阅读说明：本技术 一种高可靠液体火箭发动机系统 (High-reliability liquid rocket engine system ) 是由 聂万胜 王辉 仝毅恒 于 2020-06-04 设计创作，主要内容包括：本发明公开了一种高可靠液体火箭发动机系统,包括控制系统、燃料泵一、氧化剂泵一、燃料泵二、氧化剂泵二、旋转储能装置、逆变器、电机和压力传感器；旋转储能装置一方面直接输出自身机械能,用于驱动燃料泵一与氧化剂泵一；另一方面将机械能转化为电能输入电机,用于驱动燃料泵二与氧化剂泵二；控制系统通过压力传感器实时监测燃烧室内的压力,并利用逆变器调节电机的输入电压,进而调节燃料泵二与氧化剂泵二的输送功率,从而使得燃烧室的压力保持在设定的恒定范围。本发明摒弃了传统液体火箭发动机中的燃气发生器和涡轮等结构复杂、加工难度大、工作环境恶劣、故障率较高的部件,从而使燃烧室稳定燃烧,保证了发动机系统的可靠性。(The invention discloses a high-reliability liquid rocket engine system, which comprises a control system, a first fuel pump, a first oxidant pump, a second fuel pump, a second oxidant pump, a rotary energy storage device, an inverter, a motor and a pressure sensor, wherein the first fuel pump is connected with the first oxidant pump; the rotary energy storage device directly outputs self mechanical energy for driving the first fuel pump and the first oxidant pump; on the other hand, the mechanical energy is converted into electric energy to be input into the motor, and the electric energy is used for driving the second fuel pump and the second oxidant pump; the control system monitors the pressure in the combustion chamber in real time through the pressure sensor, and adjusts the input voltage of the motor by using the inverter, so as to adjust the transmission power of the second fuel pump and the second oxidant pump, and further keep the pressure in the combustion chamber in a set constant range. The invention abandons the components of the traditional liquid rocket engine, such as the gas generator, the turbine and the like, which have complex structures, high processing difficulty, severe working environment and higher failure rate, thereby ensuring the stable combustion of the combustion chamber and ensuring the reliability of the engine system.)

1. A high-reliability liquid rocket engine system is characterized in that: the system comprises a control system, a first fuel pump, a first oxidant pump, a second fuel pump, a second oxidant pump, a rotary energy storage device, an inverter, a motor and a pressure sensor, wherein the first fuel pump, the first oxidant pump, the second fuel pump, the second oxidant pump, the rotary energy storage device, the inverter, the motor and the pressure sensor are all connected with the control system;

the first fuel pump and the second fuel pump are used for conveying fuel to a combustion chamber of the liquid rocket engine, and the first oxidant pump and the second oxidant pump are used for conveying oxidant to the combustion chamber of the liquid rocket engine; pressure sensors are arranged in the supply system, the injector and the combustion chamber;

on one hand, the rotary energy storage device directly outputs self mechanical energy for driving the first fuel pump and the first oxidant pump; on the other hand, the mechanical energy is converted into electric energy to be input into the motor, and the electric energy is used for driving the second fuel pump and the second oxidant pump; the inverter is used for controlling the input voltage of the motor;

the control system monitors the pressure in the supply system, the injector and the combustion chamber in real time through the pressure sensor, and adjusts the input voltage of the motor by using the inverter, so as to adjust the delivery power of the second fuel pump and the second oxidant pump, and further keep the pressure of the combustion chamber in a set constant range.

2. The highly reliable liquid rocket engine system according to claim 1, wherein: the rotary energy storage device comprises an energy storage rotor, a rotating shaft, a vacuum bin and a permanent magnet brushless motor stator;

the energy storage rotor is coaxially sleeved on the periphery of the rotating shaft, the vacuum bin is coaxially sleeved on the periphery of the energy storage rotor, and two ends of the rotating shaft respectively extend out of two ends of the vacuum bin to form two output ends for directly outputting self mechanical energy so as to drive the first fuel pump and the first oxidant pump;

the permanent magnet brushless motor stator is coaxially arranged on the inner wall surface of the vacuum bin at the periphery of the energy storage rotor; the energy storage rotor is internally and integrally provided with a motor rotor, and the motor rotor and the permanent magnet brushless motor stator form a permanent magnet brushless motor.

3. The highly reliable liquid rocket engine system according to claim 2, wherein: the rotating shaft is rotatably connected with the vacuum bin through a superconducting magnetic suspension bearing.

4. A highly reliable liquid rocket engine system according to claim 3, wherein: the output end of the rotating shaft is respectively connected with the first oxidant pump or the first fuel pump through the speed reducer.

5. The highly reliable liquid rocket engine system according to claim 4, wherein: the output end of the rotating shaft is connected with the input shaft spline of the speed reducer through a spline; the vacuum bin also comprises two auxiliary bins, and the two auxiliary bins are coaxially sleeved on the peripheries of the input shafts of the two speed reducers; one end of each auxiliary bin is hermetically connected to the outer wall surface of the vacuum bin shell, and the other end of each auxiliary bin is hermetically connected to the reducer shell.

6. The highly reliable liquid rocket engine system according to claim 2, wherein: the energy storage rotor is formed by weaving carbon fibers and copper fibers in a mixed mode and can bear the surface speed of 400 m/s.

7. The highly reliable liquid rocket engine system according to claim 6, wherein: the energy storage rotor is of a disc-shaped structure and the shape coefficient of the energy storage rotor0.9-1, energy storage density of the energy storage rotorNot less than 230 Wh/kg; when the shape and the size of the energy storage rotor are not changed, the energy storage density of the energy storage rotor is improvedThereby improving the stored energy of the energy storage rotor and further reducing the whole weight of the liquid rocket engine.

8. The highly reliable liquid rocket engine system according to claim 6, wherein: the energy storage rotor adopts a variable cross-section conical shell or spoke structure.

9. The highly reliable liquid rocket engine system according to claim 1, wherein: the control system inputs control signals to the speed reducer and the inverter according to the set rocket thrust, on one hand, the speed reducer adjusts the rotating speed of the first fuel pump and the first oxidant pump according to the control signals, on the other hand, the inverter adjusts the input of the motor according to the control signals so as to adjust the transmission power of the second fuel pump and the second oxidant pump, the two aspects are adjusted together, the flow regulation of the oxidant and the fuel is realized, and the rocket thrust is changed.

Technical Field

The invention relates to the field of liquid rocket engines, in particular to a high-reliability liquid rocket engine system.

Background

The thrust of the carrier rocket is large, and the stage of the spaceflight is large. The problem of unstable combustion in the liquid rocket engine always troubles engine designers, and is the difficult point of rocket engine design. The problem of combustion instability in gas generators or prechambers in open-cycle and closed-cycle liquid rocket engines is frequent.

As shown in fig. 3, a schematic diagram of the most advanced full flow staged combustion liquid rocket power system in the world today is shown, with a closed propellant circulation supply system comprising a plurality of complex, low reliability components such as a rich burn prechamber 1', an oxygen rich prechamber 2', a fuel turbopump 3 'and an oxidizer turbopump 4'.

The turbopump is complex in design, and the turbine bears high temperature, high pressure, high vibration and high rotating speed, so that the design and processing are very difficult, the reliability is poor, and the failure rate is high. According to statistics, about half of the failures of the rocket engine are caused by the turbopump, and are pain points restricting the development of the aerospace propulsion technology. The propellant supply system of the liquid rocket engine has no fundamental change since the invention of the rocket engine, and the subversion of the propellant supply system is desired.

Disclosure of Invention

The invention aims to solve the technical problem of providing a high-reliability liquid rocket engine system aiming at the defects of the prior art, and the high-reliability liquid rocket engine system adopts a rotary energy storage device, so that parts such as a gas generator, a precombustion chamber, a turbine and the like in open circulation or closed circulation of the traditional liquid rocket engine, which have complex structures, high processing difficulty, severe working environment and higher failure rate, are abandoned, the design of the traditional liquid rocket engine is thoroughly changed, and the working reliability of the liquid rocket engine and the quick adjustment capability of a propellant are fundamentally improved.

In order to solve the technical problems, the invention adopts the technical scheme that:

a high-reliability liquid rocket engine system comprises a control system, and a first fuel pump, a first oxidant pump, a second fuel pump, a second oxidant pump, a rotary energy storage device, an inverter, a motor and a pressure sensor which are all connected with the control system.

The first fuel pump and the second fuel pump are used for conveying fuel to a combustion chamber of the liquid rocket engine, and the first oxidant pump and the second oxidant pump are used for conveying oxidant to the combustion chamber of the liquid rocket engine. Pressure sensors are arranged in the supply system, the injector and the combustion chamber.

The rotary energy storage device will on the one hand directly output its own mechanical energy for driving the first fuel pump and the first oxidant pump. On the other hand, the mechanical energy is converted into electric energy to be input into the motor for driving the second fuel pump and the second oxidant pump. The inverter is used for controlling the input voltage of the motor.

The control system monitors the pressure in the supply system, the injector and the combustion chamber in real time through the pressure sensor, and adjusts the input voltage of the motor by using the inverter, so as to adjust the delivery power of the second fuel pump and the second oxidant pump, and further keep the pressure of the combustion chamber in a set constant range.

The rotary energy storage device comprises an energy storage rotor, a rotating shaft, a vacuum bin and a permanent magnet brushless motor stator.

The energy storage rotor is coaxially sleeved on the periphery of the rotating shaft, the vacuum bin is coaxially sleeved on the periphery of the energy storage rotor, and two ends of the rotating shaft respectively extend out of two ends of the vacuum bin to form two output ends for directly outputting self mechanical energy so as to drive the first fuel pump and the first oxidant pump.

The permanent magnet brushless motor stator is coaxially arranged on the inner wall surface of the vacuum chamber at the periphery of the energy storage rotor. The energy storage rotor is internally and integrally provided with a motor rotor, and the motor rotor and the permanent magnet brushless motor stator form a permanent magnet brushless motor.

The rotating shaft is rotatably connected with the vacuum bin through a superconducting magnetic suspension bearing.

The output end of the rotating shaft is respectively connected with the first oxidant pump or the first fuel pump through the speed reducer.

The output end of the rotating shaft is connected with the input shaft spline of the speed reducer through the spline. The vacuum bin further comprises two auxiliary bins, and the two auxiliary bins are coaxially sleeved on the peripheries of the input shafts of the two speed reducers. One end of each auxiliary bin is hermetically connected to the outer wall surface of the vacuum bin shell, and the other end of each auxiliary bin is hermetically connected to the reducer shell.

The energy storage rotor is formed by weaving carbon fibers and copper fibers in a mixed mode and can bear the surface speed of 400 m/s.

The energy storage rotor is of a disc-shaped structure and adopts an equal stress design structure, and the shape coefficient K of the energy storage rotor_sThe energy storage density e of the energy storage rotor is not less than 230Wh/kg and is 0.9-1; when the shape and the size of the energy storage rotor are not changed, the energy storage density e of the energy storage rotor is improved, so that the energy storage capacity of the energy storage rotor is improved, and the whole weight of the liquid rocket engine is reduced.

The energy storage rotor adopts a variable cross-section conical shell or spoke structure.

The control system inputs control signals to the speed reducer and the inverter according to the set rocket thrust, on one hand, the speed reducer adjusts the rotating speed of the first fuel pump and the first oxidant pump according to the control signals, on the other hand, the inverter adjusts the input of the motor according to the control signals so as to adjust the transmission power of the second fuel pump and the second oxidant pump, the two aspects are adjusted together, the flow regulation of the oxidant and the fuel is realized, and the rocket thrust is changed.

The invention has the following beneficial effects:

1. compared with the traditional propellant closed cycle engine, the invention adopts an advanced and efficient rotary energy storage device to replace high-fault-rate components with high temperature, high pressure and high rotating speed in the traditional liquid rocket engine such as a gas generator, a precombustion chamber, a turbine and the like, forms a simple direct-connected propellant supply system, greatly simplifies the propellant pressurization transportation mode of the engine, reduces the occurrence probability of engine faults and fundamentally improves the reliability of the engine.

2. On one hand, the rotary energy storage device can realize mechanical energy output: the rotary energy storage device is connected with the speed reducer through a spline, the speed reducer is connected with the first fuel pump and the first oxidant pump through a spline, and the speed changer is in gear transmission; on the other hand, the electric energy output can be realized: the energy storage rotor is excited to generate electric energy and input the electric energy into the motor, and the inverter controls the input of the motor according to the control signal to ensure stable output as required; the motor is connected with the second fuel pump and the second oxidant pump through splines.

3. The invention can realize the fast rocket thrust adjustment: the control system inputs control signals to the speed reducer and the inverter, on one hand, the speed reducer adjusts the rotating speed according to the control signals so as to adjust the rotating speeds of the first fuel pump and the first oxidant pump, on the other hand, the inverter adjusts the input of the motor according to the control signals so as to adjust the transmission power of the second fuel pump and the second oxidant pump, the two aspects are adjusted together, the flow adjustment of the oxidant and the fuel is realized, and the thrust of the rocket is changed.

4. The invention can realize the combustion control of the rocket engine: the control system inputs control signals to the speed reducer and the inverter immediately once abnormal oscillation is found by collecting and diagnosing pressure change in an engine supply system, the injector and the combustion chamber, so that the working condition of the engine is changed, the control of combustion instability in the rocket engine is realized, and the safety and stability of the engine are ensured.

5. The energy storage rotor is an integrated rotor and is formed by weaving carbon fibers and copper fibers together, and the carbon fibers have high strength and can meet the requirement of high-speed rotation energy storage; and the copper fiber is conductive, and the woven energy storage rotor can convert the mechanical energy of the energy storage rotor into electric energy through excitation. Due to the integrated design, the space can be efficiently utilized, and the energy density of the rotary energy storage device is increased.

Drawings

Fig. 1 shows a schematic diagram of a highly reliable liquid rocket engine system according to the present invention.

Fig. 2 shows a schematic structural diagram of a rotary energy storage device according to the present invention.

FIG. 3 shows a schematic diagram of a prior art full flow staged combustion liquid rocket power system.

Among them are:

a rich burn prechamber; 2', an oxygen-enriched precombustion chamber; 3' a fuel turbopump; oxidant turbo pump;

10. a combustion chamber;

11. a first oxidation pump; 12. a second oxidation pump; 13. a first fuel pump; 14. a second fuel pump;

20. a control system;

30. a motor; 31. an inverter;

40. a rotational energy storage device;

41. an energy storage rotor; 42. a vacuum bin; 421. an auxiliary bin; 43. a permanent magnet brushless motor stator; 44. a rotating shaft; 45. a superconducting magnetic suspension bearing; 46. an internal spline;

50. and a speed reducer.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.