RBCC engine hydrogen peroxide thrust chamber with high-heat-load composite pre-cooling system and starting method of RBCC engine hydrogen peroxide thrust chamber

Abstract

The invention discloses an RBCC engine hydrogen peroxide thrust chamber with a high-heat-load composite pre-cooling system and a starting method, and solves the problems that the structure temperature of the hydrogen peroxide thrust chamber cannot meet the safe use condition of hydrogen peroxide under the high-heat-load condition, so that the hydrogen peroxide cannot be safely used when normal-temperature hydrogen peroxide is introduced into a cooling channel of the thrust chamber; in order to solve the technical problems that hydrogen peroxide is subjected to thermal decomposition reaction when making contact with the wall face of a thrust chamber, a large amount of high-temperature steam and oxygen are generated, and explosion of the thrust chamber is possibly caused when the high-temperature steam and oxygen are serious, a thrust chamber extension section is arranged between the thrust chamber and a stamping combustion chamber, and the thrust chamber extension section directly faces a high-heat-load environment; and heat back-invasion between the stamping combustion chamber and the thrust chamber is effectively reduced, and the wall surface temperature of the thrust chamber is reduced. The extension section cooling channel is arranged on the peripheral wall of the extension section of the thrust chamber, an outlet of the fuel electric pump is connected with the extension section cooling channel, fuel is adopted as a cooling agent to cool the extension section of the thrust chamber, and the heat insulation protection performance of the extension section of the thrust chamber is met.

Description

Technical Field

[0001] This invention relates to a high heat load pre-cooling system for hydrogen peroxide thrust chambers, specifically to a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system and its starting method. Background Technology

[0002] In recent years, with the rapid development of hypersonic vehicles and reusable space transportation systems, rocket-based combined cycle (RBCC) engines have become a frontier and focus of aerospace propulsion technology research due to their ability to efficiently cover a wide airspace from the ground to the outer atmosphere. RBCC engines cleverly combine the high thrust-to-weight ratio of rocket engines with the high specific impulse characteristics of ramjet engines, achieving optimal matching of power performance through mode switching. Depending on orbital change requirements, the rocket thrust chamber (hereinafter referred to as the thrust chamber) on the RBCC engine may need to be started multiple times to increase thrust and achieve large-scale maneuvering orbit changes. This means that RBCC engines have application scenarios involving long-term ramjet mode operation and intermittent operation with multiple rocket starts.

[0003] Hydrogen peroxide (H2O2) propellant, with its high density specific impulse, room temperature storage, and green and non-toxic properties, is considered an ideal choice for achieving rapid response and reusability in RBCC (Regenerative Brake-Computer Combustion) power systems. However, in the structural layout of RBCC engines, the thrust chamber is located above the ramjet combustion chamber. The thermal load on the thrust chamber mainly includes the convective radiation heating of the 3000K high-temperature gas inside the thrust chamber during operation, and the high-temperature heat conduction from the mounting wall of the thrust chamber nozzle outlet caused by the operation of the ramjet combustion chamber. The outer wall temperature of the main cooling ramjet combustion chamber can reach up to 800℃. In the design of RBCC engines, active cooling schemes are generally used to achieve reliable thermal protection of the thrust chamber structure under long-term operating conditions. However, the cold source within the engine system is extremely limited; without introducing other media, the fuel and oxidizer carried by the engine are the only available cold source. Using hydrogen peroxide as a coolant to regenerate the cooling jacket of the thrust chamber body is the optimal technical path for achieving thermal management.

[0004] Hydrogen peroxide has poor thermal stability, with a thermal explosion temperature of only 150°C. When the thrust chamber needs to be restarted after operating under high heat load conditions in the ram mode, the temperature of the thrust chamber cooling channel wall may have exceeded 500°C, which is far higher than the propellant thermal explosion threshold. Under these conditions, if room temperature hydrogen peroxide is directly introduced into the thrust chamber cooling channel, a violent thermal decomposition reaction will occur when the working fluid comes into contact with the wall. This process will instantly generate a large amount of high-temperature steam and oxygen, which may lead to a thrust chamber explosion in severe cases. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problem in the prior art where, under high heat load conditions, the thrust chamber structure temperature cannot meet the safe use conditions of hydrogen peroxide, leading to a thermal decomposition reaction when hydrogen peroxide comes into contact with the thrust chamber wall during the process of introducing room temperature hydrogen peroxide into the thrust chamber cooling channel, generating a large amount of high-temperature steam and oxygen, which may lead to a thrust chamber explosion in severe cases. The invention provides a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system and its starting method.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: A hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite precooling system is characterized by comprising a thrust chamber and a thrust chamber extension. The thrust chamber includes a thrust chamber head and a thrust chamber body. The thrust chamber head is connected to external fuel via a main fuel valve. A gas source is also connected to the pipeline between the main fuel valve and the thrust chamber head via a fuel purging valve. The outer peripheral wall of the thrust chamber body has a thrust chamber cooling channel. The outlet of the thrust chamber cooling channel is connected to the oxidizer chamber of the thrust chamber head. The inlet of the thrust chamber cooling channel is connected to an external hydrogen peroxide source via an oxidizer main valve. A gas source is also connected to the pipeline between the oxidizer main valve and the inlet of the thrust chamber cooling channel via an oxidizer purging valve. One end of the thrust chamber extension is connected to the exhaust port of the thrust chamber body, and the other end is used to connect to the second inlet of the ramjet combustion chamber of the RBCC engine. The outer peripheral wall of the thrust chamber extension is provided with an extension cooling channel. The inlet of the extended cooling passage is connected to the outlet of the fuel electric pump of the RBCC engine, and the outlet of the extended cooling passage is connected to the first inlet of the ramjet combustion chamber.

[0007] Furthermore, the gas source is a nitrogen source, and the temperature of the nitrogen source is 0~30°C. .

[0008] Furthermore, the hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite precooling system also includes a control device; A temperature sensor is installed at the inlet of the thrust chamber cooling channel, and the temperature sensor is electrically connected to the control device. The control device is also electrically connected to the oxidant purging valve and is used to control the opening and closing of the oxidant purging valve based on the temperature signal collected by the temperature sensor.

[0009] Meanwhile, the present invention also provides a starting method for the hydrogen peroxide thrust chamber of an RBCC engine with a high heat load composite precooling system, which is characterized by including the following steps: Step 1: Construct the hydrogen peroxide thrust chamber of the RBCC engine with the high heat load composite precooling system described above. Connect the other end of the thrust chamber extension to the second inlet of the ramjet combustion chamber of the RBCC engine. Connect the inlet of the cooling channel of the extension to the outlet of the fuel electric pump of the RBCC engine. Connect the outlet of the cooling channel of the extension to the first inlet of the ramjet combustion chamber. Step 2: Turn on the electric fuel pump and feed fuel through the outlet of the electric fuel pump into the extension cooling channel to actively cool the thrust chamber extension, and then feed the fuel into the ramjet combustion chamber through the first inlet of the ramjet combustion chamber. Step 3: Open the oxidizer purge valve to connect the gas source with the thrust chamber cooling channel. The gas from the gas source enters the thrust chamber cooling channel to cool the thrust chamber body. After heat exchange, the gas passes through the oxidizer chamber at the thrust chamber head and enters the inner cavity of the thrust chamber body to cool the inner wall of the thrust chamber body. The purge cooling process is completed within the preset time. Then, close the oxidizer purge valve to shut off the gas source and the thrust chamber cooling passage; Step 4: Open the fuel purging valve and blow gas into the thrust chamber head through the gas source. The gas pressure is [insert pressure here]. ; Step 5: Preset time for opening the fuel purging valve Then, the oxidizer main valve is opened, connecting the hydrogen peroxide to the thrust chamber cooling channel. The hydrogen peroxide from the hydrogen peroxide source enters the oxidizer chamber at the head of the thrust chamber after passing through the cooling channel. The hydrogen peroxide decomposition combustion gas, after catalytic decomposition, is injected into the ramjet combustion chamber after passing through the thrust chamber body. The thrust chamber starts in single-component operating mode, at which time the chamber pressure is [value missing]. ,and ; Step 6: After the thrust chamber operates in a single-component mode, open the main fuel valve and close the fuel purge valve. The fuel passes through the thrust chamber head and enters the inner cavity of the thrust chamber body to mix and burn with the hydrogen peroxide decomposition gas. The thrust chamber switches to a dual-component mode, completing the start-up of the hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite pre-cooling system.

[0010] Furthermore, in step 3, the pre-set time for blowing off cooling is... Related to the inlet temperature T of the thrust chamber cooling channel, if Continue blowing away the cooling agent; if If the oxidizer purge valve is closed, the gas source and the thrust chamber cooling channel will be shut off.

[0011] Furthermore, in step 5, a preset time is set. It takes 3-5 seconds.

[0012] The beneficial effects of this invention are: 1. This invention discloses a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system. By integrating a thrust chamber extension section between the thrust chamber and the ramjet combustion chamber, the extension section directly faces the high heat load environment, effectively reducing heat backflow between the ramjet combustion chamber and the thrust chamber, and lowering the wall temperature of the thrust chamber. A cooling channel is provided on the outer peripheral wall of the thrust chamber extension section, and the outlet of the fuel electric pump is connected to this cooling channel. Fuel is used as a coolant to cool the thrust chamber extension section. The high decomposition temperature of the fuel ensures safe cooling of the thrust chamber extension section and satisfies the thermal insulation protection performance of the thrust chamber extension section for the thrust chamber body.

[0013] 2. The present invention provides a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system. The inlet of the thrust chamber cooling channel is connected to a gas source through an oxidant purging valve. Under high heat load conditions, before hydrogen peroxide is introduced into the thrust chamber cooling channel, nitrogen gas is first used to purge and cool the inner cavity of the thrust chamber cooling channel and the thrust chamber body to ensure that the temperature of the thrust chamber cooling channel wall drops below a safe temperature. Then, hydrogen peroxide is controlled to enter the thrust chamber cooling channel to ensure safe and reliable start-up of the thrust chamber.

[0014] 3. The present invention provides a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system. It uses nitrogen as the cooling gas source. Nitrogen is an inert gas that will not corrode the product or react chemically with the propellant, thus achieving safe and reliable cooling of the thrust chamber.

[0015] 4. The present invention provides a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite pre-cooling system. By installing a temperature sensor at the inlet of the thrust chamber cooling channel, the cooling effect of the thrust chamber can be directly monitored, and it can be determined when hydrogen peroxide can be introduced into the thrust chamber cooling channel, thereby improving safety.

[0016] 5. This invention provides a high-heat-load start-up method for the hydrogen peroxide thrust chamber of an RBCC engine. First, the fuel electric pump outlet is turned on, and fuel is introduced into the extension section cooling channel to actively cool the thrust chamber extension section. As the fuel flows within the extension section cooling channel, radiative and convective heat flow from the high-temperature combustion gases in the ramjet combustion chamber, as well as heat conduction from the ramjet combustion chamber wall structure, is dissipated through convective heat exchange, thereby establishing an effective low-temperature barrier between the thrust chamber and the ramjet combustion chamber. This significantly reduces the thermal load on the thrust chamber, alleviating the preheating to extreme temperatures at the source and creating favorable conditions for subsequent safe start-up. Then, open the oxidizer purge valve to connect the gas source with the thrust chamber cooling channel, purge and cool the thrust chamber cooling channel, and perform secondary cooling of the thrust chamber until the inlet temperature of the thrust chamber cooling channel drops to within a safe temperature. At this time, open the oxidizer main valve and hydrogen peroxide is introduced. The thrust chamber starts in single-component mode. After stable operation, close the fuel purge valve and open the fuel main valve. The thrust chamber switches to dual-component working mode. This starting method can ensure that hydrogen peroxide medium safely enters the thrust chamber cooling channel and ensures the safe and reliable operation of the engine.

[0017] 6. The present invention provides a high-heat-load start-up method for the hydrogen peroxide thrust chamber of an RBCC engine. By controlling the purging and cooling time through the inlet temperature of the thrust chamber cooling channel, it is possible to ensure that the thrust chamber temperature has met the reliable start-up conditions through actual temperature measurement. If a fixed purging time is used, it is impossible to determine whether the thrust chamber temperature has dropped to a safe range.

[0018] 7. The present invention provides a high-heat-load starting method for the hydrogen peroxide thrust chamber of an RBCC engine. Before opening the oxidizer main valve, the fuel purging valve is opened first, and protective gas is introduced into the thrust chamber head through a gas source. The gas pressure is greater than the single-unit operating chamber pressure of the thrust chamber, which effectively prevents the oxygen-rich gas generated by the catalytic decomposition of hydrogen peroxide from backflowing into the fuel chamber of the thrust chamber head after the thrust chamber starts. This would prevent the fuel from contacting and deflagrizing with the hydrogen peroxide oxygen-rich gas in the thrust chamber head after the subsequent fuel valve is opened, thus causing an explosion of the thrust chamber. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of an embodiment of the hydrogen peroxide thrust chamber of an RBCC engine with a high heat load composite precooling system according to the present invention.

[0020] The attached figures are labeled as follows: 1. Thrust chamber; 101. Thrust chamber head; 102. Thrust chamber body; 2. Rammed combustion chamber; 3. Fuel electric pump; 4. Fuel main valve; 5. Thrust chamber extension; 6. Oxidizer main valve; 7. Oxidizer purge valve; 8. Fuel purge valve. Detailed Implementation

[0021] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings and embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] like Figure 1 As shown in the figure, an embodiment of the present invention provides a hydrogen peroxide thrust chamber for an RBCC engine with a high heat load composite precooling system, comprising a thrust chamber 1, a thrust chamber extension section 5, and a control device; the RBCC engine includes a ramjet combustion chamber 2 and a fuel electric pump 3; The thrust chamber 1 includes a thrust chamber head 101 and a thrust chamber body 102. The thrust chamber head 101 is connected to external fuel via a main fuel valve 4. A gas source is also connected to the pipeline between the main fuel valve 4 and the thrust chamber head 101 via a fuel purging valve 8. The outer peripheral wall of the thrust chamber body 102 has a thrust chamber cooling channel. The outlet of the thrust chamber cooling channel connects to the oxidizer chamber of the thrust chamber head 101. The inlet of the thrust chamber cooling channel is connected to an external hydrogen peroxide source via an oxidizer main valve 6. A gas source is also connected to the pipeline between the oxidizer main valve 6 and the inlet of the thrust chamber cooling channel via an oxidizer purging valve 7. The gas source is a nitrogen source, and the temperature of the nitrogen source is 0~30℃. In this embodiment, kerosene is used as the fuel.

[0023] One end of the thrust chamber extension 5 is connected to the exhaust port of the thrust chamber body 102, and the other end is connected to the second inlet of the ramjet combustion chamber 2. The outer peripheral wall of the thrust chamber extension 5 is provided with an extension cooling channel. The fuel electric pump 3 has an inlet and an outlet. The inlet is connected to external fuel, and the outlet is connected to the inlet of the extension cooling channel. The outlet of the extension cooling channel is connected to the first inlet of the ramjet combustion chamber 2. By setting a thrust chamber extension 5 between the thrust chamber 1 and the ramjet combustion chamber 2, the thrust chamber extension 5 is integrated into the ramjet combustion chamber 2, directly facing the high heat load environment, effectively reducing heat backflow between the ramjet combustion chamber 2 and the thrust chamber 1, and lowering the wall temperature of the thrust chamber 1. An extension cooling channel is set on the outer peripheral wall of the thrust chamber extension 5, and the outlet of the fuel electric pump 3 is connected to the extension cooling channel. Fuel is used as a coolant to cool the thrust chamber extension 5. The high decomposition temperature of the fuel ensures safe cooling of the thrust chamber extension 5 and meets the thermal insulation protection performance requirements of the thrust chamber extension 5 for the thrust chamber body 102.

[0024] A temperature sensor is installed at the inlet of the thrust chamber cooling channel. The temperature sensor is electrically connected to the control device. The control device is also electrically connected to the oxidant purge valve 7, and is used to control the opening and closing of the oxidant purge valve 7 according to the temperature signal collected by the temperature sensor.

[0025] Meanwhile, the present invention also provides a starting method for the hydrogen peroxide thrust chamber of an RBCC engine with a high heat load composite precooling system, comprising the following steps: Step 1: Construct the hydrogen peroxide thrust chamber of the RBCC engine with the high heat load composite precooling system, connect the other end of the thrust chamber extension 5 to the second inlet of the ramjet combustion chamber 2 of the RBCC engine, connect the inlet of the extension cooling channel to the outlet of the fuel electric pump 3 of the RBCC engine, and connect the outlet of the extension cooling channel to the first inlet of the ramjet combustion chamber 2. Step 2: Turn on the fuel electric pump 3 and feed fuel through the outlet of the fuel electric pump 3 into the extension cooling channel to actively cool the thrust chamber extension 5, and then feed the fuel into the ramjet combustion chamber 2 through the first inlet of the ramjet combustion chamber 2. Step 3: Open the oxidizer purge valve 7 to connect the gas source with the thrust chamber cooling channel. The gas from the gas source enters the thrust chamber cooling channel to cool the thrust chamber body. After heat exchange, the gas passes through the oxidizer chamber in the thrust chamber head 101 and enters the inner cavity of the thrust chamber body 102 to cool the inner wall of the thrust chamber body, thus purging the pre-set cooling system. Then, close the oxidizer purge valve 7 to shut off the gas source and the thrust chamber cooling passage; Blow-out cooling preset Related to the inlet temperature T of the thrust chamber cooling channel, if Continue blowing away the cooling agent; if If the control device closes the oxidizer purge valve 7, it will shut down the gas source and the thrust chamber cooling channel.

[0026] Step 4: Open fuel purging valve 8 and blow gas into the thrust chamber head through the gas source. The gas pressure is [insert pressure here]. ; Step 5: Fuel purge valve 8 opens for a preset time. Then, the oxidizer main valve 6 is opened, connecting the hydrogen peroxide to the thrust chamber cooling channel. The hydrogen peroxide from the hydrogen peroxide source enters the oxidizer chamber of the thrust chamber head 101 after passing through the thrust chamber cooling channel. The hydrogen peroxide decomposition gas after catalytic decomposition passes through the thrust chamber body 102 and is injected into the ramjet combustion chamber 2. The thrust chamber 1 starts in single-component operating mode. At this time, the chamber pressure of the thrust chamber 1 is [value missing]. ,and Fuel purge valve 8 opening preset time The duration is 3-5 seconds; this embodiment uses... .

[0027] Step 6: After the single-component working mode of thrust chamber 1 is stable, open the main fuel valve 4 and close the fuel purge valve 8. The fuel enters the inner cavity of the thrust chamber body 102 after passing through the thrust chamber head 101 and mixes with the hydrogen peroxide decomposition gas for combustion. Thrust chamber 1 switches to the dual-component working mode, completing the start-up of the hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite pre-cooling system.

[0028] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present invention should be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A hydrogen peroxide thrust chamber for an RBCC engine with a high-heat-load composite pre-cooling system, characterized in that: It includes the thrust chamber (1) and the thrust chamber extension (5); The thrust chamber (1) includes a thrust chamber head (101) and a thrust chamber body (102). The thrust chamber head (101) is connected to external fuel via a fuel main valve (4). A gas source is also connected to the pipeline between the fuel main valve (4) and the thrust chamber head (101) via a fuel purge valve (8). The outer peripheral wall of the thrust chamber body (102) has a thrust chamber cooling channel. The outlet of the thrust chamber cooling channel is connected to the oxidant chamber of the thrust chamber head (101), and the inlet is connected to a hydrogen peroxide source via an oxidant main valve (6). A gas source is also connected to the pipeline between the oxidant main valve (6) and the inlet of the thrust chamber cooling channel via an oxidant purge valve (7). One end of the thrust chamber extension (5) is connected to the exhaust port of the thrust chamber body (102), and the other end is used to connect to the second inlet of the ramjet combustion chamber (2) of the RBCC engine. The outer peripheral wall of the thrust chamber extension (5) is provided with an extension section cooling channel. The inlet of the extended cooling channel is connected to the outlet of the fuel electric pump (3) of the RBCC engine, and the outlet of the extended cooling channel is connected to the first inlet of the ramjet combustion chamber (2).

2. The hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite precooling system according to claim 1, characterized in that: The gas source is a nitrogen source, and the temperature of the nitrogen source is 0~30℃. .

3. The hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite precooling system according to claim 1, characterized in that: It also includes control devices; A temperature sensor is installed at the inlet of the thrust chamber cooling channel, and the temperature sensor is electrically connected to the control device. The control device is also electrically connected to the oxidant purge valve (7) and is used to control the opening and closing of the oxidant purge valve (7) according to the temperature signal collected by the temperature sensor.

4. A starting method for the hydrogen peroxide thrust chamber of an RBCC engine with a high heat load composite precooling system, characterized in that, Includes the following steps: Step 1: Construct the hydrogen peroxide thrust chamber of the RBCC engine with a high heat load composite precooling system as described in claim 1, connect the other end of the thrust chamber extension section (5) to the second inlet of the ramjet combustion chamber (2) of the RBCC engine, connect the inlet of the extension section cooling channel to the outlet of the fuel electric pump (3) of the RBCC engine, and connect the outlet of the extension section cooling channel to the first inlet of the ramjet combustion chamber (2). Step 2: Turn on the fuel electric pump (3) and put one stream of fuel into the extension cooling channel through the outlet of the fuel electric pump (3) to actively cool the thrust chamber extension (5), and then put it into the ramjet combustion chamber (2) through the first inlet of the ramjet combustion chamber (2). Step 3: Open the oxidizer purge valve (7) to connect the gas source with the thrust chamber cooling channel, allowing the gas from the gas source to enter the thrust chamber cooling channel to cool the thrust chamber body. After heat exchange, the gas passes through the oxidizer chamber of the thrust chamber head (101) and enters the inner cavity of the thrust chamber body (102) to cool the inner wall of the thrust chamber body. The purge cooling is performed for a preset time. Then, close the oxidizer purge valve (7) to shut off the gas source and the thrust chamber cooling passage; Step 4: Open the fuel purging valve (8) and blow gas into the thrust chamber head through the gas source. The gas pressure is [insert pressure here]. ; Step 5: Fuel purge valve (8) opens for a preset time. Then, the oxidizer main valve (6) is opened to connect the hydrogen peroxide with the thrust chamber cooling channel. The hydrogen peroxide from the hydrogen peroxide source enters the oxidizer chamber of the thrust chamber head (101) after passing through the thrust chamber cooling channel. The hydrogen peroxide decomposition gas after catalytic decomposition of hydrogen peroxide passes through the thrust chamber body (102) and is injected into the ramjet combustion chamber (2). The thrust chamber (1) starts in single-component working mode. At this time, the chamber pressure of the thrust chamber (1) is 1. ,and ; Step 6: After the single-component working mode of the thrust chamber (1) is stable, open the fuel main valve (4) and close the fuel purge valve (8). The fuel enters the inner cavity of the thrust chamber body (102) after passing through the thrust chamber head (101) and mixes with the hydrogen peroxide decomposition gas for combustion. The thrust chamber (1) switches to the dual-component working mode, and the hydrogen peroxide thrust chamber of the RBCC engine with high heat load composite pre-cooling system is started.

5. The high-heat-load start-up method for the hydrogen peroxide thrust chamber of an RBCC engine according to claim 4, characterized in that, In step 3, the pre-set cooling time for blow-off is... Related to the inlet temperature T of the thrust chamber cooling channel, if Continue blowing to cool; if Then the oxidizer purge valve (7) is closed, so that the gas source and the thrust chamber cooling channel are closed.

6. The high-heat-load start-up method for the hydrogen peroxide thrust chamber of an RBCC engine according to claim 4, characterized in that, In step 5, the preset time is... It takes 3-5 seconds.

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