulsion system can increase the engine's specific impulse by more than 5%.

[0023] Compared with the prior art, the technical effects of the present invention are embodied in the following aspects:

[0024] (1) Combine solid fuel ramjet, rotating detonation and solid rocket propulsion systems to improve the overall performance of the engine.

[0025] (2) Shorten the structural size of the entire system design through reasonable layout.

[0026] (3) The choked flow channel design satisfies the sonic injection conditions at the inlet of the rotating detonation combustion chamber.

[0027] (4) By adding an isolation section, the total airflow pressure loss can be minimized while suppressing the back pressure transmission.

[0028] (5) The pressure index design of the main charge is used to achieve adaptive adjustment of the primary gas flow rate according to the incoming air flow. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is the overall structural diagram of the technical solution of the present invention.

[0030] Figure 2-Figure 4 It is a schematic structural diagram of the technical solution of the present invention. DETAILED DESCRIPTION

[0031] In order to make the purpose, content and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below with reference to the accompanying drawings and examples.

[0032] In order to solve the above technical problems, the present invention provides a solid fuel ramjet rotating detonation combined power system, such as Figure 1 As shown, the power system includes: an air inlet 1, an isolation section 3, a main charge 4, a pre-blast tube 6, a rotating detonation combustion chamber 7, a booster rocket engine charge 8, a booster rocket engine nozzle 9, a tail fin 10, and a rotating detonation combustion chamber nozzle 11;

[0033] Among them, first, a large space is reserved in the nose cone of the air inlet 1 to install the warhead and guidance elements;

[0034] Secondly, the booster-stage solid rocket engine is installed in the inner ring of the rotating detonation combustion chamber 7, which significantly shortens the length of the engine without affecting the operation of the rotating detonation combustion chamber 7;

[0035] The main charge 4 of the engine is installed behind the nose cone of the air inlet 1. When the flight Mach number increases to above 2, the main charge 4 ignites and burns. The rich primary gas generated by the main charge 4 is carried by the incoming air captured by the air inlet 1 and enters the rotating detonation combustion chamber 7.

[0036] In addition, after passing through the intake duct 1, the air needs to pass through an isolation section 3, and then pass through the choked flow channel to reach the sonic injection condition before entering the rotating detonation combustion chamber 7.

[0037] Among them, the isolation section 3 is set as a groove with flow directionality, which on the one hand reduces the total pressure loss of the forward airflow, and on the other hand effectively suppresses the back pressure transmission of the detonation wave of the rotating detonation combustion chamber 7, thereby avoiding the back pressure transmission from destroying the wave system structure of the intake duct 1.

[0038] Among them, the tail of the rotating detonation combustion chamber 7 adopts an expansion nozzle, and the booster-stage rocket engine adopts a Laval nozzle, ensuring that the two do not interfere with each other and can work normally.

[0039] The central components including the air inlet 1 and the rotating detonation combustion chamber 7 are connected and fixed to the outer shell of the system design through the front end bracket 2 and the rear end bracket 5.

[0040] Among them, the control system circuit is arranged inside the front end bracket 2 and the rear end bracket 5, connecting the tail fin, the charge igniter and the booster rocket ignition system.

[0041] Among them, the rear end bracket 5, the booster rocket shell, and the rotating detonation combustion chamber shell are heat-bearing components, which are made of high-temperature alloy materials and adopt insulation measures.

[0042] Among them, the incoming air captured by the air inlet 1 passes through the isolation section 3, carrying the primary combustion gas generated by the solid propellant, and enters the rotating detonation combustion chamber 7 after passing through the choked flow channel. It is detonated with the help of the high-temperature and high-pressure gas generated by the pre-detonation tube 6, forming a rotating detonation wave. The high-temperature and high-pressure gas after the wave is discharged from the combustion chamber through the expansion nozzle, thereby generating continuous thrust to ensure stable flight of the device.

[0043] During the takeoff phase, the booster stage solid rocket engine continues to work, accelerating the flight device to above Mach 2. Then the booster stage propellant is exhausted, the main propellant 4 ignites and burns, and the engine enters the ramjet working mode.

[0044] The incoming air carries the primary combustion gas through the choked flow passage and enters the rotating detonation combustion chamber 7, thereby ensuring the sonic injection condition at the combustion chamber inlet.

[0045] Among them, the rear end bracket 5, pre-detonation tube 6, and rotating detonation combustion chamber 7 are made of nickel-based high-temperature alloy, the booster-stage rocket engine nozzle 9 and the rotating detonation combustion chamber nozzle 11 are made of tungsten-molybdenum alloy, and the inner wall of the combustion chamber is pasted with carbon phenolic and epoxy resin insulation layers; the remaining components are made of heat-resistant stainless steel.

[0046] The main charge 4 uses hydrocarbon fuel-rich propellant, and the booster-stage rocket engine charge 8 uses modified double-base propellant.

[0047] In a preferred embodiment of the present invention, each component is formed by machining and 3D printing, connected by threads and welding, and the threaded connections are sealed with glue.

[0048] Example 1

[0049] Solid-fuel ramjet engines require a booster-stage solid rocket to accelerate the flight device to above Mach 2, after which the ramjet mode can function normally. In the traditional solid-fuel ramjet engine layout, the afterburner chamber is long, and there is still a long booster-stage solid rocket engine behind the afterburner chamber. At the same time, a large space needs to be reserved for the layout of the aircraft's warhead, navigation, and control systems. These reasons make the engine structure longer and its stability reduced. The combustion chamber of a rotating detonation engine is usually annular, and the head of the combustion chamber needs to meet supersonic injection conditions. At the same time, the high pressure generated during operation will be transmitted back to the upstream of the combustion chamber, affecting the upstream flow organization.

[0050] The present invention solves the aforementioned problems through rational layout and design. First, a large space is reserved within the inlet nose cone for installing the warhead and guidance elements. Second, the booster-stage solid rocket engine is installed within the inner ring of the rotating detonation chamber, significantly shortening the engine length without affecting the operation of the rotating detonation chamber. The engine main charge is installed behind the inlet nose cone. When the flight Mach number increases to above 2, the main charge ignites and burns, and the resulting rich primary combustion gas is carried by the incoming air captured by the inlet into the rotating detonation chamber. In addition, after passing through the inlet, the air needs to pass through an isolation section and then through a choked flow channel to reach supersonic injection conditions before entering the rotating detonation chamber. The isolation section is designed with directional grooves, which not only reduce the total pressure loss of the forward airflow, but also effectively suppress the backpressure backflow of the rotating detonation chamber, preventing the backpressure backflow from damaging the wave structure of the inlet. The tail of the rotating detonation chamber uses an expansion nozzle, and the booster-stage rocket engine uses a Laval nozzle, ensuring that the two do not interfere with each other and can both operate normally. The central component is connected to the system's outer casing via a bracket. The control system wiring is routed through the bracket, connecting the tail fins, charge igniter, and booster rocket ignition system. The rear bracket, booster rocket casing, and rotating detonation combustor casing are heated components and require high-temperature alloy materials and thermal insulation.

[0051] The present invention belongs to the technical field of tactical weapon system layout and engine structure design, and specifically relates to a solid fuel ramjet rotating detonation combined power system. Compared with traditional solid rockets, the use of solid ramjet air-breathing power can significantly improve the engine specific impulse, thereby increasing the range of the aircraft. In a solid fuel ramjet engine, the incoming air carries the primary combustion gas produced by the combustion of the propellant into the afterburner for mixed combustion, and its mixed combustion efficiency directly determines the engine performance. In response to the problem that mixed combustion in the afterburner is difficult to organize, the present invention proposes the use of a rotating detonation combustion chamber instead of a traditional isobaric combustion chamber, thereby improving the thermal efficiency of the engine cycle and making the engine structure more compact. Theoretical calculations show that the invention can increase the engine specific impulse by more than 5%. At the same time, the present invention provides a systematic design solution in combination with a solid fuel ramjet rotating detonation combined engine.

[0052] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A solid fuel ramjet rotating detonation combined power system, characterized in that: The power system comprises: an air inlet (1), an isolation section (3), a main charge (4), a pre-detonation tube (6), and a rotating detonation combustion chamber (7); Among them, first, space is reserved in the nose cone of the air inlet (1) for installing the warhead and guidance elements; Secondly, the booster-stage solid rocket engine is installed in the inner ring of the rotating detonation combustion chamber (7), and the length of the engine is significantly shortened without affecting the operation of the rotating detonation combustion chamber (7); The main charge (4) of the engine is installed behind the nose cone of the air inlet (1). When the flight Mach number increases to above 2, the main charge (4) ignites and burns, and the fuel-rich primary combustion gas generated by the main charge (4) is carried by the incoming air captured by the air inlet (1) and enters the rotating detonation combustion chamber (7). In addition, after passing through the intake duct (1), the air needs to pass through an isolation section (3), and then pass through the choked flow channel to reach the sonic injection condition before entering the rotating detonation combustion chamber (7).

2. The solid fuel ramjet rotating detonation combined power system according to claim 1, characterized in that: The isolation section (3) is configured as a groove with flow directionality, which reduces the total pressure loss of the forward airflow on the one hand, and effectively suppresses the back-pressure transmission of the detonation wave of the rotating detonation combustion chamber (7) on the other hand, thereby preventing the back-pressure transmission from damaging the wave system structure of the intake duct (1).

3. The solid fuel ramjet rotating detonation combined power system according to claim 1, characterized in that: The tail of the rotating detonation combustion chamber (7) adopts an expansion nozzle, and the booster-stage rocket engine adopts a Laval nozzle, ensuring that the two do not interfere with each other and can both operate normally.

4. The solid fuel ramjet rotating detonation combined power system according to claim 1, characterized in that: The central components including the air inlet (1) and the rotary detonation combustion chamber (7) are connected and fixed to the outer shell through the front bracket (2) and the rear bracket (5).

5. The solid fuel ramjet rotating detonation combined power system according to claim 4, characterized in that: The control system circuit is arranged inside the front bracket (2) and the rear bracket (5), and is connected to the tail fin, the charge igniter and the booster rocket ignition system.

6. The solid fuel ramjet rotating detonation combined power system according to claim 5, characterized in that: The rear end bracket (5), the booster rocket shell, and the rotating detonation combustion chamber shell are heated components, are made of high-temperature alloy materials, and adopt thermal insulation measures.

7. The solid fuel ramjet rotating detonation combined power system according to claim 6, characterized in that: The incoming air captured by the air inlet (1) passes through the isolation section (3), and then carries the primary combustion gas generated by the solid propellant, enters the rotating detonation combustion chamber (7) through the choked flow channel, and is detonated with the help of the high-temperature and high-pressure gas generated by the pre-detonation tube (6), forming a rotating detonation wave. The high-temperature and high-pressure gas after the wave is discharged from the combustion chamber through the expansion nozzle, thereby generating continuous thrust to ensure the stable flight of the device.

8. The solid fuel ramjet rotating detonation combined power system according to claim 7, characterized in that: During the takeoff phase, the booster stage solid rocket engine continues to work, accelerating the flight device to a Mach number of more than 2. Then the booster stage propellant is exhausted, the main propellant (4) ignites and burns, and the engine enters the ramjet working mode.

9. The solid fuel ramjet rotating detonation combined power system according to claim 8, characterized in that: The incoming air carries the primary combustion gas through the choked flow channel and enters the rotating detonation combustion chamber (7), ensuring the sonic injection condition at the combustion chamber inlet.

10. The solid fuel ramjet rotating detonation combined power system according to claim 9, characterized in that: The rear end bracket (5), pre-detonation tube (6), and rotating detonation combustion chamber (7) are made of nickel-based high-temperature alloy, the booster rocket engine nozzle and the rotating detonation combustion chamber nozzle (11) are made of tungsten-molybdenum alloy, and the inner wall of the combustion chamber is pasted with carbon phenolic and epoxy resin insulation layers; the remaining components are made of heat-resistant stainless steel; The main charge (4) uses hydrocarbon fuel-rich propellant, and the booster-stage rocket engine charge uses modified double-base propellant.

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