Ignition matching control system for full-flow staged combustion cycle engine

Abstract

The present invention relates to an ignition matching control system for a full-flow staged combustion cycle engine, and belongs to the field of engine design. An oxidizer pump and a fuel pump are symmetrically provided on two sides of a thrust chamber; an oxidizer pump turbine is connected to the oxidizer pump; the oxidizer pump is separately communicated with a liquid oxygen main valve and a liquid oxygen auxiliary valve via pipes; the liquid oxygen main valve is communicated with an oxidizer-rich gas generator; the liquid oxygen auxiliary valve is communicated with a fuel-rich gas generator; the oxidizer-rich gas generator is communicated with the thrust chamber via the oxidizer pump turbine; a fuel pump turbine is communicated with the fuel pump; the fuel pump is divided into two paths via a fuel main valve, wherein one path is communicated with the thrust chamber, and the other path is communicated with a fuel auxiliary valve; the fuel auxiliary valve is communicated with the oxidizer-rich gas generator; two output ends of the thrust chamber converge to be communicated with a fuel shut-off valve; the fuel shut-off valve is communicated with the fuel-rich gas generator; the fuel-rich gas generator is communicated with the thrust chamber via the fuel pump turbine. The present invention achieves accelerated filling of the fuel system during start-up, thereby solving problems such as the tendency of the fuel-rich gas generator to undergo high-temperature combustion and the lag in the ramp-up rate of the fuel system relative to that of the oxidizer system during start-up.

Description

Full-flow afterburning cycle engine ignition matching control system

[0001] This application claims priority to Chinese Patent Application No. 2024118214102, filed on December 11, 2024, entitled "Ignition Matching Control System for Full-Flow Afterburning Cycle Engine", the entire contents of which are incorporated herein by reference. Technical Field

[0002] This invention belongs to the field of engine design and relates to an ignition matching control system for a full-flow afterburning cycle engine. Background Technology

[0003] The full-flow afterburning cycle engine comprises an oxygen-enriched system consisting of an oxygen-enriched gas generator and an oxidizer main turbopump, a fuel-enriched system consisting of a fuel-enriched gas generator and a fuel main turbopump assembly, and a thrust chamber, among other components. Liquid oxygen flows directly into the oxygen-enriched generator and the fuel-enriched system after passing through the pump. A small portion of the fuel from the fuel pump outlet flows directly into the oxygen-enriched generator and is burned in the liquid oxygen, while the majority must flow through the large-volume, high-flow-resistance thrust chamber cooling jacket before entering the fuel-enriched generator and being burned in the liquid oxygen. Furthermore, the cryogenic fuel undergoes significant vaporization within the large-volume, high-flow-resistance cooling jacket, resulting in a slow fuel filling process in the fuel-enriched generator. This slow fuel supply to the fuel-enriched generator can lead to deviations in the air-fuel mixture ratio, high combustion temperatures, and generator ablation. Additionally, the low gas flow rate in the fuel-enriched generator results in a slower work-capacity increase compared to the oxygen-enriched system, potentially causing the oxygen-enriched system to accelerate faster than the fuel-enriched system, leading to start-up failures. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose an ignition matching control system for a full-flow afterburning cycle engine. This system accelerates the filling of the fuel system during the starting process, solves problems such as the easy high-temperature combustion of the rich fuel generator and the fuel system ramp-up rate lagging behind the oxygen system during the starting process, and ensures normal engine starting.

[0005] The solution of the present invention is:

[0006] The full-flow afterburning cycle engine ignition matching control system includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen secondary valve, a fuel secondary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, and a thrust chamber.

[0007] The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. A fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which merge and connect to the input end of the fuel shut-off valve. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine. A helium-driven gas source interface is located on the fuel turbine.

[0008] In the aforementioned full-flow afterburning cycle engine ignition matching control system, the working process of the control system is as follows:

[0009] At time T0, external liquid oxygen enters through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; fuel enters through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve.

[0010] At time T1, the helium drive gas source interface on the fuel pump turbine is opened, and external high-pressure helium enters, causing the fuel pump turbine to start rotating and reach stability, and the fuel pump generates positive head.

[0011] At time T2, the main fuel valve is opened; driven by the positive head of the fuel pump, the fuel is split and flows; one stream of fuel enters the thrust chamber cooling jacket to pre-cool the thrust chamber cooling jacket, and then flows out of the cooling jacket and flows to the fuel shut-off valve inlet; the high-pressure helium gas makes the pipeline pressure high, effectively reducing fuel boiling; the other stream of fuel flows to the fuel auxiliary valve inlet.

[0012] At time T3, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened; liquid oxygen and fuel flow into the oxygen-enriched generator, ignite to produce oxygen-enriched gas, and then drive the oxygen pump turbine; after the oxygen-enriched gas drives the turbine pump, it flows into the thrust chamber.

[0013] Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator; liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel pump turbine; after the rich gas drives the fuel pump turbine, it flows into the thrust chamber.

[0014] Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

[0015] In the aforementioned full-flow afterburning cycle engine ignition matching control system, at time T1, high-pressure helium gas is introduced to force the start of the fuel pump turbine, ensuring a stable flow supply and facilitating the stable filling of the large-capacity thrust chamber.

[0016] In the aforementioned full-flow afterburning cycle engine ignition matching control system, at time T2, the main fuel valve is opened in advance to accelerate the filling of the large thrust chamber, which is beneficial for the rapid filling of the large thrust chamber.

[0017] The aforementioned full-flow afterburning cycle engine ignition matching control system achieves flexible and precise control through the dynamic adjustment and control of four valves: liquid oxygen main valve, fuel auxiliary valve, fuel main valve, and liquid oxygen auxiliary valve. It also ensures that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and climbed, ensuring that no destructive high temperatures occur in the generator and thrust chamber.

[0018] The full-flow afterburning cycle engine ignition matching control system includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen secondary valve, a fuel secondary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, a pre-cooled exhaust valve, and a thrust chamber.

[0019] The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. The fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which converge and connect to the input end of the fuel shut-off valve and the pre-cooling discharge valve, respectively. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine.

[0020] In the aforementioned full-flow afterburning cycle engine ignition matching control system, the working process of the control system is as follows:

[0021] At time T0, external liquid oxygen flows in through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; external fuel flows in through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve.

[0022] At time T1, the main fuel valve is opened, and the fuel is split into two streams. One stream of fuel enters the thrust chamber cooling jacket to pre-cool the jacket, and then flows out of the cooling jacket and is discharged to the outside through the pre-cooling discharge valve, thus completing the low-temperature pre-cooling of the thrust chamber cooling jacket. The other stream of fuel flows to the inlet of the auxiliary fuel valve.

[0023] At time T2, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened, and liquid oxygen and fuel flow into the oxygen-enriched generator, igniting to produce oxygen-enriched gas, which then drives the oxygen turbopump; after the oxygen-enriched gas drives the turbopump, it flows into the thrust chamber.

[0024] Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator, and liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel turbopump; after the rich gas drives the turbopump, it flows into the thrust chamber.

[0025] Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

[0026] In the aforementioned full-flow afterburning cycle engine ignition matching control system, at time T1, the main fuel valve is opened in advance to accelerate the filling of the large thrust chamber, which is beneficial for the rapid filling of the large thrust chamber.

[0027] The aforementioned full-flow afterburning cycle engine ignition matching control system achieves flexible and precise control through the dynamic adjustment and control of four valves: liquid oxygen main valve, fuel auxiliary valve, fuel main valve, and liquid oxygen auxiliary valve. It also ensures that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and climbed, ensuring that no destructive high temperatures occur in the generator and thrust chamber.

[0028] In the above-mentioned full-flow afterburning cycle engine ignition matching control system, the times T0, T1, T2, and T3 are arranged in sequence, and the time interval between two adjacent times is set according to requirements.

[0029] The advantages of this invention compared to the prior art are:

[0030] (1) The present invention features an asymmetric drive method where the fuel-rich system turbopump is driven by high-pressure gas and the oxygen-rich system is not driven; high-pressure filling ensures a stable supply of cryogenic fuel in the thrust chamber, effectively reducing the degree of propellant boiling and reducing propellant loss;

[0031] (2) The present invention features a dual-valve design with adjustable fuel main valve and fuel shut-off valve at the outlet and inlet of the cooling jacket, allowing for advance filling of the thrust chamber cooling jacket;

[0032] (3) The four valves of the oxygen-enriched system and the fuel-enriched system of the present invention are dynamically adjusted to ensure the flow matching of the oxygen-enriched system and the fuel-enriched system during the start-up process;

[0033] (4) The present invention sets a pre-cooling discharge valve before the fuel shut-off valve to pre-cool the thrust chamber cooling jacket in advance, so that the low temperature fuel can complete the pre-cooling of the thrust chamber in advance, remove the boiling propellant, and ensure a stable flow supply. Attached Figure Description

[0034] Figure 1 is a schematic diagram of the first form of the full-flow afterburning cycle engine ignition matching control system of the present invention;

[0035] Figure 2 is a schematic diagram of the second form of the full-flow afterburning cycle engine ignition matching control system of the present invention; Detailed Implementation

[0036] The present invention will be further described below with reference to the embodiments.

[0037] This invention provides an ignition matching control system for a full-flow afterburning cycle engine, which accelerates the filling of the fuel system during the starting process, solves problems such as the easy high-temperature combustion of the rich fuel generator and the fuel system ramp-up rate lagging behind the oxygen system during the starting process, and ensures normal engine starting.

[0038] This invention designs two types of ignition matching control systems for full-flow afterburning cycle engines, as shown in Figure 1. The first type of ignition matching control system for full-flow afterburning cycle engines includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen secondary valve, a fuel secondary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, and a thrust chamber. The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. A fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which merge and connect to the input end of the fuel shut-off valve. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine. A helium-driven gas source interface is located on the fuel turbine.

[0039] The working process of this control system is as follows:

[0040] At time T0, external liquid oxygen enters through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; fuel enters through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve.

[0041] At time T1, the helium drive gas source interface on the fuel pump turbine is opened, and external high-pressure helium enters, causing the fuel pump turbine to start rotating and reach stability, and the fuel pump to generate positive head. At time T1, the entry of high-pressure helium enables forced start of the fuel pump turbine, ensuring stable flow supply and facilitating stable filling of the large-capacity thrust chamber.

[0042] At time T2, the main fuel valve is opened; driven by the positive head of the fuel pump, the fuel is split and flows; one stream of fuel enters the thrust chamber cooling jacket to pre-cool the jacket, and then flows out of the cooling jacket to the fuel shut-off valve inlet; the high-pressure helium gas makes the pipeline pressure high, effectively reducing fuel boiling; the other stream of fuel flows to the fuel auxiliary valve inlet; at time T2, by opening the main fuel valve in advance, the filling of the large thrust chamber cavity is accelerated, which is beneficial to the rapid filling of the large thrust chamber cavity.

[0043] At time T3, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened; liquid oxygen and fuel flow into the oxygen-enriched generator, ignite to produce oxygen-enriched gas, and then drive the oxygen pump turbine; the oxygen-enriched gas drives the turbine pump and then flows into the thrust chamber.

[0044] Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator; liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel pump turbine; after the rich gas drives the fuel pump turbine, it flows into the thrust chamber.

[0045] Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

[0046] By dynamically adjusting and controlling the four valves—the main liquid oxygen valve, the auxiliary fuel valve, the main fuel valve, and the auxiliary liquid oxygen valve—flexible and precise control is achieved, ensuring that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and that no destructive high temperatures occur inside the generator or the thrust chamber.

[0047] The beneficial effects of the first full-flow afterburning cycle engine ignition matching control system are:

[0048] (1) The asymmetric drive mode of high-pressure gas drive for the fuel-rich system turbopump and no drive for the oxygen-rich system; high-pressure filling ensures a stable supply of cryogenic fuel in the thrust chamber, effectively reducing the degree of propellant boiling and reducing propellant loss.

[0049] (2) The cooling jacket outlet and inlet are designed with adjustable fuel main valve and fuel shut-off valve, and the thrust chamber cooling jacket is filled in advance.

[0050] (3) Dynamic adjustment of the four valves of the oxygen-enriched system and the fuel-enriched system ensures the flow matching of the oxygen-enriched system and the fuel-enriched system during the start-up process.

[0051] As shown in Figure 2, the second type of full-flow afterburning cycle engine ignition matching control system includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen secondary valve, a fuel secondary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, a pre-cooling exhaust valve, and a thrust chamber. The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. The fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which converge and connect to the input end of the fuel shut-off valve and the pre-cooling discharge valve, respectively. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine.

[0052] The working process of this control system is as follows:

[0053] At time T0, external liquid oxygen flows in through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; external fuel flows in through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve.

[0054] At time T1, the main fuel valve is opened, and the fuel is diverted. One stream of fuel enters the thrust chamber cooling jacket to pre-cool it, and then flows out of the cooling jacket and is discharged to the outside through the pre-cooling discharge valve, thus completing the low-temperature pre-cooling of the thrust chamber cooling jacket. The other stream of fuel flows to the inlet of the auxiliary fuel valve. At time T1, by opening the main fuel valve in advance, the filling of the large thrust chamber cavity is accelerated, which is beneficial to the rapid filling of the large thrust chamber cavity.

[0055] At time T2, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened, and liquid oxygen and fuel flow into the oxygen-enriched generator, igniting to produce oxygen-enriched gas, which then drives the oxygen turbopump; after the oxygen-enriched gas drives the turbopump, it flows into the thrust chamber.

[0056] Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator, and liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel turbopump; after the rich gas drives the turbopump, it flows into the thrust chamber.

[0057] Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

[0058] By dynamically adjusting and controlling the four valves—the main liquid oxygen valve, the auxiliary fuel valve, the main fuel valve, and the auxiliary liquid oxygen valve—flexible and precise control is achieved, ensuring that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and that no destructive high temperatures occur inside the generator or the thrust chamber.

[0059] The two full-flow afterburning cycle engine ignition matching control systems are arranged in time sequence at times T0, T1, T2, and T3, and the time interval between two adjacent times is set according to requirements.

[0060] The beneficial effects of the second type of full-flow afterburning cycle engine ignition matching control system are:

[0061] (1) A pre-cooling discharge valve is installed before the fuel shut-off valve to pre-cool the thrust chamber cooling jacket in advance, so that the low-temperature fuel can be pre-cooled in advance, the boiling propellant can be removed, and the flow rate can be kept stable.

[0062] (2) The cooling jacket outlet and inlet are designed with adjustable fuel main valve and fuel shut-off valve, and the thrust chamber cooling jacket is filled in advance.

[0063] (3) Dynamic adjustment of the four valves of the oxygen-enriched system and the fuel-enriched system ensures the flow matching of the oxygen-enriched system and the fuel-enriched system during the start-up process.

[0064] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A full flow staged combustion cycle engine ignition match control system characterized by: Includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen auxiliary valve, a fuel auxiliary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, and a thrust chamber; The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. The fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which merge and connect to the input end of the fuel shut-off valve. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine. A helium-driven gas source interface is located on the fuel turbine.

2. The full-flow afterburning cycle engine ignition matching control system according to claim 1, characterized in that: The working process of the control system is as follows: At time T0, external liquid oxygen enters through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; fuel enters through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve. At time T1, the helium drive gas source interface on the fuel pump turbine is opened, and external high-pressure helium enters, causing the fuel pump turbine to start rotating and reach stability, and the fuel pump generates positive head. At time T2, the main fuel valve is opened; driven by the positive head of the fuel pump, the fuel is diverted and flows. One fuel stream enters the thrust chamber cooling jacket to pre-cool the jacket, and then flows out of the cooling jacket to the fuel shut-off valve inlet; the high-pressure helium gas keeps the pipeline pressure high, effectively reducing fuel boiling; the other fuel stream flows to the fuel auxiliary valve inlet. At time T3, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened; liquid oxygen and fuel flow into the oxygen-enriched generator, ignite to produce oxygen-enriched gas, and then drive the oxygen pump turbine; after the oxygen-enriched gas drives the turbine pump, it flows into the thrust chamber. Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator; liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel pump turbine; after the rich gas drives the fuel pump turbine, it flows into the thrust chamber. Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

3. The full-flow afterburning cycle engine ignition matching control system according to claim 2, characterized in that: At time T1, high-pressure helium gas is introduced to force the start of the fuel pump turbine, ensuring a stable flow supply and facilitating the stable filling of the large-capacity thrust chamber.

4. The full-flow afterburning cycle engine ignition matching control system according to claim 2, characterized in that: At time T2, the fuel main valve is opened in advance to accelerate the filling of the large-capacity thrust chamber, which is beneficial for the rapid filling of the large-capacity thrust chamber.

5. The full-flow afterburning cycle engine ignition matching control system according to claim 2, characterized in that: By dynamically adjusting and controlling four valves—the main liquid oxygen valve, the auxiliary fuel valve, the main fuel valve, and the auxiliary liquid oxygen valve—flexible and precise control is achieved, ensuring that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and that no destructive high temperatures occur inside the generator or the thrust chamber.

6. A full-flow afterburning cycle engine ignition matching control system, characterized in that: It includes an oxygen-enriched generator, an oxygen pump turbine, an oxygen pump, a liquid oxygen main valve, a liquid oxygen auxiliary valve, a fuel auxiliary valve, a fuel-enriched generator, a fuel pump turbine, a fuel pump, a fuel main valve, a fuel shut-off valve, a pre-cooling discharge valve, and a thrust chamber. The thrust chamber is vertically positioned. Oxygen pumps and fuel pumps are symmetrically arranged on either side of the thrust chamber. Each oxygen pump has an oxidizer inlet. An oxygen pump turbine is connected to the oxygen pump. The oxygen pump is connected via pipelines to the input ends of both the main liquid oxygen valve and the auxiliary liquid oxygen valve. The output end of the main liquid oxygen valve is connected to the input end of the oxygen-enriched generator. The output end of the auxiliary liquid oxygen valve is connected to the input end of the fuel-enriched generator. The output end of the oxygen-enriched generator connects to the thrust chamber via the oxygen pump turbine. Each fuel pump has a fuel inlet. The fuel pump turbine is connected to the fuel pump. The fuel pump outlet, after passing through the main fuel valve, splits into two paths: one path connects to the thrust chamber, and the other path connects to the input end of the auxiliary fuel valve. The output end of the auxiliary fuel valve connects to the input end of the oxygen-enriched generator. The thrust chamber has two output ends, which converge and connect to the input end of the fuel shut-off valve and the pre-cooling discharge valve, respectively. The output end of the fuel shut-off valve connects to the input end of the fuel-enriched generator. The output end of the fuel-enriched generator connects to the thrust chamber via the fuel pump turbine.

7. The full-flow afterburning cycle engine ignition matching control system according to claim 6, characterized in that: The working process of the control system is as follows: At time T0, external liquid oxygen flows in through the oxidant inlet of the oxygen pump and flows to the inlet of the liquid oxygen main valve; external fuel flows in through the fuel inlet of the fuel pump and flows to the inlet of the fuel main valve. At time T1, the main fuel valve is opened, and the fuel is split into two streams. One stream of fuel enters the thrust chamber cooling jacket to pre-cool the jacket, and then flows out of the cooling jacket and is discharged to the outside through the pre-cooling discharge valve, thus completing the low-temperature pre-cooling of the thrust chamber cooling jacket. The other stream of fuel flows to the inlet of the auxiliary fuel valve. At time T2, the main liquid oxygen valve and the auxiliary fuel valve connected to the oxygen-enriched generator are opened, and liquid oxygen and fuel flow into the oxygen-enriched generator, igniting to produce oxygen-enriched gas, which then drives the oxygen turbopump; after the oxygen-enriched gas drives the turbopump, it flows into the thrust chamber. Open the liquid oxygen auxiliary valve and fuel shut-off valve connected to the rich gas generator, and liquid oxygen and fuel flow into the rich gas generator, ignite to produce rich gas, and then drive the fuel turbopump; after the rich gas drives the turbopump, it flows into the thrust chamber. Oxygen-enriched gas and fuel-enriched gas burn in the thrust chamber to generate thrust.

8. The full-flow afterburning cycle engine ignition matching control system according to claim 7, characterized in that: At time T1, the fuel main valve is opened in advance to accelerate the filling of the large-capacity thrust chamber, which is beneficial for the rapid filling of the large-capacity thrust chamber.

9. The full-flow afterburning cycle engine ignition matching control system according to claim 7, characterized in that: By dynamically adjusting and controlling the four valves—the main liquid oxygen valve, the auxiliary fuel valve, the main fuel valve, and the auxiliary liquid oxygen valve—flexible and precise control is achieved, ensuring that the speed and pressure of the fuel-rich system and the oxygen-rich system are matched and that no destructive high temperatures occur inside the generator or the thrust chamber.

10. The full-flow afterburning cycle engine ignition matching control system according to claim 2 or 7, characterized in that: The times T0, T1, T2, and T3 are arranged in chronological order, and the time interval between two adjacent times is set according to requirements.

Images