Ignition control system for distributed orbit and attitude control engines

Abstract

The present invention provides an ignition control system suitable for a distributed orbit attitude control engine, comprising a propulsion circuit box, a low-voltage shielded cable and a bipropellant thruster, wherein the bipropellant thruster comprises a thrust chamber, an integrated spark plug, an oxygen circuit solenoid valve and a combustion circuit solenoid valve; the propulsion circuit box is connected to the bipropellant thrusters distributed in various directions of the spacecraft through various low-voltage shielded cables, and the propulsion work instructions issued by the aircraft control center are analyzed and the integrated spark plug, the oxygen circuit solenoid valve and the combustion circuit solenoid valve of the corresponding bipropellant thruster are triggered to open / close according to the modulation timing, and the thrust chamber is controlled to complete steady-state and pulse ignition and then output thrust impulse. The present invention simplifies the requirements of the orbit attitude control propulsion system using bipropellant non-self-igniting propellant for engine ignition control, and has the application advantages of light structure weight, high spark energy, low overall energy consumption, long service life, good mechanical environment adaptability, high reliability, etc.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid rocket engines, and in particular to an ignition control system suitable for a distributed orbit and attitude control engine. Background Art

[0002] Driven by the demands for low cost, reuse, and large-scale lunar / Mars development, liquid rocket engines based on combinations of cryogenic propellants such as liquid oxygen / methane, and orbital attitude control propulsion systems, have broad application prospects in the fields of reusable launch vehicles, high-performance space vehicles, planetary ascent / descent, and planetary surface flybys due to their high comprehensive performance (specific impulse performance, reuse performance, operability and maintainability, and in-situ resource production, etc.).

[0003] However, unlike conventional self-igniting or catalytic decomposition engines using nitrogen tetroxide / hydrazine propellant combinations, engines using cryogenic propellant combinations such as liquid oxygen / methane require a special ignition system to operate the engine, so a reliable ignition control system has become the core key to the operation of a two-component non-self-igniting engine. Especially for space propulsion systems with more than a dozen or even dozens of orbit and attitude control engines, each engine requires an ignition system to achieve tens of thousands of pulse ignitions, and orbit and attitude control engines are often scattered in various positions of the aircraft, and the service life of several months or years and other special needs have put forward higher requirements for the engine ignition control system. Summary of the invention

[0004] In view of the defects in the prior art, an object of the present invention is to provide an ignition control system suitable for a distributed orbit attitude control engine.

[0005] The ignition control system for a distributed orbit attitude control engine provided by the present invention comprises: a propulsion circuit box, a low-voltage shielded cable and a bipropellant thruster;

[0006] The propulsion circuit box includes a command parsing & triggering module, a timing modulation module, a control gate circuit module, a spark plug pushing module, an oxygen valve constant current modulation module, a combustion valve constant current modulation module, a noise suppression module, a voltage regulation module, an oscillator and a control data acquisition and storage module;

[0007] The instruction parsing & triggering module is respectively connected to the timing modulation module and the voltage regulation module; the timing modulation module, the spark plug pushing module, the oxygen valve constant current modulation module, the combustion valve constant current modulation module and the oscillator are respectively connected to the control gate circuit module; the voltage regulation module is respectively connected to the noise suppression module, the oscillator and the control data acquisition and storage module; the control data acquisition and storage module is also respectively connected to the control gate circuit module, the spark plug pushing module and the combustion valve constant current modulation module;

[0008] The bipropellant thruster comprises a thrust chamber, an integrated spark plug, an oxygen circuit solenoid valve and a combustion circuit solenoid valve;

[0009] The propulsion circuit box is connected to the bipropellant thrusters distributed in various directions of the spacecraft through the low-voltage shielded cable, parses the propulsion work instructions issued by the aircraft control center and triggers the integrated spark plugs, oxygen circuit solenoid valves and combustion circuit solenoid valves of the corresponding bipropellant thrusters to open / close according to the modulation timing, controls the thrust chamber to complete steady-state and pulse ignition, and then outputs thrust impulse.

[0010] The instruction parsing & triggering module is powered by the voltage regulating module, receives the digital signal instruction issued by the aircraft control center, determines the triggering timing, working mode and working duration information of each bipropellant thruster through internal calculation, and then triggers the corresponding timing modulation module to work;

[0011] The timing modulation module receives the thruster working information sent by the instruction parsing & triggering module, completes the PLC programming of the on / off time of the integrated spark plug, oxygen circuit solenoid valve and combustion circuit solenoid valve of the corresponding thruster, and drives the control gate circuit module to work;

[0012] The control gate circuit module includes a spark plug control gate, an oxygen valve control gate and a combustion valve control gate, and controls the on / off of the spark plug pulse control current, the oxygen valve current and the combustion valve current respectively according to the PLC instruction issued by the timing modulation module based on the CMOS analog switch principle, thereby controlling the operation of the integrated spark plug, the oxygen circuit solenoid valve and the combustion circuit solenoid valve;

[0013] The spark plug push module is constructed based on the ignition coil dedicated power triode V3040s, and the oscillator provides a pulse control current through the spark plug control gate to convert the power supply of the voltage regulation module into the ignition coil pulse push current;

[0014] The oscillator is constructed by a time base circuit, which converts the power supply of the voltage regulation module into a spark plug pulse control current with a pulse frequency of 200Hz / pulse width of 2ms;

[0015] The oxygen valve constant current modulation module and the fuel valve constant current modulation module respectively control the oxygen circuit solenoid valve loop current and the fuel circuit solenoid valve loop current within ±5% of the rated working current, thereby suppressing the valve working current exceeding the limit caused by the large change in the valve coil winding due to the large change in the working temperature of the bipropellant thruster;

[0016] The noise suppression module is constructed by common mode inductors and capacitors to suppress noise from the aircraft power supply line;

[0017] The voltage regulation module has multi-channel voltage regulation and voltage stabilization functions to provide the required power supply voltage to each module;

[0018] The control data acquisition and storage module acquires the real-time working current signals of the integrated spark plugs, oxygen circuit solenoid valves and combustion circuit solenoid valves of each of the bipropellant thrusters and the temperature sensor signals embedded in the propulsion circuit box, converts them into digital signals for storage, and provides them to the aircraft's health monitoring and fault diagnosis system.

[0019] Preferably, the low-voltage shielded cable contains an ignition coil with a shielding layer to push the current transmission core, an oxygen valve current transmission core and a combustion valve current transmission core. The cable shielding layer is well connected with the metal shell of the propulsion circuit box and the metal shell of the integrated spark plug. The core and the inner / outer double shielding layer design of the cable is adopted to effectively isolate the electromagnetic interference between the cores and between the cable and the external environment.

[0020] Preferably, the bipropellant thruster controls the supply / cutoff of the oxidant through the oxygen circuit solenoid valve, controls the supply / cutoff of the fuel through the combustion circuit solenoid valve, converts the ignition coil pulse driving current transmitted through the low-voltage shielded cable into a pulse excitation voltage of 20,000 volts through the integrated spark plug, breaks down the oxidant in the thrust chamber to form a high-temperature ignition plasma flow, induces the mixed combustion of the oxidant and the fuel, and then generates jet thrust.

[0021] Preferably, the integrated spark plug includes an integrated metal shell, an iron core, a low-voltage primary coil, a high-voltage secondary coil, a spring pressure plate, a center electrode, a customized ceramic part and a metal cover plate. The low-voltage primary coil and the high-voltage secondary coil adopt a closed magnetic circuit coil structure with high inductance efficiency and small structural size, and rare earth permanent magnets are added to the iron core magnetic circuit to make the iron core biased, so as to make full use of the hysteresis loop curve to achieve the maximum magnetic field change rate, thereby achieving the maximum coil induced voltage. The central electrode, the customized ceramic part and the integrated metal shell are fixed together by mechanical connection, and low-temperature inorganic glue is coated in the gap between the three, and they are formed into a whole after high-temperature curing; the spring pressing plate is customized from metal with good electrical conductivity, connecting the high-voltage secondary coil and the central electrode to transmit a high-voltage pulse current of 20,000 volts, and the elastic elasticity of the spring pressing plate is used to improve the connection reliability under various harsh mechanical environments during the flight of the launch vehicle; the metal cover plate is installed after the high-voltage secondary coil, spring pressing plate and central electrode are assembled and fixed, and low-temperature inorganic glue is vacuum-filled inside the integrated metal shell, and the integrated spark plug is made into a whole after high-temperature curing. The integrated metal shell is customized with a flange interface or a threaded interface as required to be installed and fixed with the thrust chamber, and a minimum discharge gap is formed between the central electrode and the wall of the thrust chamber. The specifications of the central electrode are customized according to the specific structural size of the bipropellant engine, thereby ensuring that the spark breakdown position is always located inside the thrust chamber.

[0022] Preferably, the propulsion circuit box adopts a fully sealed aluminum alloy shell to achieve electromagnetic shielding, a heat sink is installed on the internal power element and it is close to the aluminum alloy shell to enhance the heat dissipation capacity, and epoxy resin glue is vacuum-filled and cured at high temperature to improve internal insulation and mechanical environment adaptability.

[0023] Preferably, the oscillator adjusts the pulse frequency and pulse width of the spark plug pulse control current according to different spark discharge frequencies and spark energy requirements of the integrated spark plug.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] (1) The ignition control system uses a propulsion circuit box to receive and analyze the instructions from the spacecraft control center, and simultaneously control the bipropellant thrusters distributed in all directions of the spacecraft to perform steady-state and pulse ignition operations. Multiple thrusters can be triggered independently or simultaneously, which greatly simplifies the requirements for engine ignition control of the trajectory and attitude control propulsion system using bipropellant non-hypergolic propellants;

[0026] (2) The integrated spark plug integrates high / low voltage ignition coils and discharge electrodes into an integrated design and is independently packaged. The spark plug is vacuum-filled with inorganic glue and cured at high temperature, which not only improves the airtightness and mechanical environmental adaptability of the integrated spark plug, but also eliminates the high-voltage glow discharge phenomenon inside the spark plug. At the same time, the ignition control system can transmit the ignition excitation voltage through a low-voltage shielded cable, avoiding the corona discharge problem of using traditional high-voltage transmission cables in a rarefied gas environment, which is beneficial to the cable assembly layout of the space propulsion system and improves the safety of the propulsion system in flight applications;

[0027] (3) The propulsion circuit box, low-voltage shielded cable and integrated spark plug all adopt reliable metal shielding measures, which effectively reduces the electromagnetic radiation interference of the orbit attitude control engine ignition process on the propulsion system and spacecraft;

[0028] (4) The ignition control system has the advantages of light structure, high spark energy, low overall energy consumption, long service life, good mechanical environment adaptability and high reliability;

[0029] (5) The present invention is applicable to various space orbit attitude control propulsion systems using bicomponent non-hypergolic propellant combinations such as liquid oxygen / methane, liquid oxygen / alcohol, liquid oxygen / kerosene, and liquid oxygen / liquid hydrogen, including launch vehicles, high-performance upper stages, orbit transfer vehicles, satellites, extraterrestrial planet / small celestial body exploration vehicles, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0031] Figure 1 A schematic diagram of the principle of an ignition control system applicable to a distributed orbit attitude control engine provided by the present invention;

[0032] Figure 2 A schematic diagram of the structure of the integrated spark plug provided by the present invention;

[0033] In the figure: 1-propulsion circuit box; 2-low-voltage shielded cable; 3-bicomponent thruster; 11-command analysis & trigger module; 12-timing modulation module; 13-control gate circuit module; 14-spark plug push module; 15-oxygen valve constant current modulation module; 16-fuel valve constant current modulation module; 17-noise suppression module; 18-voltage regulation module; 19-oscillator; 20-control data acquisition and storage module; 31-thrust chamber; 32-integrated spark plug; 33-oxygen circuit solenoid valve; 34-fuel circuit solenoid valve; 131-spark plug control door; 132-oxygen valve control door; 133-fuel valve control door; 321-integrated metal shell; 322-iron core; 323-low-voltage primary coil; 324-high-voltage secondary coil; 325-spring pressure plate; 326-center electrode; 327-customized ceramic parts; 328-metal cover plate. DETAILED DESCRIPTION

[0034] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0035] Example:

[0036] like Figure 1 As shown, the ignition control system for a distributed orbit attitude control engine provided by the present invention comprises a propulsion circuit box 1, a low-voltage shielded cable 2 and a bipropellant thruster 3;

[0037] The propulsion circuit box 1 includes a command parsing & triggering module 11, a timing modulation module 12, a control gate circuit module 13, a spark plug pushing module 14, an oxygen valve constant current modulation module 15, a combustion valve constant current modulation module 16, a noise suppression module 17, a voltage regulation module 18, an oscillator 19 and a control data acquisition and storage module 20;

[0038] The bipropellant thruster 3 comprises a thrust chamber 31, an integrated spark plug 32, an oxygen circuit solenoid valve 33 and a combustion circuit solenoid valve 34; the propulsion circuit box 1 is connected to the bipropellant thrusters 3 distributed in various directions of the spacecraft through the low-voltage shielded cable 2, parses the propulsion work instructions issued by the aircraft control center and triggers the corresponding integrated spark plug 32, oxygen circuit solenoid valve 33 and combustion circuit solenoid valve 34 of the bipropellant thruster 3 to open / close according to the modulation timing, controls the thrust chamber 31 to complete steady-state and pulse ignition, and then outputs thrust impulse.

[0039] The instruction parsing & triggering module 11 is powered by the voltage regulating module 18, receives the digital signal instructions issued by the aircraft control center, determines the triggering timing, working mode (steady state or pulse) and working duration of each of the bicomponent thrusters 3 through internal calculations, and then triggers the corresponding timing modulation module 12 to work.

[0040] The timing modulation module 12 receives the thruster working information sent by the instruction analysis & triggering module 11, completes the PLC programming of the opening / closing time of the integrated spark plug 32, the oxygen circuit solenoid valve 33 and the combustion circuit solenoid valve 34 of the corresponding thruster, and drives the control gate circuit module 13 to work.

[0041] The control gate circuit module 13 includes a spark plug control gate 131, an oxygen valve control gate 132 and a fuel valve control gate 133. Based on the CMOS analog switch principle, the control gate module 13 controls the on / off of the spark plug pulse control current, the oxygen valve current and the fuel valve current according to the PLC instructions issued by the timing modulation module 12, thereby controlling the operation of the integrated spark plug 32, the oxygen circuit solenoid valve 33 and the fuel circuit solenoid valve 34.

[0042] The spark plug push module 14 is constructed based on the ignition coil dedicated power triode V3040s. The oscillator 19 provides a pulse control current through the spark plug control gate 131, and converts the power supplied by the voltage regulating module 18 into an ignition coil pulse push current. It has the characteristics of large push current, small voltage drop and high reliability.

[0043] The oscillator 19 is constructed by a time base circuit (preferably NE555), which converts the power supplied by the voltage regulating module 18 into a spark plug pulse control current with a pulse frequency of 200Hz / pulse width of 2ms (adjustable) to meet the ignition coil driving requirements of the integrated spark plug 32, and has the characteristics of high precision, simple and reliable circuit.

[0044] The oxygen valve constant current modulation module 15 and the fuel valve constant current modulation module 16 can respectively control the loop current of the oxygen circuit solenoid valve 33 and the loop current of the fuel circuit solenoid valve 34 within ±5% of the rated working current, effectively suppressing the valve working current exceeding the limit caused by the large change of the valve coil winding due to the large change of the working temperature of the bipropellant thruster 3.

[0045] The noise suppression module 17 is constructed by common mode inductors and capacitors, etc., which effectively suppresses noise from the aircraft power supply line and improves the overall anti-interference ability of the propulsion circuit box 1.

[0046] The voltage regulating module 18 has multi-channel voltage regulating and stabilizing functions, and provides the required power supply voltage to the instruction parsing & triggering module 11, the oscillator 19, the spark plug pushing module 14, the oxygen circuit solenoid valve 33 and the combustion circuit solenoid valve 34, etc.

[0047] The control data acquisition and storage module 20 collects the real-time working current signals of the integrated spark plugs 32, oxygen circuit solenoid valves 33 and combustion circuit solenoid valves 34 of each of the bipropellant thrusters 3 and the temperature sensor signals embedded in the propulsion circuit box 1, converts them into digital signals for storage, and provides them to the aircraft's health monitoring and fault diagnosis system.

[0048] The low-voltage shielded cable 2 contains an ignition coil driving current transmission core, an oxygen valve current transmission core and a combustion valve current transmission core with a shielding layer. The cable shielding layer is well connected with the metal shell of the propulsion circuit box 1 and the metal shell of the integrated spark plug 32. The core and cable inner / outer double shielding layer design is adopted to effectively isolate the electromagnetic interference between the cores and between the cable and the external environment.

[0049] The bipropellant thruster 3 controls the supply / cutoff of the oxidant through the oxygen circuit solenoid valve 33, controls the supply / cutoff of the fuel through the combustion circuit solenoid valve 34, and converts the ignition coil pulse driving current (low voltage) transmitted through the low-voltage shielded cable 2 into a pulse excitation voltage of about 20,000 volts through the integrated spark plug 32, breaks down the oxidant in the thrust chamber 31 to form a high-temperature ignition plasma flow, induces the mixed combustion of the oxidant and the fuel, and then generates jet thrust.

[0050] Figure 2 Schematic diagram of the structure of the integrated spark plug 32 provided by the present invention. Figure 2 As shown, the integrated spark plug 32 includes an integrated metal shell 321, an iron core 322, a low-voltage primary coil 323, a high-voltage secondary coil 324, a spring pressure plate 325, a center electrode 326, a customized ceramic part 327 and a metal cover plate 328. The low-voltage primary coil 323 and the high-voltage secondary coil 324 adopt a closed magnetic circuit coil structure with high inductance efficiency and small structural size, and rare earth permanent magnets are added to the magnetic circuit of the iron core 322 to bias the iron core 322 to fully utilize the hysteresis loop curve to achieve the maximum magnetic field change rate, thereby achieving the maximum coil induced voltage, and having the characteristics of small coil volume and large output energy.

[0051] The central electrode 326, the customized ceramic part 327 and the integrated metal shell 321 are fixed together through mechanical connection, and low-temperature inorganic glue is coated in the gaps between the three. After high-temperature curing, they form a whole, thereby improving the airtightness of the mechanical connection.

[0052] The spring pressing piece 325 is customized from a metal with good electrical conductivity, and connects the high-voltage secondary coil 324 and the central electrode 326 to transmit a high-voltage pulse current of about 20,000 volts. The elasticity of the spring pressing piece 325 is utilized to improve the connection reliability in various harsh mechanical environments during the flight of the launch vehicle.

[0053] After the high-voltage secondary coil 324, spring pressure piece 325 and center electrode 326 are assembled and fixed, the metal cover plate 328 is installed, and low-temperature inorganic glue is vacuum-filled inside the integrated metal shell 321. After high-temperature curing, the integrated spark plug 32 becomes a whole, which further enhances the airtightness of the integrated spark plug 32, improves the overall mechanical environment adaptability, and eliminates the high-voltage line corona discharge problem due to the absence of residual air inside. At the same time, the integrated metal shell 321 and the metal cover plate 328 constitute a reliable shielding layer, which effectively suppresses the electromagnetic interference of the integrated spark plug 32 to the external environment.

[0054] The integrated metal shell 321 can be customized with a flange interface or a threaded interface as needed to be installed and fixed to the thrust chamber 31. A minimum discharge gap is formed between the center electrode 326 and the wall of the thrust chamber 31. The specifications of the center electrode 326 can be customized according to the specific structural dimensions of the bipropellant engine 3, thereby ensuring that the spark breakdown position is always located inside the thrust chamber 31.

[0055] The propulsion circuit box 1 adopts a fully sealed aluminum alloy shell to achieve electromagnetic shielding, and a heat sink is installed on the internal power components and is close to the aluminum alloy shell to enhance the heat dissipation capacity. The epoxy resin glue is vacuum-filled and cured at high temperature to improve the internal insulation and mechanical environment adaptability.

[0056] The oscillator 19 can adjust the pulse frequency and pulse width of the spark plug pulse control current according to different requirements of the integrated spark plug 32 such as the spark discharge frequency and spark energy.

[0057] The center electrode 326 is made of high-temperature alloy material to increase its service life in the high-temperature ignition and combustion environment in the thrust chamber 31 .

[0058] The working principle of the ignition control system applicable to the distributed orbit attitude control engine provided by the present invention is as follows:

[0059] The propulsion circuit box 1 is connected to the aircraft power supply, and the DC voltage is transmitted to the voltage regulation module 18 after filtering the power supply noise through the noise suppression module 17. After the voltage regulation module 18 performs voltage transformation and voltage stabilization, different DC voltages are provided to the instruction analysis & triggering module 11, the oscillator 19, the spark plug driving module 14, etc.

[0060] The propulsion circuit box 1 receives propulsion work instructions (such as acceleration, deceleration, pitch, yaw, etc. and their numerical information) issued by the aircraft control center, and is parsed by the instruction parsing & triggering module 11 to determine the extension number, extension number, working mode, working time, etc. of the bipropellant thruster 3 that needs to be triggered, and triggers the timing modulation module 12 corresponding to the corresponding extension. The timing modulation module 12 customizes the corresponding on / off work program of the bipropellant thruster 3 through PLC programming, and then controls the integrated spark plug 32, the oxygen circuit solenoid valve 33 and the combustion circuit solenoid valve 34 to perform on / off work according to the modulation program through the control gate circuit module 13, thereby controlling the thrust chamber 31 to complete the steady-state and pulse ignition output thrust impulse.

[0061] The spark plug push module 14 converts the power supplied by the voltage regulating module 18 into an ignition coil pulse push current based on the spark plug pulse control signal (frequency, pulse width) generated by the oscillator 19, and transmits it to the low-voltage primary coil 323 of the integrated spark plug 32 via the low-voltage shielded cable 2. A pulse voltage of about 20,000 volts is generated in the high-voltage secondary coil 324 through electromagnetic induction, which is conducted through the spring pressing plate 325 and the center electrode 326, and finally breaks down at the minimum discharge gap between the center electrode 326 and the wall of the thrust chamber 31 to form an electric spark.

[0062] The ignition control system provided by the present invention and applicable to the distributed orbit attitude control engine has the following advantages:

[0063] 1) The ignition control system uses a propulsion circuit box 1 to receive and analyze the instructions of the aircraft control center, and at the same time controls the bipropellant thrusters 3 distributed in various positions of the aircraft to perform steady-state and pulse ignition operations. Multiple thrusters can be triggered independently or simultaneously, which greatly simplifies the requirements for engine ignition control of the trajectory attitude control propulsion system using bipropellant non-hypergolic propellant.

[0064] 2) The integrated spark plug 32 integrates the high / low voltage ignition coil and discharge electrode into an integrated design and is independently packaged. The spark plug is vacuum-filled with inorganic glue and cured at high temperature, which not only improves the airtightness and mechanical environmental adaptability of the integrated spark plug 32, but also eliminates the high-voltage glow discharge phenomenon inside the spark plug. At the same time, the ignition control system can transmit the ignition excitation voltage through the low-voltage shielded cable 2, avoiding the corona discharge problem of using traditional high-voltage transmission cables in a rarefied gas environment, which is beneficial to the cable assembly layout of the space propulsion system and improves the safety of the propulsion system in flight applications.

[0065] 3) The propulsion circuit box 1, the low-voltage shielded cable 2 and the integrated spark plug 32 all adopt reliable metal shielding measures, which effectively reduce the electromagnetic radiation interference of the orbit attitude control engine ignition process on the propulsion system and the spacecraft.

[0066] 4) The ignition control system has the advantages of light structure, high spark energy, low overall energy consumption, long service life, good adaptability to mechanical environment and high reliability.

[0067] The present invention is applicable to various space orbit attitude control propulsion systems using bicomponent non-hypergolic propellant combinations such as liquid oxygen / methane, liquid oxygen / alcohol, liquid oxygen / kerosene, and liquid oxygen / liquid hydrogen, including launch vehicles, high-performance upper stages, orbit transfer vehicles, satellites, extraterrestrial planet / small celestial body exploration vehicles, etc.

[0068] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0069] Those skilled in the art know that, in addition to implementing the system, device and its various modules provided by the present invention in a purely computer-readable program code, it is entirely possible to implement the same program in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers and embedded microcontrollers by logically programming the method steps. Therefore, the system, device and its various modules provided by the present invention can be considered as a hardware component, and the modules included therein for implementing various programs can also be considered as structures within the hardware component; the modules for implementing various functions can also be considered as both software programs for implementing the method and structures within the hardware component.

[0070] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An ignition control system suitable for a distributed orbit attitude control engine, characterized in that: include: A propulsion circuit box (1), a low-voltage shielded cable (2) and a bipropellant thruster (3); The propulsion circuit box (1) comprises a command parsing & triggering module (11), a timing modulation module (12), a control gate circuit module (13), a spark plug pushing module (14), an oxygen valve constant current modulation module (15), a combustion valve constant current modulation module (16), a noise suppression module (17), a voltage regulation module (18), an oscillator (19) and a control data acquisition and storage module (20); The bipropellant thruster (3) comprises a thrust chamber (31), an integrated spark plug (32), an oxygen circuit solenoid valve (33) and a combustion circuit solenoid valve (34); The propulsion circuit box (1) is connected to the bipropellant thrusters (3) distributed in all directions of the spacecraft via the low-voltage shielded cable (2), analyzes the propulsion work instructions issued by the spacecraft control center and triggers the integrated spark plugs (32), oxygen circuit solenoid valves (33) and combustion circuit solenoid valves (34) of the corresponding bipropellant thrusters (3) to open / close according to the modulation timing, controls the thrust chamber (31) to complete steady-state and pulse ignition, and outputs thrust impulse; The instruction parsing & triggering module (11) is powered by the voltage regulating module (18), receives the digital signal instruction issued by the aircraft control center, determines the triggering timing, working mode and working duration information of each bipropellant thruster (3) through internal calculation, and then triggers the corresponding timing modulation module (12) to work; The timing modulation module (12) receives the thruster operation information sent by the instruction analysis & triggering module (11), completes the PLC programming of the on / off time of the integrated spark plug (32), the oxygen circuit solenoid valve (33) and the combustion circuit solenoid valve (34) of the corresponding thruster, and drives the control gate circuit module (13) to work; The control gate circuit module (13) comprises a spark plug control gate (131), an oxygen valve control gate (132) and a combustion valve control gate (133), and controls the on / off of the spark plug pulse control current, the oxygen valve current and the combustion valve current respectively according to the PLC instruction issued by the timing modulation module (12) based on the CMOS analog switch principle, thereby controlling the operation of the integrated spark plug (32), the oxygen circuit solenoid valve (33) and the combustion circuit solenoid valve (34); The spark plug driving module (14) is constructed based on a power three-stage tube V3040s dedicated to the ignition coil, and the oscillator (19) provides a pulse control current through the spark plug control gate (131), and converts the power supplied by the voltage regulating module (18) into an ignition coil pulse driving current; The oscillator (19) is constructed by a time base circuit, which converts the power supply of the voltage regulation module (18) into a spark plug pulse control current with a pulse frequency of 200 Hz / pulse width of 2 ms; The oxygen valve constant current modulation module (15) and the fuel valve constant current modulation module (16) respectively control the loop current of the oxygen circuit electromagnetic valve (33) and the loop current of the fuel circuit electromagnetic valve (34) within ±5% of the rated working current, thereby suppressing the valve working current exceeding the limit caused by the large change of the valve coil winding due to the large change of the working temperature of the bipropellant thruster (3); The noise suppression module (17) is constructed by common mode inductors and capacitors to suppress noise from the aircraft power supply line; The voltage regulating module (18) has multi-channel voltage regulating and voltage stabilizing functions, and provides the required power supply voltage to each module; The control data acquisition and storage module (20) acquires real-time working current signals of the integrated spark plugs (32), oxygen circuit solenoid valves (33) and combustion circuit solenoid valves (34) of each of the bipropellant thrusters (3) and the temperature sensor signals embedded in the propulsion circuit box (1), converts them into digital signals for storage, and provides them to the aircraft's health monitoring and fault diagnosis system.

2. The ignition control system for a distributed orbit attitude control engine according to claim 1, characterized in that: The low-voltage shielded cable (2) contains an ignition coil driving current transmission core with a shielding layer, an oxygen valve current transmission core and a combustion valve current transmission core. The cable shielding layer is well connected with the metal shell of the propulsion circuit box (1) and the metal shell of the integrated spark plug (32). The design of the inner / outer double shielding layer of the core and the cable effectively isolates the electromagnetic interference between the cores and between the cable and the external environment.

3. The ignition control system for a distributed orbit attitude control engine according to claim 1, characterized in that: The bipropellant thruster (3) controls the supply / cutoff of the oxidant through the oxygen circuit solenoid valve (33), controls the supply / cutoff of the fuel through the combustion circuit solenoid valve (34), converts the ignition coil pulse driving current transmitted through the low-voltage shielded cable (2) into a pulse excitation voltage of 20,000 volts through the integrated spark plug (32), breaks down the oxidant in the thrust chamber (31) to form a high-temperature ignition plasma flow, induces the oxidant and fuel to mix and burn, and then generates jet thrust.

4. The ignition control system for a distributed orbit attitude control engine according to claim 1, characterized in that: The integrated spark plug (32) comprises an integrated metal shell (321), an iron core (322), a low-voltage primary coil (323), a high-voltage secondary coil (324), a spring pressing piece (325), a center electrode (326), a customized ceramic part (327) and a metal cover plate (328); The integrated metal shell (321) is installed and fixed to the thrust chamber (31) by customizing a flange interface or a threaded interface as required; The low-voltage primary coil (323) and the high-voltage secondary coil (324) adopt a closed magnetic circuit coil structure, and rare earth permanent magnets are added to the magnetic circuit of the iron core (322) so that the iron core (322) is biased, so as to fully utilize the hysteresis loop curve to achieve the maximum magnetic field change rate, thereby achieving the maximum coil induced voltage; The central electrode (326), the customized ceramic part (327) and the integrated metal shell (321) are fixed together by mechanical connection, and a low-temperature inorganic glue is applied to the gap between the three, and they are cured at high temperature to form a whole; After the high-voltage secondary coil (324), the spring pressing sheet (325) and the center electrode (326) are assembled and fixed, the metal cover plate (328) is installed, and low-temperature inorganic glue is vacuum-filled inside the integrated metal shell (321), and after high-temperature curing, the integrated spark plug (32) becomes a whole; The spring pressing piece (325) is made of a metal with good electrical conductivity, and is connected to the high-voltage secondary coil (324) and the central electrode (326) to transmit a high-voltage pulse current of 20,000 volts. The elasticity of the spring pressing piece (325) is used to improve the connection reliability in various harsh mechanical environments during the flight of the carrier rocket. A minimum discharge gap is formed between the central electrode (326) and the wall surface of the thrust chamber (31), and the specifications of the central electrode (326) are customized according to the specific structural dimensions of the bipropellant engine, thereby ensuring that the spark breakdown position is always located inside the thrust chamber (31).

5. The ignition control system for a distributed orbit attitude control engine according to claim 1, characterized in that: The propulsion circuit box (1) adopts a fully sealed aluminum alloy shell to achieve electromagnetic shielding, a heat sink is installed on the internal power element and is closely attached to the aluminum alloy shell to enhance the heat dissipation capability, and epoxy resin glue is vacuum-filled and cured at high temperature to improve internal insulation and mechanical environment adaptability.

6. The ignition control system for a distributed orbit attitude control engine according to claim 1, characterized in that: The oscillator (19) adjusts the pulse frequency and pulse width of the spark plug pulse control current according to the different spark discharge frequencies and spark energy requirements of the integrated spark plug (32).

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