CN113404621B - Solid-liquid mixed engine and method for Mars ascending aircraft - Google Patents

Abstract

The invention discloses a solid-liquid hybrid engine and method for a Mars ascending vehicle, belonging to the technical field of aerospace propulsion; it comprises a thrust chamber, an oxidant supply system and a thrust vector control system; the oxidant supply system comprises an oxidant storage tank, an extruded oxidant supply subsystem and The pumped expansion cycle oxidant supply subsystem; the squeezed oxidant supply subsystem inputs oxidant to the thrust chamber through extrusion, and the pumped expansion cycle oxidant supply subsystem inputs oxidant to the thrust chamber through the expansion cycle; the thrust vector The control system adjusts the flow rate of nitrous oxide entering the nozzle by opening and closing the control valves on different secondary flow pipelines, so as to realize the thrust vector control and the adjustment of the attitude of the ascender. The invention adopts paraffin fuel with superior ultra-low temperature mechanical properties and nitrous oxide with low freezing point and high saturated vapor pressure as propellant, which solves the problems that solid and liquid engines cannot adapt to extreme temperature difference on Mars and are difficult to store for a long time.

Description

Solid-liquid hybrid engine and method for Mars ascent vehicle

technical field

The invention belongs to the technical field of aerospace propulsion, and in particular relates to a solid-liquid hybrid engine and a method for a Mars ascending vehicle.

Background technique

Mars is the closest celestial body to Earth in the solar system and is the focus of current planetary exploration. Since the 1960s, humans have successfully launched a number of probes to the surface of Mars, but the scientific instruments carried by the probes can no longer meet the research needs of the current scientific community. Therefore, there is an urgent need to carry out the return of samples on the Martian surface. The sample return mission can be divided into the following steps: 1) launch probes to the surface of Mars to take samples; 2) Mars ascent vehicle sends samples to Mars orbit; 3) Mars orbiter carries samples back to Earth.

The Mars ascent vehicle is the key to the sample return mission, but the surface environment of Mars is harsh, with an average temperature of -63 °C, and the lowest temperature in winter can reach -133 °C. At present, the solid and liquid rocket motors that are widely used cannot adapt to this temperature condition. The glass transition temperature of the propellant used in the solid rocket motor is about -70 °C. It cannot work normally. In order to solve the problem of propellant fracture, the entire ascender needs to be insulated, which greatly increases the cost of the sample return mission; the propellant often used in liquid rocket engines has the characteristics of high freezing point and low saturated vapor pressure, and cannot be used for long periods of time. Time storage, nor can it be used as a Mars ascent vehicle engine.

The oxidant delivery mode of solid-liquid hybrid engine is divided into extrusion type and pump pressure type. In this state, the performance of the turbo pump will decrease. Based on this, the patent titled "Solid-Liquid Rocket Engine Electric Pump Delivery System" published by Yu Nanjia, Zhang Yuanjun and others of Beihang University. The patent application number for this invention is 201710618855.4. Control the flow, and ensure that the oxidant can be supplied to the combustion chamber at a stable pressure and flow by adjusting the speed of the pump and the flow control valve. In an article titled "Simulation and Optimization Design of Pump-Pressure Solid-Liquid Rocket Engine System" published in the Journal of Aerodynamics, Zhu Hao et al. of Beihang University proposed a high-temperature working fluid based on the catalytic decomposition of hydrogen peroxide. A pumped oxidant delivery system that drives a turbo pump, which is 20% smaller than a squeeze delivery system.

SUMMARY OF THE INVENTION

Technical problem to be solved:

In order to avoid the deficiencies of the prior art, the present invention proposes a solid-liquid hybrid engine for a Mars ascension vehicle, and the engine uses paraffin fuel/nitrous oxide as propellant. The glass transition temperature of paraffin fuel is extremely low, and it can maintain good mechanical properties at the ambient temperature of Mars. Nitrous oxide has the characteristics of high saturated vapor pressure and low freezing point, and can be stored for a long time at low temperature. At the same time, the theoretical specific impulse of the paraffin fuel/nitrous oxide solid-liquid hybrid engine can reach 3100N·s·kg ^-1 and the average thrust can reach 3400N, which can meet the mission requirements of the Mars ascent vehicle.

The technical scheme of the present invention is: a solid-liquid hybrid engine for a Mars ascending vehicle, comprising a thrust chamber; it is characterized in that: it further comprises an oxidant supply system and a thrust vector control system connected with the thrust chamber;

The oxidant supply system includes an oxidant storage tank 1, an extruded oxidant supply subsystem and a pumped expansion cycle oxidant supply subsystem; the oxidant storage tank 1 is arranged above the thrust chamber, and the extruded oxidant supply subsystem The oxidant is input into the thrust chamber by extrusion, and the pump expansion cycle oxidant supply subsystem inputs the oxidant into the thrust chamber through the expansion cycle;

The extruded oxidant supply subsystem includes a high-pressure helium storage tank 5, a pressurization pipeline 28 and an extrusion supply pipeline 29; a plurality of high-pressure helium storage tanks 5 are arranged on the periphery of the thrust chamber, and their outlets are connected to each other through pipes. connected with the oxidant storage tank 1 through the pressurization pipeline 28; the outlet of the pressurized pipeline 28 extends into the oxidant storage tank 1 and extends above the interior of the oxidant storage tank 1, for the high pressure helium gas The helium gas in the storage tank 5 is passed into the top of the oxidant storage tank 1 to give the oxidant downward pressure; the output port of the oxidant storage tank 1 is communicated with the thrust chamber through the extrusion supply pipeline 29, and the oxidant output by extrusion is connected to the thrust chamber. Input into the thrust chamber and burn with the paraffin fuel 11 in the combustion chamber;

The pumped expansion cycle oxidant supply subsystem includes a turbo pump 2, a first cooling cycle line 31, a turbo pump exhaust line 33, a first pump pressure supply line 34, a second cooling cycle line 41, a first Two pump pressure supply pipelines 35; the upper end of the first cooling circulation pipeline 31 is communicated with the oxidant storage tank 1, and the lower end is communicated with the nozzle interlayer of the thrust chamber, and the oxidant is input into the nozzle interlayer; the second cooling The upper end of the circulation pipeline 41 is communicated with the turbo pump 2, and the lower end is communicated with the nozzle interlayer of the thrust chamber, and the oxidant heated by the nozzle interlayer is input into the turbo pump 2, and the turbo expands to do work to drive the turbo pump 2 to work; the turbo pump 2 is arranged above the thrust chamber, the inlet is communicated with the oxidant storage tank 1 through the first pump pressure supply line 34, and the outlet is communicated with the thrust chamber through the second pump pressure supply line 35; after the turbo pump 2 is started, the oxidant is input to the The thrust chamber is combusted with the paraffin fuel 11 in the combustion chamber, and at the same time, the oxidant that drives the turbo pump to work enters the combustion chamber through the turbo pump exhaust line 33 to participate in the combustion;

The thrust vector control system includes a vector control flow regulator 27, a thrust vector control pipeline 30 and a secondary flow pipeline 32; the upper end of the thrust vector control pipeline 30 is communicated with the oxidant storage tank 1, and the lower end is connected with the secondary flow The pipelines 32 communicate with each other, and a plurality of the secondary flow pipelines 32 are arranged on the periphery of the expansion section of the thrust chamber nozzle along the circumferential direction, and communicate with a plurality of injection ports opened in the circumferential direction of the expansion section of the thrust chamber nozzle. The control valves on different secondary flow pipelines 32 are opened and closed to adjust the flow rate of nitrous oxide entering the expansion section of the nozzle, so as to realize thrust vector control and adjustment of the attitude of the ascender.

A further technical solution of the present invention is: the thrust chamber comprises a boron/potassium nitrate igniter 3, a thrust chamber housing 6, a regenerative cooling nozzle 7, an injector 8, a front combustion chamber 9, a front combustion chamber thermal insulation layer 10, Paraffin grain 11, combustion chamber 12, combustion chamber insulation layer 13, post combustion chamber insulation layer 14, post combustion chamber 15; 2 boron/potassium nitrate igniters 3 are arranged at the front combustion chamber; the injector 8 adopts hydraulic power Porous once-through injector with small loss; the front combustion chamber 9 further atomizes and disperses the oxidant, and the front combustion chamber insulation layer 10 is installed on the wall surface of the front combustion chamber 9 to protect the thrust chamber shell 6 from heat; the combustion chamber 12 The outer peripheral surface of the flame retardant is covered with a combustion chamber insulation layer 13 and a thrust chamber shell 6. The paraffin fuel 11 is placed in the combustion chamber, and its low-temperature mechanical properties can adapt to the temperature environment on the surface of Mars; in order to improve the combustion efficiency, a post-combustion chamber 15 is designed. A post-combustion chamber insulation layer 14 is installed on the wall of the post-combustion chamber; the nozzle adopts a regenerative cooling nozzle 7, and its outer wall is a sandwich structure composed of double walls, and the convective cooling of the liquid nitrous oxide in the sandwich is used to realize the nozzle heat protection.

A further technical solution of the present invention is that: the front end cover 4 of the thrust chamber is installed on the upper end of the thrust chamber, and two boron/potassium nitrate igniters 3 are installed on it to realize engine ignition.

A further technical solution of the present invention is: the extrusion type oxidant supply subsystem further includes a filling and discharging valve 16, a pressure reducing valve 17, a pressure increasing control valve 19, an extrusion system control valve 23, and an extrusion system flow regulator 25. Filling and discharging valve 16 is arranged at the outer end of the pipeline where a plurality of high-pressure helium gas storage tanks 5 communicate with each other, for filling helium gas into high-pressure helium gas storage tank 5; pressure reducing valve 17 and booster control valve 19 are provided On the pressurizing pipeline 28, it is used to control the output gas pressure of the pressurizing pipeline 28; the extrusion system control valve 23 and the extrusion system flow regulator 25 are arranged on the extrusion supply pipeline 29, and are used to control the output of the oxidant and the gas pressure. flow regulation;

A further technical solution of the present invention is: the pumped expansion cycle oxidant supply subsystem further includes a one-way valve 18, a cooling circulation pipeline control valve 20, a circulating circuit pipeline control valve 22, a pumping system control valve 24, a cooling circuit control valve 24, The circulation flow regulator 26; the check valve 18 is arranged on the exhaust line 33 of the turbo pump to prevent the backflow of the oxidant; the cooling circulation line control valve 20 and the cooling circulation flow regulator 26 are arranged on the first cooling circulation line 31, Used for oxidant output and flow regulation; the circulation loop pipeline control valve 22 is set on the second cooling circulation pipeline 41, and the pump pressure system control valve 24 is set on the first pump pressure supply pipeline 34, both used to control the oxidant enter.

A further technical solution of the present invention is: the number of the high-pressure helium gas storage tanks 5 is 4, which are uniformly distributed on the periphery of the thrust chamber shell 6 in the circumferential direction, and are used to pressurize the oxidant storage tank.

A further technical solution of the present invention is: the secondary flow pipeline 32 is an L-shaped pipe, the long arm end is arranged on the outer wall surface of the nozzle along the axial direction of the nozzle expansion section, and the short arm end is inserted into the nozzle of the nozzle ; The upper ends of a plurality of long arms are communicated with the thrust vector control pipeline 30 after being communicated through the annular pipeline.

A further technical solution of the present invention is: the number of the secondary flow pipelines 32 is 4, which are evenly distributed along the circumferential direction.

A further technical solution of the present invention is that: the thrust vector control system further includes a secondary flow pipeline control valve 21 , and the secondary flow pipeline 32 is notified of the on-off of each secondary flow pipeline 32 through the secondary flow pipeline control valve 21 .

A method for supplying an oxidant for a solid-liquid hybrid engine for a Mars ascending vehicle, characterized in that the specific steps are as follows:

Step 1: When the engine standby command is issued, the pressure boosting control valve 19 is opened to pressurize the oxidant storage tank 1, and the system enters the standby state;

Step 2: After the official work order is issued, the boron/potassium nitrate igniter 3 is started to generate high-temperature gas, and after 0.5s, the control valve 23 of the extrusion system is opened, the paraffin fuel 11 is ignited under the action of high-temperature gas and nitrous oxide, and the engine is ignited After the start is completed, the engine adopts the extrusion oxidant supply method;

Step 3: After the ignition is started, open the cooling circuit control valve 20 and the circulation circuit control valve 22. After the nitrous oxide flows through the interlayer in the regeneration cooling nozzle 7 to absorb heat, it enters the turbine, and the turbine pump 2 is started and turned on. The pump pressure system control valve 24, the turbo pump 2 absorbs nitrous oxide from the oxidant storage tank 1, and supplies it to the thrust chamber; the turbo pump works smoothly, and after monitoring the stability of the combustion chamber pressure, the extrusion system control valve 23 is closed. Expansion circulating oxidant supply mode;

Step 4: If the attitude adjustment in a certain direction is required during the flight of the ascender, open one or two secondary flow pipeline control valves 21 on the four sets of secondary flow pipelines 32, and control the flow regulator 27 through the vector control. Control the flow rate of the oxidant entering the expansion section of the nozzle. After the nitrous oxide enters the expansion section of the nozzle, it is rapidly atomized and evaporated, and mixed with the gas to interfere with the supersonic gas flow to generate an oblique shock wave, which deflects the direction of the supersonic gas flow. , generate a lateral force, and realize the attitude adjustment of the ascender.

beneficial effect

The beneficial effects of the present invention are:

1) The solid-liquid hybrid engine designed by the present invention adopts paraffin fuel with superior ultra-low temperature mechanical properties and nitrous oxide with low freezing point and high saturated vapor pressure as propellant, which solves the problem that solid and liquid engines cannot adapt to the extreme temperature difference on Mars and are difficult to long-term. storage, etc.;

2) The solid-liquid hybrid engine oxidant supply system designed by the present invention combines the extrusion type and the pump pressure type two types of oxidant supply systems, which solves the problem that due to the low temperature of the Martian environment, the vapor pressure of nitrous oxide is low. The problem that the expansion cycle supply system cannot be started smoothly by relying on the vapor pressure of nitrous oxide;

3) The solid-liquid hybrid engine oxidant supply system proposed in the present invention takes advantage of the fast response of the extrusion type oxidant supply method, which enables the engine thrust chamber to rapidly build up pressure, achieve a stable working state, and then turn into a pump pressure type oxidant. The supply method utilizes the pump pressure oxidant supply method to work in a stable state, which can effectively avoid the problem of excessive pressure drop in the thrust chamber during the engine operation in the extrusion type oxidant supply method. According to the calculation of the gas generation rate of the ignition powder, the gas concentration of boron/potassium nitrate in the thrust chamber reaches the highest at 0.5s, which is most conducive to the start of the engine;

4) The solid-liquid mixed engine oxidant supply system designed by the present invention utilizes the oxidant to absorb the heat transferred from the high-temperature gas to the nozzle wall, and the generated high-temperature work drives the turbo pump to work, which improves the energy utilization rate of the engine, and at the same time, the oxidant evaporates and absorbs heat. , to cool the nozzle wall to prevent nozzle ablation;

5) The thrust vector control system adopted by the present invention injects nitrous oxide with a certain pressure into the expansion section of the nozzle through the control valve and the flow regulator to interfere with the supersonic gas flow and achieve the purpose of thrust vector control. . The thrust vector control system only needs to control the coordinated work of the valve and the flow regulator, and has good time responsiveness. The control system is used to fix the nozzle, which simplifies the nozzle structure. Specifically, during the flight of the ascender, attitude adjustment in a certain direction is required, one or two secondary flow pipeline control valves 21 on the four sets of secondary flow pipelines 32 are opened, and the flow regulator 27 is controlled by the vector Control the flow rate of the oxidant entering the expansion section of the nozzle. After the nitrous oxide enters the expansion section of the nozzle, it is rapidly atomized and evaporated, and mixed with the gas to interfere with the supersonic gas flow to generate an oblique shock wave, which deflects the direction of the supersonic gas flow. , generate a lateral force, and realize the attitude adjustment of the ascender. After calculation, the maximum deflection of the ascender vector can be controlled by 3° in each direction.

Description of drawings

Fig. 1 is the solid-liquid hybrid engine system diagram of the present invention;

2 is a structural diagram of the solid-liquid hybrid engine according to the present invention; (1) a front view, (2) a main cross-sectional view, and (3) a right cross-sectional view;

Fig. 3 is a partial pipeline structure diagram of the solid-liquid hybrid engine according to the present invention; (1) a supply pipeline structure diagram; (2) a thrust vector control pipeline structure diagram.

DESCRIPTION OF REFERENCE NUMERALS: 1. Oxidant storage tank, 2. Turbo pump, 3. Boron/potassium nitrate igniter, 4. Thrust chamber front cover, 5. High pressure helium storage tank, 6. Thrust chamber housing, 7. Regeneration Cooling nozzle, 8. Injector, 9. Front combustion chamber, 10. Front combustion chamber insulation layer, 11. Paraffin grain, 12. Combustion chamber, 13. Combustion chamber insulation layer, 14. After combustion chamber insulation layer, 15. Rear combustion chamber, 16. Filling and discharging valve, 17. Pressure reducing valve, 18. Check valve, 19. Booster control valve, 20. Cooling circulation pipeline control valve, 21. Secondary flow pipeline control valve , 22. Circulation circuit pipeline control valve, 23. Extrusion system control valve, 24. Pump pressure system control valve, 25. Extrusion system flow regulator, 26. Cooling circulation flow regulator, 27. Vector control flow regulator , 28. Booster pipeline, 29. Extrusion supply pipeline, 30. Thrust vector control pipeline, 31. First cooling circulation pipeline, 32. Secondary flow pipeline, 33. Turbo pump exhaust pipeline, 34. The first pump pressure supply line, 35. The second pump pressure supply line, 41. The second cooling circulation line.

Detailed ways

The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", " rear, left, right, vertical, horizontal, top, bottom, inside, outside, clockwise, counterclockwise, etc., or The positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, Therefore, it should not be construed as a limitation of the present invention.

1-3, a solid-liquid hybrid engine for a Mars ascending vehicle of the present invention includes a thrust chamber, an oxidant supply system and a thrust vector control system;

The oxidant supply system includes an oxidant storage tank 1, an extruded oxidant supply subsystem and a pumped expansion cycle oxidant supply subsystem; the oxidant storage tank 1 is arranged above the thrust chamber, and the extruded oxidant supply subsystem The oxidant is input into the thrust chamber by extrusion, and the pump expansion cycle oxidant supply subsystem inputs the oxidant into the thrust chamber through the expansion cycle;

The extruded oxidant supply subsystem includes a high-pressure helium storage tank 5, a pressurization pipeline 28 and an extrusion supply pipeline 29; a plurality of high-pressure helium storage tanks 5 are arranged on the periphery of the thrust chamber, and their outlets are connected to each other through pipes. connected with the oxidant storage tank 1 through the pressurization pipeline 28; the outlet of the pressurized pipeline 28 extends into the oxidant storage tank 1 and extends above the interior of the oxidant storage tank 1, for the high pressure helium gas The helium gas in the storage tank 5 is passed into the top of the oxidant storage tank 1 to give the oxidant downward pressure; the output port of the oxidant storage tank 1 is communicated with the thrust chamber through the extrusion supply pipeline 29, and the oxidant output by extrusion is connected to the thrust chamber. Input into the thrust chamber and burn with the paraffin fuel 11 in the combustion chamber;

The extrusion type oxidant supply subsystem also includes a filling and discharging valve 16, a pressure reducing valve 17, a pressure boosting control valve 19, an extrusion system control valve 23, and an extrusion system flow regulator 25; the filling and discharging valve 16 is arranged in the The outer ends of the pipelines where the multiple high-pressure helium gas storage tanks 5 communicate with each other are used to fill the high-pressure helium gas storage tank 5 with helium gas; It is used to control the output gas pressure of the booster pipeline 28; the extrusion system control valve 23 and the extrusion system flow regulator 25 are arranged on the extrusion supply pipeline 29 to control the output of the oxidant and the flow regulation.

The pumped expansion cycle oxidant supply subsystem includes a turbo pump 2, a first cooling cycle pipeline 31, a turbo pump exhaust pipeline 33, a first pump pressure supply pipeline 34, a second pump pressure supply pipeline 35, The second cooling cycle pipeline 41; the upper end of the first cooling cycle pipeline 31 is communicated with the oxidant storage tank 1, and the lower end is communicated with the nozzle interlayer of the thrust chamber, and will be input into the nozzle interlayer; the second cooling cycle The upper end of the pipeline 41 is communicated with the turbo pump 2, and the lower end is communicated with the nozzle interlayer of the thrust chamber, and the oxidant heated by the nozzle interlayer is input into the turbo pump 2, and the turbo expands to do work to drive the turbo pump 2 to work; the turbo pump 2 It is arranged above the thrust chamber, the inlet is communicated with the oxidant storage tank 1 through the first pump pressure supply line 34, and the outlet is communicated with the thrust chamber through the second pump pressure supply line 35; after the turbo pump 2 is started, the oxidant is input to the thrust The combustion chamber is combusted with the paraffin fuel 11 in the combustion chamber, and at the same time, the oxidant that drives the turbo pump to work enters the combustion chamber through the turbo pump exhaust line 33 to participate in the combustion;

The pumped expansion cycle oxidant supply subsystem also includes a one-way valve 18, a cooling cycle pipeline control valve 20, a circulating circuit pipeline control valve 22, a pumping system control valve 24, and a cooling cycle flow regulator 26; one-way The valve 18 is arranged on the exhaust pipe 33 of the turbo pump to prevent the backflow of the oxidant; the cooling circulation pipe control valve 20 and the cooling circulation flow regulator 26 are arranged on the first cooling circulation pipe 31 for output and flow regulation of the oxidant ; Circulation loop pipeline control valve 22 is arranged on the second cooling cycle pipeline 41, and the pump pressure system control valve 24 is arranged on the first pump pressure supply pipeline 34, both of which are used to control the oxidant input.

The thrust vector control system includes a vector control flow regulator 27, a thrust vector control pipeline 30 and a secondary flow pipeline 32; the upper end of the thrust vector control pipeline 30 is communicated with the oxidant storage tank 1, and the lower end is connected with the secondary flow The pipelines 32 communicate with each other, and a plurality of the secondary flow pipelines 32 are arranged on the periphery of the expansion section of the thrust chamber nozzle along the circumferential direction, and communicate with a plurality of injection ports opened in the circumferential direction of the expansion section of the thrust chamber nozzle. The control valves on different secondary flow pipelines 32 are opened and closed to adjust the flow rate of nitrous oxide entering the expansion section of the nozzle, so as to realize thrust vector control and adjustment of the attitude of the ascender.

The thrust chamber includes a boron/potassium nitrate igniter 3, a thrust chamber shell 6, a regenerative cooling nozzle 7, an injector 8, a front combustion chamber 9, a front combustion chamber insulation layer 10, a paraffin grain 11, and a combustion chamber 12. , the combustion chamber insulation layer 13, the rear combustion chamber insulation layer 14, the rear combustion chamber 15; 2 boron/potassium nitrate igniters 3 are arranged at the front combustion chamber; the injector 8 adopts a porous straight-through injection with small hydraulic loss The front combustion chamber 9 further atomizes and disperses the oxidant, and a front combustion chamber insulation layer 10 is installed on the wall surface of the front combustion chamber 9 to protect the thrust chamber shell 6 from heat; the outer peripheral surface of the combustion chamber 12 is covered with a combustion chamber Insulation layer 13 and thrust chamber shell 6, paraffin fuel 11 is placed in the combustion chamber, and its low-temperature mechanical properties can adapt to the temperature environment on the surface of Mars; in order to improve the combustion efficiency, a post-combustion chamber 15 is designed. The combustion chamber insulation layer 14; the nozzle adopts the regenerative cooling nozzle 7, and its outer wall is a sandwich structure composed of double walls, and the convective cooling of the liquid nitrous oxide in the sandwich is used to realize the thermal protection of the nozzle. The front end cover 4 of the thrust chamber is installed on the upper end of the thrust chamber, and two boron/potassium nitrate igniters 4 are installed on it to realize the ignition of the engine.

Example:

The "solid-liquid hybrid engine for Mars ascension vehicle" of the present invention includes: an oxidant storage tank 1, a turbo pump 2, a boron/potassium nitrate igniter 3, a thrust chamber front end cover 4, a high-pressure helium gas storage tank 5, a thrust chamber shell 6, Regenerative cooling nozzle 7, injector 8, front combustion chamber 9, front combustion chamber insulation layer 10, paraffin grain 11, combustion chamber 12, combustion chamber insulation layer 13, post combustion chamber insulation layer 14, post combustion chamber 15, Filling and discharging valve 16, pressure reducing valve 17, one-way valve 18, pressure boosting control valve 19, cooling circulation line control valve 20, secondary flow line control valve 21, circulation circuit line control valve 22, extrusion system Control valve 23, pumping system control valve 24, extrusion system flow regulator 25, cooling circulation flow regulator 26, vector control flow regulator 27, booster pipeline 28, extrusion supply pipeline 29, thrust vector control tube circuit 30, first cooling circulation line 31, secondary flow line 32, turbo pump exhaust line 33, first pump pressure supply line 34, second pump pressure supply line 35, second cooling circulation line 41.

Assembly of the extrusion type oxidant supply subsystem: the pressurization pipeline 28 connects the four high-pressure helium gas storage tanks 5 , and a filling and discharging valve 16 is installed at one end of the pipeline 28 for filling the high-pressure helium gas storage tank 5 The helium gas is filled, the other end of the pressurizing pipeline 28 leads into the oxidant storage tank 1 , and the pressurizing control valve 19 and the pressure reducing valve 17 are installed on the pressurizing pipeline 28 . The extrusion supply pipeline 29 communicates the oxidant storage tank 1 with the thrust chamber, and is used to realize the delivery of the oxidant into the thrust chamber. The extrusion supply pipeline 29 is equipped with an extrusion system control valve 23 and an extrusion system flow regulator. 25. Realize the flow management of oxidant entering the thrust chamber. The oxidant storage tank is also connected with a filling and discharging valve to realize the filling of the oxidant.

Pump expansion cycle oxidant supply subsystem assembly: The first cooling cycle pipeline 31 connects the oxidant storage tank 1, the regeneration cooling nozzle 7 and the turbo pump 2, and the function is to introduce the low-temperature oxidant into the interlayer of the regeneration cooling nozzle 7 , to achieve active thermal protection of the nozzle, the high-temperature oxidant after heat absorption is led to the turbine for expansion to do work, and pushes the turbo pump 2 to work, and the turbine discharges the expanded nitrous oxide gas through the turbo pump exhaust pipe 33 into the thrust Inside, a check valve 18 is installed on the exhaust line 33 of the turbo pump to prevent the backflow of the oxidant. The first pump pressure supply line 34 and the second pump pressure supply line 35 respectively connect the oxidant storage tank 1, the turbo pump 2 and the thrust chamber, and the turbo pump absorbs the oxidant and supplies it to the thrust chamber at a certain pressure.

Thrust vector control system assembly: one end of the thrust vector control pipeline 30 is connected to the oxidant storage tank 1, and the other end is connected to a diverter. The ports are connected to each other to lead the oxidant to the expansion section of the nozzle. Each secondary flow pipeline is equipped with a vector control flow regulator 27 and a secondary flow pipeline control valve 21. By opening and closing different secondary flow pipelines and adjusting The amount of oxidant flow can realize thrust vector control and ascender attitude adjustment.

After the engine is assembled, the high-pressure helium storage tank 5 is filled with high-pressure helium gas through the filling and discharge valve 16 on the boosting pipeline 28, and the pressure in the high-pressure helium gas storage tank 5 is required to be no less than 10MPa. Fill the storage tank with nitrous oxide liquid through the filling and discharging valve on the oxidant storage tank 1, and the mass should not be less than 238kg.

The specific operations of this embodiment:

When the engine standby command is issued, the supercharging control valve 19 is opened to pressurize the oxidant storage tank 1, and the system enters the standby state. After the official work order is issued, the boron/potassium nitrate igniter 3 is started to generate high-temperature gas. After 0.5s, the control valve 23 of the extrusion system is opened, and the paraffin fuel 11 is ignited under the action of high-temperature gas and nitrous oxide. The ignition and start of the engine are completed. At this time, the engine adopts the extrusion type oxidant supply method. After the ignition is started, the control valve 20 of the cooling circuit and the control valve 22 of the circulation circuit are opened. After the nitrous oxide flows through the interlayer in the regeneration cooling nozzle 7 to absorb heat, it enters the turbine, the turbine pump 2 is started, and the pumping system is turned on. The valve 24 is controlled, and the turbo pump 2 sucks nitrous oxide from the oxidant tank 1 and supplies it to the thrust chamber. The turbo pump works smoothly, and after monitoring the stability of the combustion chamber pressure, the control valve 23 of the extrusion system is closed. At this time, the engine adopts the expansion cycle oxidant supply method. By adjusting the cooling circulation flow regulator 26, the flow rate of the nitrous oxide entering the interlayer of the regenerative cooling nozzle 7 is managed to realize the speed control of the turbo pump 2 and ensure the stable supply of the oxidant to the thrust chamber.

If the attitude adjustment in a certain direction needs to be performed during the flight of the ascender, one or two of the secondary flow pipeline control valves 21 on the four sets of secondary flow pipelines 32 are opened, and the vector control flow regulator 27 is used to control the inlet jet. The flow rate of the oxidant in the expansion section of the tube is large. After the nitrous oxide enters the expansion section of the nozzle, it is rapidly atomized and evaporated, and mixed with the gas, which interferes with the supersonic gas flow and generates an oblique shock wave, which deflects the direction of the supersonic gas flow and produces side effects. To achieve the attitude adjustment of the ascender. After calculation, the maximum deflection of the ascender vector can be controlled by 3° in each direction.

Although the embodiments of the present invention have been shown and described above, it should be understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and those of ordinary skill in the art will not depart from the principles and spirit of the present invention Variations, modifications, substitutions, and alterations to the above-described embodiments are possible within the scope of the present invention without departing from the scope of the present invention.

Claims (10)

1. a solid-liquid hybrid engine for a Mars ascending vehicle, comprising a thrust chamber; it is characterized in that: also comprise an oxidant supply system and a thrust vector control system that are connected with the thrust chamber; The oxidant supply system includes an oxidant storage tank (1), an extruded oxidant supply subsystem and a pumped expansion cycle oxidant supply subsystem; the oxidant storage tank (1) is arranged above the thrust chamber, and the extruded oxidant supply subsystem The oxidant supply subsystem inputs oxidant to the thrust chamber through extrusion. First, the extrusion oxidant supply method is used to rapidly build up the pressure in the thrust chamber of the engine to achieve a stable working state, and then switch to the pump-pressure oxidant supply method. The expansion cycle oxidant supply subsystem supplies oxidant to the thrust chamber through the expansion cycle; The extrusion-type oxidant supply subsystem includes a high-pressure helium storage tank (5), a boosting pipeline (28) and an extrusion supply pipeline (29); a plurality of high-pressure helium storage tanks (5) are arranged in the thrust chamber The outer periphery of the oxidant is communicated with each other through pipes, and communicated with the oxidant storage tank (1) through the pressurization pipeline (28); the outlet of the pressurization pipeline (28) extends into the oxidant storage tank (1), and It extends to the inside of the oxidant storage tank (1), and is used to pass the helium gas in the high-pressure helium gas storage tank (5) into the upper part of the inside of the oxidant storage tank (1) to give the oxidant downward pressure; the oxidant storage tank The output port of (1) is communicated with the thrust chamber through the extrusion supply pipeline (29), and the oxidant output by the extrusion is input into the thrust chamber to burn with the paraffin fuel (11) in the combustion chamber; The pumped expansion cycle oxidant supply subsystem includes a turbo pump (2), a first cooling cycle pipeline (31), a turbo pump exhaust pipeline (33), a first pump pressure supply pipeline (34), a first Two cooling circulation pipelines (41) and a second pump pressure supply pipeline (35); the upper end of the first cooling circulation pipeline (31) is communicated with the oxidant storage tank (1), and the lower end is interlayered with the nozzle of the thrust chamber Connected, the oxidant is input into the nozzle interlayer; the upper end of the second cooling circulation pipeline (41) is communicated with the turbo pump (2), and the lower end is communicated with the nozzle interlayer of the thrust chamber, and will be heated through the nozzle interlayer. The oxidant is input into the turbo pump (2), the turbo expands to do work, and drives the turbo pump (2) to work; the turbo pump (2) is arranged above the thrust chamber, and the inlet is connected to the oxidant storage tank through the first pump pressure supply pipeline (34). (1) communication, the outlet is communicated with the thrust chamber through the second pump pressure supply pipeline (35); after the turbo pump (2) is started, the oxidant is input into the thrust chamber, and burns with the paraffin fuel (11) in the combustion chamber, and at the same time, The oxidant that drives the turbo pump to work enters the combustion chamber through the turbo pump exhaust line (33) to participate in the combustion; The thrust vector control system comprises a vector control flow regulator (27), a thrust vector control pipeline (30) and a secondary flow pipeline (32); the upper end of the thrust vector control pipeline (30) is connected to an oxidant storage tank (1) Communication, the lower end is communicated with the secondary flow pipeline (32), and a plurality of the secondary flow pipelines (32) are circumferentially arranged on the periphery of the expansion section of the thrust chamber nozzle, and are connected with the thrust chamber nozzle. The multiple injection ports opened in the circumferential direction of the expansion section are connected, and by opening and closing the control valves on different secondary flow pipelines (32), the flow rate of nitrous oxide entering the expansion section of the nozzle is adjusted to realize thrust vector control and ascender. attitude adjustment. 2. The solid-liquid hybrid engine for the Mars ascending vehicle according to claim 1, wherein the thrust chamber comprises a boron/potassium nitrate igniter (3), a thrust chamber housing (6), a regenerative cooling nozzle (7) ), injector (8), front combustion chamber (9), front combustion chamber insulation layer (10), paraffin fuel (11), combustion chamber (12), combustion chamber insulation layer (13), post combustion chamber insulation layer (14), post combustion chamber (15); 2 boron/potassium nitrate igniters (3) are arranged at the front combustion chamber; the injector (8) adopts a porous straight-through injector with small hydraulic loss; front combustion The chamber (9) further atomizes and disperses the oxidant, and a front combustion chamber heat insulating layer (10) is installed on the wall surface of the front combustion chamber (9) to thermally protect the thrust chamber shell (6); the outer periphery of the combustion chamber (12) The surface is covered with a combustion chamber insulation layer (13) and a thrust chamber shell (6). The paraffin fuel (11) is placed in the combustion chamber, and its low-temperature mechanical properties can adapt to the temperature environment on the surface of Mars. The chamber (15) is provided with a post-combustion chamber thermal insulation layer (14) on the wall surface of the post-combustion chamber; the nozzle adopts a regenerative cooling nozzle (7), the outer wall of which is a sandwich structure composed of double walls, and uses liquid nitrous oxide. Convective cooling within the sandwich achieves nozzle thermal protection. 3. according to claim 2, it is characterized in that: the thrust chamber front end cover (4) is installed on the thrust chamber upper end, and 2 boron/potassium nitrate igniters (3) are installed on it, Used to achieve engine ignition. 4. The solid-liquid hybrid engine for a Mars ascending vehicle according to claim 1, wherein the extruded oxidant supply subsystem further comprises a filling and discharging valve (16), a pressure reducing valve (17), a pressure boosting control A valve (19), an extrusion system control valve (23), an extrusion system flow regulator (25); a filling and discharging valve (16) is arranged at the outer end of the pipeline where the plurality of high-pressure helium gas storage tanks (5) communicate with each other , used for filling the high-pressure helium storage tank (5) with helium gas; the pressure reducing valve (17) and the booster control valve (19) are arranged on the booster pipeline (28) to control the booster pipeline (28) Output gas pressure; the extrusion system control valve (23) and the extrusion system flow regulator (25) are arranged on the extrusion supply pipeline (29) for controlling the output of the oxidant and regulating the flow. 5. The solid-liquid hybrid engine for a Mars ascending vehicle according to claim 1, wherein the pumped expansion cycle oxidant supply subsystem further comprises a one-way valve (18), a cooling cycle pipeline control valve (20) , circulation loop pipeline control valve (22), pump pressure system control valve (24), cooling circulation flow regulator (26); one-way valve (18) is arranged on the turbo pump exhaust pipeline (33) to prevent oxidant return; the cooling circulation pipeline control valve (20) and the cooling circulation flow regulator (26) are arranged on the first cooling circulation pipeline (31) for output and flow regulation of the oxidant; the circulation circuit pipeline control valve (22) ) is arranged on the second cooling circulation pipeline (41), and the pump pressure system control valve (24) is arranged on the first pump pressure supply pipeline (34), both of which are used to control the oxidant input. 6. The solid-liquid hybrid engine for the Mars ascending vehicle according to claim 1, wherein the quantity of the high-pressure helium storage tank (5) is 4, which are evenly distributed on the periphery of the thrust chamber shell (6) along the circumferential direction , used to pressurize the oxidant tank. 7. The solid-liquid hybrid engine for a Mars ascending vehicle according to claim 1, wherein the secondary flow pipeline (32) is an L-shaped pipe, and its long arm end is arranged along the axial direction of the nozzle expansion section On the outer wall surface of the nozzle, the short arm end is inserted into the nozzle of the nozzle; the upper ends of the plurality of long arms are connected through an annular pipe and then communicated with the thrust vector control pipeline (30). 8 . The solid-liquid hybrid engine for a Mars ascending vehicle according to claim 1 , wherein the number of the secondary flow pipelines ( 32 ) is 4, which are evenly distributed along the circumferential direction. 9 . 9. The solid-liquid hybrid engine for a Mars ascending vehicle according to claim 1, wherein the thrust vector control system further comprises a secondary flow pipeline control valve (21), which is controlled by the secondary flow pipeline control valve (21). ) notifies the on-off of each secondary flow pipeline (32). 10. A method for supplying an oxidant of a solid-liquid hybrid engine for a Mars ascending vehicle according to any one of claims 1-9, characterized in that the concrete steps are as follows: Step 1: When the engine standby command is issued, the pressure boosting control valve (19) is opened to pressurize the oxidant storage tank (1), and the system enters the standby state; Step 2: After the official work order is issued, the boron/potassium nitrate igniter (3) is activated to generate high-temperature gas, and after 0.5s, the control valve (23) of the extrusion system is opened, and the paraffin fuel (11) is heated between the high-temperature gas and nitrous oxide. The engine is ignited under the action, and the ignition and start of the engine are completed. At this time, the engine adopts the extrusion type oxidant supply method; Step 3: After the ignition is started, the cooling circuit control valve (20) and the circulation circuit control valve (22) are opened, and the nitrous oxide flows through the interlayer in the regeneration cooling nozzle (7) to absorb heat, and then enters the turbine. The pump (2) is started, and the control valve (24) of the pump pressure system is opened, and the turbo pump (2) absorbs nitrous oxide from the oxidant storage tank (1) and supplies it to the thrust chamber; the turbo pump works smoothly and monitors the stable pressure of the combustion chamber After that, close the extrusion system control valve (23), at this time the engine adopts the expansion cycle type oxidant supply mode; Step 4: If the attitude adjustment in a certain direction needs to be performed during the flight of the ascender, open one or two secondary flow pipeline control valves (21) on the four sets of secondary flow pipelines (32), and control the valve through vector control. The flow regulator (27) controls the flow rate of the oxidant entering the expansion section of the nozzle. After the nitrous oxide enters the expansion section of the nozzle, it is rapidly atomized and evaporated, and mixed with the gas to interfere with the supersonic gas flow to generate oblique shock waves. The direction of the supersonic gas flow is deflected, generating lateral force and realizing the attitude adjustment of the ascender.

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