Solid rocket engine safety and ignition control method, device and equipment

Abstract

The invention relates to a solid rocket engine safety and ignition control method, device and equipment. The method comprises the steps that whether three insurance signals are triggered or not is judged, if yes, a high-voltage pulse capacitor is charged within one second, a safety indication signal is output, a differential ignition control electric signal is received, and an ignition signal is output. According to the content of the invention, the high-energy ignition condition is met, the technology maturity degree is improved, the voltage stabilization scheme is simplified, and the requirements of miniaturization, low cost and generalization are met.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rocket engine ignition control, and in particular relates to a solid rocket engine safety and ignition control method, device and equipment. Background Art

[0002] The traditional solid rocket engine ignition device usually achieves safety control through mechanical isolation, which belongs to the staggered safety ignition system. Its ignition element generally adopts a stun-sensing electric ignition tube that meets the 1A / 1W / 5min non-ignition requirements. Since the mechanical structure is easily restricted by volume, mass, production and installation processes, it is difficult to achieve miniaturization and integrated design.

[0003] In recent years, with the continuous development of ignition / detonation technology, the in-line safety ignition system based on pulse power control circuit is considered to be one of the important technical ways to realize the new generation of ignition / detonation system, and has been promoted and applied to ammunition fuze safety system. The in-line safety ignition system is usually composed of electrical connectors, ignition control circuits and impact plate ignition tubes. The detonation conditions of the impact plate ignition tube are very strict, requiring high energy of several thousand volts and several thousand amperes to be excited, and it is inherently safe, so it puts forward higher technical requirements for the ignition control circuit.

[0004] Currently, due to the maturity and implementation cost of related technologies, there are few reports on the application of in-line safety ignition systems in solid rocket engines, and the development of in-line safety and ignition control circuits for solid rocket engines is also relatively slow. In the patent with publication number CN112523899A, a high-voltage pulse power ignition circuit based on a peak-shifting charging mechanism is proposed, which mentions the boost discharge of the main and auxiliary dual capacitors and the capacitor voltage detection scheme involving the processor MCU. This scheme uses an outdated cold cathode tube as a high-voltage switch, requires the use of an additional pulse transformer, and relies on the function of the controller MCU to achieve voltage stabilization. It does not achieve functional decoupling and simplification, and cannot meet the needs of product miniaturization, low cost and generalization in practical applications.

[0005] Therefore, according to the above background technology, the main problems that need to be solved at present include the following aspects: Difficulties in miniaturization and integrated design: Due to the limitation of mechanical structure, it is difficult to realize miniaturization and integrated design of traditional solid rocket engine ignition device. This poses new challenges to the demand for modern solid rocket engines.

[0006] High-energy ignition conditions are difficult to meet: The detonation conditions of the impact piece ignition tube are very strict, requiring high energy of several thousand volts and several thousand amperes to be excited, and it is inherently safe. Therefore, higher technical requirements are placed on the ignition control circuit, and it is necessary to design an ignition circuit that can provide high energy and fast response.

[0007] Technology maturity and implementation cost limitations: Due to the maturity and implementation cost of related technologies, there are few reports on the application of in-line safety ignition systems in solid rocket engines. The current technical solutions have not yet fully met the needs in practical applications.

[0008] The voltage stabilization control scheme is not simplified enough: In the prior art, the voltage stabilization control scheme often relies on the functional implementation of the controller MCU, such as the scheme mentioned in patent CN112523899A. This method fails to achieve functional decoupling and simplification, increasing the complexity and cost of implementation.

[0009] Poor performance of high-voltage switch components: The cold cathode tube used in the existing technology as a high-voltage switch has poor performance and requires the use of an additional pulse transformer, which not only increases the complexity of the system but also affects the improvement of overall performance.

[0010] Unable to meet the requirements of miniaturization, low cost and universality: Existing solutions are difficult to meet the requirements of practical applications in terms of miniaturization, low cost and universality. New technologies and designs need to be developed to meet these requirements. Summary of the invention

[0011] In view of this, the present application proposes a solid rocket engine safety and ignition control method, device and equipment.

[0012] According to one aspect of the present application, a solid rocket engine safety and ignition control method is proposed, characterized in that it includes:

[0013] Step S1: determine whether the insurance signal has a modulation signal, if yes, release the insurance, if no, wait for the modulation signal to be connected, the step S1 also includes:

[0014] Step S1001: obtaining a first insurance signal and / or a second insurance signal and / or a third insurance signal, wherein the first insurance signal is a power positive pole connection signal, the second insurance signal is a power negative pole connection signal, and the third insurance signal is a pulse width modulation signal;

[0015] Step S1002: determining whether the first safety signal, the second safety signal, and the third safety signal are all connected, if so, executing step S2, otherwise continuing to execute step S1;

[0016] Step S2: within 1 second, the voltage across a high-voltage pulse capacitor with a capacity of 0.24 microfarad is increased to a first high-voltage range, wherein the first high-voltage range is 1200 to 1300 volts, and the high-voltage pulse capacitor is controlled by a voltage or current negative feedback voltage stabilization method;

[0017] Step S3: outputting a safety indication signal externally, wherein the safety indication signal includes: an analog voltage signal of 0 to 3 volts and / or an open-drain output signal reflecting whether the first high voltage in step S2 is successfully established;

[0018] Step S4: receiving a differential ignition control electrical signal, and when the differential ignition control electrical signal is received, controlling the polysilicon doped silicon (MCT) to be turned on, releasing the impact energy within no more than 800 nanoseconds, and then igniting the engine.

[0019] In a possible implementation, the pulse width modulation signal frequency ranges from 20 to 60 kHz, and the positive duty cycle ranges from 10% to 30%.

[0020] In a possible implementation, the pulse width modulation signal is a pulse width modulation signal with a frequency of 33 kHz, a duty cycle of 16.5%, and a voltage amplitude of 3.3 volts.

[0021] According to another aspect of the present application, a solid rocket engine safety and ignition control device is provided, comprising:

[0022] A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the energy storage capacitor is charged and stored through the flyback circuit, and the high-voltage pulse capacitor is boosted to a first high-voltage range, the first insurance signal is a power positive electrode connection signal, the second insurance signal is a power negative electrode connection signal, and the third insurance signal is a pulse width modulation signal, and the first high-voltage range is 1200 to 1300 volts;

[0023] A safety status feedback unit, the safety status feedback unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an output safety indication signal to the outside, the safety indication signal includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established;

[0024] An energy release control unit, which is connected to the boost and energy storage unit through the high-voltage pulse capacitor and is used to generate an ignition signal for the rocket engine, and the ignition signal is used to release the ignition energy of the rocket engine.

[0025] In a possible implementation, the boost and energy storage unit further includes:

[0026] A positive power input port (VIN), used for receiving the first insurance signal;

[0027] A negative input port (GND) for receiving the second insurance signal;

[0028] A pulse width modulation signal input port (PWM), used for receiving the third insurance signal;

[0029] Switch enable signal output port (SW_ENABLE), used to output switch enable signal;

[0030] A flyback circuit, the flyback circuit comprising:

[0031] A positive power input port (VIN) for connecting a primary first terminal of a transformer (a first transformer, L1), a second resistor (R1) and a second capacitor (C2);

[0032] A negative power input port (GND) for the S pin of the transistor (U1), the first resistor (R2) and the anode of the second diode (D1);

[0033] A pulse width modulation signal input port (PWM), used for connecting a third resistor (R3);

[0034] A first transformer (L1), wherein a first terminal of the primary side is connected to a positive input port (VIN) of a power supply, a second terminal of the primary side is connected to a D pin of a transistor (U1), a third terminal of the secondary side is connected to an anode of a first diode (D2), and a fourth terminal of the secondary side is connected to a negative terminal of the high-voltage pulse capacitor (first capacitor, C1);

[0035] A high-voltage pulse capacitor (first capacitor, C1), with a positive terminal connected to the cathode of the first diode (D2) and a negative terminal connected to a high-voltage ground (AGND);

[0036] The second resistor (R1) and the second capacitor (C2) are connected in parallel and are used to connect the positive input port (VIN) of the power supply and the cathode of the second diode (D1);

[0037] A second diode (D1), used to connect the second resistor (R1), the second capacitor (C2) and the S pin of the transistor (U1);

[0038] A transistor (U1), whose pins are marked as D, S, and G, wherein the G terminal is used to connect to the switch enable signal output port (SW_ENABLE), the S terminal is used to connect to the ground (GND), and the D terminal is used to connect to the primary second terminal of the first transformer (L1);

[0039] The first resistor (R2) and the third resistor (R3) are used to connect the pulse width modulation signal input port (PWM), the switch enable signal output port (SW_ENABLE) and the ground (GND).

[0040] In a possible implementation, the security status feedback unit includes:

[0041] A resistor voltage divider circuit, used for dividing the voltage across the high-voltage pulse capacitor (first capacitor, C1), with a voltage division ratio of 120 times, the resistor voltage divider circuit comprising a first resistor (R4) and a second resistor (R5);

[0042] a first comparator, whose positive input terminal is connected to the first reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a switch enable signal (SW_ENABLE) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 1250 volts;

[0043] a second comparator, whose positive input terminal is connected to the second reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a safety feedback state output signal (SEC_FB) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 800 volts;

[0044] A first voltage stabilizing diode (D6), used for providing a first reference voltage, wherein the first reference voltage terminal is connected to a positive electrode of a power supply through the first voltage stabilizing diode (D6);

[0045] The second voltage stabilizing diode (D7) is used to provide a second reference voltage, and the second reference voltage terminal is connected to the positive electrode of the power supply through the second voltage stabilizing diode (D7).

[0046] The first resistor (R4), the second resistor (R5) and the first voltage stabilizing diode (D6) are all made of components with an accuracy error of less than 5%.

[0047] In a possible implementation, the security status feedback unit includes:

[0048] a first capacitor (C5), connected between the resistor voltage divider circuit and the ground (GND), for smoothing the voltage signal;

[0049] An operational amplifier (U3.2), whose inverting input terminal is connected to a connection point of a first resistor (R7), a second resistor (R8) and a first capacitor (C5), and whose non-inverting input terminal is used to output a safety feedback state signal (SEC_FB);

[0050] The operational amplifier (U3.2) is used to provide an accurate analog output signal according to input voltage conditions.

[0051] In a possible implementation, the energy release control unit includes:

[0052] The positive input port of the power supply (VIN) is used to receive the power supply signal;

[0053] Ground (GND), used to receive the negative pole signal of the power supply;

[0054] Logic ground port (DGND), single-point grounding is adopted;

[0055] Rocket engine ignition signal ports (FIRE+ and FIRE-), including: the rocket engine ignition signal port positive signal port (FIRE+) and the rocket engine ignition signal port negative port (FIRE-);

[0056] Polycrystalline silicon doped silicon (MCT, U4), whose pins are marked as D, S, G, GS, respectively, wherein the D terminal is connected to the positive electrode of the high-voltage pulse capacitor (first capacitor, C1), the G terminal is connected to the output terminal of the differential gate driver (U5), the GS terminal is connected to the ground (GND), and the S terminal is connected to the positive electrode of the detonator (LG);

[0057] A differential gate driver (U5) includes five pins, namely: a first pin (VDD) is used for power supply access of the differential gate driver (U5) and is connected to the positive power input port (VIN); a second pin (GND) is used for connecting to the ground (GND); a third pin (IN+) is used for connecting to the positive signal terminal (FIRE+) of the rocket engine ignition signal port; a fourth pin (IN-) is used for connecting to the negative signal terminal (FIRE-) of the rocket engine ignition signal port; and a fifth pin (OUT) is used for outputting a signal connected to the G terminal of the polysilicon doped silicon (MCT, U4);

[0058] A high-voltage pulse capacitor (first capacitor, C1), with its positive electrode connected to the D terminal of the polysilicon-doped silicon (MCT, U4), and its negative electrode connected to the high-voltage ground (AGND);

[0059] A second capacitor (C6), used as a decoupling capacitor of the differential gate driver (U5), connected in parallel between the positive input port (VIN) of the power supply and the ground (GND), and placed close to the first pin (VDD) of the differential gate driver (U5) in the circuit;

[0060] A first resistor (R9), one end of which is connected to the ground (GND), and the other end of which is connected to the fifth pin (OUT) of the differential gate driver (U5);

[0061] The second resistor (R10) is a 0 ohm resistor, one end of which is connected to the logic ground port (DGND) and the other end of which is connected to the ground (GND);

[0062] A first transient voltage suppression diode (D3), comprising three pins, wherein a first pin is connected to a positive signal terminal (FIRE+) of the rocket engine ignition signal port, a second pin is connected to a negative signal terminal (FIRE-) of the rocket engine ignition signal port, and a third pin is connected to the logic ground (DGND);

[0063] A second transient voltage suppression diode (D4), a first pin of which is connected to the G terminal of the polycrystalline silicon doped silicon (MCT, U4), and a second pin of which is connected to the ground (GND);

[0064] a high-speed current transient blocker (D5) having an anode connected to the fifth pin (OUT) of the differential gate driver (U5) and a cathode connected to the ground (GND);

[0065] A detonator (LG), used for performing an ignition action, is connected in series between the negative electrode of the high-voltage pulse capacitor (the first capacitor, C1) and the S terminal of the polycrystalline silicon doped silicon (MCT, U4).

[0066] Wherein, the energy release control unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor (first capacitor, C1) to release the ignition energy of the rocket engine.

[0067] In a possible implementation, the resistors and the voltage-stabilizing diodes used for voltage division in the device are components with an error of less than 5%.

[0068] According to another aspect of the present application, a solid rocket engine safety and ignition control device is provided, comprising:

[0069] A solid rocket engine safety and ignition control device, the solid rocket engine safety and ignition control device comprising:

[0070] A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the flyback circuit charges the energy storage capacitor and stores energy, and boosts the high-voltage pulse capacitor to a first high-voltage range, the first insurance signal is a power positive electrode connection signal, the second insurance signal is a power negative electrode connection signal, and the third insurance signal is a pulse width modulation signal, and the first high-voltage range is 1200 to 1300 volts;

[0071] A safety status feedback unit, the safety status feedback unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an output safety indication signal to the outside, the safety indication signal includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established;

[0072] An energy release control unit, the energy release control unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an ignition signal, and the ignition signal is used to release the ignition energy of the rocket engine;

[0073] An external control interface, used to receive external control signals and transmit them to the solid rocket motor safety and ignition control device;

[0074] A power module, used to provide operating voltage for the solid rocket motor safety and ignition control device;

[0075] The signal processing module is used to process and convert signals from the solid rocket motor safety and ignition control device.

[0076] Based on the relevant technical solutions of the present application, it is suitable for power supply with a 12-18 volt DC power supply, the boost power consumption is less than or equal to 2 watts, the maintenance power consumption is less than or equal to 0.2 watts, the capacitor charging stable value is 1250 volts with a deviation of plus or minus 50 volts, and the ignition ready time is less than or equal to 1 second. At the same time, compared with other technical solutions, it has significant advantages in miniaturization, low cost and versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0077] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments, features, and aspects of the present application and, together with the description, serve to explain the principles of the present application.

[0078] Figure 1 Shown is a flow chart of a solid rocket engine safety and ignition control method according to an embodiment of the present application;

[0079] Figure 2 What is shown is a main structure diagram of a solid rocket engine safety and ignition control device according to an embodiment of the present application;

[0080] Figure 3 Shown is a schematic diagram of the circuit principle of a boost and energy storage unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application;

[0081] Figure 4 What is shown is a circuit principle schematic diagram of a digital logic signal output of a safety state feedback unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application;

[0082] Figure 5 What is shown is a schematic diagram of the circuit principle of the analog voltage signal output of the safety state feedback unit of the solid rocket engine safety and ignition control device according to an embodiment of the present application;

[0083] Figure 6Shown is a schematic diagram of the circuit principle of an energy release control unit of a solid rocket engine safety and ignition control device in an embodiment of the present application. DETAILED DESCRIPTION

[0084] Various exemplary embodiments, features and aspects of the present application will be described in detail below with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0085] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0086] In addition, in order to better illustrate the present disclosure, numerous specific details are provided in the following specific embodiments. It should be understood by those skilled in the art that the present application can also be implemented without certain specific details. In some examples, methods, means, components and circuits well known to those skilled in the art are not described in detail in order to highlight the subject matter of the present application.

[0087] [Method Example]

[0088] Figure 1 The flowchart of a solid rocket engine safety and ignition control method according to an embodiment of the present application is shown. Figure 1 As shown, the method includes:

[0089] Step S1: determine whether the insurance signal has a modulation signal, if yes, release the insurance, if no, wait for the modulation signal to be connected, step S1 also includes:

[0090] Step S1001: obtaining a first insurance signal and / or a second insurance signal and / or a third insurance signal, wherein the first insurance signal is a power positive pole connection signal, the second insurance signal is a power negative pole connection signal, and the third insurance signal is a pulse width modulation signal;

[0091] Step S1002: Determine whether the first safety signal, the second safety signal, and the third safety signal are all connected. If they are connected, execute step S2; if not, continue to execute step S1;

[0092] Step S2: within 1 second, the voltage across a high-voltage pulse capacitor with a capacity of 0.24 microfarad is increased to a first high-voltage range, the first high-voltage range is 1200 to 1300 volts, and the high-voltage pulse capacitor is controlled by a voltage or current negative feedback voltage stabilization method;

[0093] Step S3: Outputting a safety indication signal to the outside, the safety indication signal comprising: an analog voltage signal of 0 to 3 volts and / or an open-drain output signal reflecting whether the first high voltage in step S2 is successfully established;

[0094] Step S4: receiving the differential ignition control electrical signal. When the differential ignition control electrical signal is received, the polycrystalline silicon doped silicon (MCT) is controlled to be turned on, and the impact energy is released within no more than 800 nanoseconds, thereby igniting the engine.

[0095] In another preferred embodiment, the PWM signal frequency ranges from 20 to 60 kHz, and the positive duty cycle ranges from 10% to 30%.

[0096] In another preferred embodiment, the pulse width modulation signal is a pulse width modulation signal with a frequency of 33 kHz, a duty cycle of 16.5%, and a voltage amplitude of 3.3 volts.

[0097] [Device Example]

[0098] Figure 2 The main structure diagram of a solid rocket engine safety and ignition control device according to an embodiment of the present application is shown, and the device includes:

[0099] A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the energy storage capacitor is charged and stored through the flyback circuit, and the high-voltage pulse capacitor is boosted to a first high-voltage range. The first insurance signal is a power positive electrode connection signal, the second insurance signal is a power negative electrode connection signal, and the third insurance signal is a pulse width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0100] A safety status feedback unit, which is connected to the boost and energy storage unit via a high-voltage pulse capacitor, and is used to generate an output safety indication signal, which includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established;

[0101] Energy release control unit, which is connected to the boost and energy storage unit through a high-voltage pulse capacitor and is used to generate an ignition signal for the rocket engine. The ignition signal is used to release the ignition energy of the rocket engine.

[0102] In another preferred embodiment, Figure 3 The figure shows a schematic diagram of the circuit principle of a boost and energy storage unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application. The boost and energy storage unit also includes:

[0103] A positive power input port (VIN), used for receiving a first insurance signal;

[0104] The negative input port of the power supply (GND) is used to receive the second insurance signal;

[0105] A pulse width modulation signal input port (PWM), used for receiving a third insurance signal;

[0106] Switch enable signal output port (SW_ENABLE), used to output switch enable signal;

[0107] Flyback circuit, the flyback circuit includes:

[0108] A positive power input port (VIN) for connecting a primary first terminal of a transformer (a first transformer, L1), a second resistor (R1) and a second capacitor (C2);

[0109] A negative power input port (GND) for the S pin of the transistor (U1), the first resistor (R2) and the anode of the second diode (D1);

[0110] A pulse width modulation signal input port (PWM), used for connecting a third resistor (R3);

[0111] A first transformer (L1), wherein a first terminal of the primary side is connected to a positive input port (VIN) of a power supply, a second terminal of the primary side is connected to a D pin of a transistor (U1), a third terminal of the secondary side is connected to an anode of a first diode (D2), and a fourth terminal of the secondary side is connected to a negative terminal of a high-voltage pulse capacitor (a first capacitor, C1);

[0112] A high-voltage pulse capacitor (first capacitor, C1), with a positive terminal connected to the cathode of the first diode (D2) and a negative terminal connected to a high-voltage ground (AGND);

[0113] The second resistor (R1) and the second capacitor (C2) are connected in parallel and are used to connect the positive input port (VIN) of the power supply and the cathode of the second diode (D1);

[0114] A second diode (D1) is used to connect the second resistor (R1), the second capacitor (C2) and the S pin of the transistor (U1);

[0115] A transistor (U1), whose pins are marked as D, S, and G, wherein the G terminal is used to connect to a switch enable signal output port (SW_ENABLE), the S terminal is used to connect to a ground (GND), and the D terminal is used to connect to a primary second terminal of a first transformer (L1);

[0116] The first resistor (R2) and the third resistor (R3) are used to connect a pulse width modulation signal input port (PWM), a switch enable signal output port (SW_ENABLE) and a ground (GND).

[0117] In another preferred embodiment, Figure 4 The diagram shows a circuit schematic diagram of a safety state feedback unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application. The safety state feedback unit includes:

[0118] A resistor voltage divider circuit, used for dividing the voltage across the high-voltage pulse capacitor (first capacitor, C1), with a voltage division ratio of 120 times, the resistor voltage divider circuit comprising a first resistor (R4) and a second resistor (R5);

[0119] a first comparator, whose positive input terminal is connected to the first reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a switch enable signal (SW_ENABLE) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 1250 volts;

[0120] a second comparator, whose positive input terminal is connected to the second reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a safety feedback state output signal (SEC_FB) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 800 volts;

[0121] A first voltage stabilizing diode (D6), used for providing a first reference voltage, wherein the first reference voltage terminal is connected to the positive electrode of the power supply through the first voltage stabilizing diode (D6);

[0122] The second voltage stabilizing diode (D7) is used to provide a second reference voltage, and the second reference voltage terminal is connected to the positive electrode of the power supply through the second voltage stabilizing diode (D7).

[0123] The first resistor (R4), the second resistor (R5) and the first voltage stabilizing diode (D6) are all made of components with an accuracy error of less than 5%.

[0124] In another preferred embodiment, Figure 5 The circuit schematic diagram of the analog voltage signal output of the safety state feedback unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application is shown. The safety state feedback unit includes:

[0125] A first capacitor (C5), connected between the resistor voltage divider circuit and ground (GND), for smoothing the voltage signal;

[0126] An operational amplifier (U3.2), whose inverting input terminal is connected to a connection point of a first resistor (R7), a second resistor (R8) and a first capacitor (C5), and whose non-inverting input terminal is used to output a safety feedback state signal (SEC_FB);

[0127] Among them, the operational amplifier (U3.2) is used to provide an accurate analog output signal according to the input voltage conditions.

[0128] In another preferred embodiment, Figure 6 The diagram shows a schematic circuit diagram of an energy release control unit of a solid rocket engine safety and ignition control device according to an embodiment of the present application. The energy release control unit includes:

[0129] The positive input port of the power supply (VIN) is used to receive the power supply signal;

[0130] Ground (GND), used to receive the negative pole signal of the power supply;

[0131] Logic ground port (DGND), single-point grounding is adopted;

[0132] Rocket engine ignition signal port (FIRE+ and FIRE-), including: rocket engine ignition signal port positive signal port (FIRE+) and rocket engine ignition signal port negative port (FIRE-);

[0133] Polycrystalline silicon doped silicon (MCT, U4), whose pins are marked as D, S, G, GS, respectively, wherein the D terminal is connected to the positive electrode of the high-voltage pulse capacitor (the first capacitor, C1), the G terminal is connected to the output terminal of the differential gate driver (U5), the GS terminal is connected to the ground (GND), and the S terminal is connected to the positive electrode of the detonator (LG);

[0134] The differential gate driver (U5) includes five pins, namely: the first pin (VDD) is used for the power supply of the differential gate driver (U5) and is connected to the positive power input port (VIN), the second pin (GND) is used to connect to the ground (GND), the third pin (IN+) is used to connect to the positive signal terminal (FIRE+) of the rocket engine ignition signal port, the fourth pin (IN-) is used to connect to the negative signal terminal (FIRE-) of the rocket engine ignition signal port, and the fifth pin (OUT) is used to output the signal and is connected to the G terminal of the polysilicon doped silicon (MCT, U4);

[0135] A high voltage pulse capacitor (first capacitor, C1), with its positive electrode connected to the D terminal of the polysilicon doped silicon (MCT, U4), and its negative electrode connected to the high voltage ground (AGND);

[0136] A second capacitor (C6), used as a decoupling capacitor of the differential gate driver (U5), connected in parallel between the positive input port (VIN) of the power supply and the ground (GND), and placed close to the first pin (VDD) of the differential gate driver (U5) in the circuit;

[0137] A first resistor (R9), one end of which is connected to the ground (GND), and the other end of which is connected to the fifth pin (OUT) of the differential gate driver (U5);

[0138] The second resistor (R10) is a 0 ohm resistor, one end of which is connected to the logic ground port (DGND) and the other end is connected to the ground (GND);

[0139] A first transient voltage suppression diode (D3), comprising three pins, wherein a first pin is connected to a positive signal terminal (FIRE+) of a rocket engine ignition signal port, a second pin is connected to a negative signal terminal (FIRE-) of a rocket engine ignition signal port, and a third pin is connected to a logic ground (DGND);

[0140] a second transient voltage suppression diode (D4), having a first pin connected to the G terminal of the polysilicon doped silicon (MCT, U4), and a second pin connected to the ground (GND);

[0141] a high-speed current transient blocker (D5) having an anode connected to the fifth pin (OUT) of the differential gate driver (U5) and a cathode connected to ground (GND);

[0142] The detonator (LG), used to perform the ignition action, is connected in series between the negative electrode of the high-voltage pulse capacitor (the first capacitor, C1) and the S terminal of the polysilicon doped silicon (MCT, U4).

[0143] Among them, the energy release control unit is connected to the boost and energy storage unit through a high-voltage pulse capacitor (the first capacitor, C1) to release the ignition energy of the rocket engine.

[0144] In another preferred embodiment, the resistors and voltage-stabilizing diodes used for voltage division in the device are components with an error of less than 5%.

[0145] In another preferred embodiment, the polysilicon doped silicon (MCT, U4) is a non-self-triggering type MCT.

[0146] In another preferred embodiment, the polysilicon doped silicon (MCT, U4) is a self-triggering MCT.

[0147] [Equipment Example]

[0148] A solid rocket engine safety and ignition control device, comprising:

[0149] Solid rocket motor safety and ignition control device, solid rocket motor safety and ignition control device includes:

[0150] A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the flyback circuit charges the energy storage capacitor and stores energy, and the high-voltage pulse capacitor is boosted to a first high-voltage range. The first insurance signal is a power supply positive electrode connection signal, the second insurance signal is a power supply negative electrode connection signal, and the third insurance signal is a pulse width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0151] A safety status feedback unit, which is connected to the boost and energy storage unit via a high-voltage pulse capacitor, and is used to generate an output safety indication signal, which includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established;

[0152] An energy release control unit, which is connected to the boost and energy storage unit via a high-voltage pulse capacitor and is used to generate an ignition signal, and the ignition signal is used to release the ignition energy of the rocket engine;

[0153] An external control interface for receiving external control signals and transmitting them to the solid rocket motor safety and ignition control device;

[0154] A power module, used to provide operating voltage for the solid rocket motor safety and ignition control device;

[0155] Signal processing module, used to process and convert signals from solid rocket motor safety and ignition control devices.

[0156] The embodiments of the present disclosure have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A solid rocket engine safety and ignition control method, characterized in that: include: Step S1: determine whether the insurance signal has a modulation signal, if yes, release the insurance, if no, wait for the modulation signal to be connected, the step S1 also includes: Step S1001: obtaining a first insurance signal and / or a second insurance signal and / or a third insurance signal, wherein the first insurance signal is a power positive pole connection signal, the second insurance signal is a power negative pole connection signal, and the third insurance signal is a pulse width modulation signal; Step S1002: determining whether the first safety signal, the second safety signal, and the third safety signal are all connected, if so, executing step S2, otherwise continuing to execute step S1; Step S2: within 1 second, the voltage across a high-voltage pulse capacitor with a capacity of 0.24 microfarad is increased to a first high-voltage range, wherein the first high-voltage range is 1200 to 1300 volts, and the high-voltage pulse capacitor is controlled by a voltage or current negative feedback voltage stabilization method; Step S3: outputting a safety indication signal externally, wherein the safety indication signal includes: an analog voltage signal of 0 to 3 volts and / or an open-drain output signal reflecting whether the first high voltage in step S2 is successfully established; Step S4: receiving a differential ignition control electrical signal, and when the differential ignition control electrical signal is received, controlling the polysilicon doped silicon (MCT) to be turned on, releasing the impact energy within no more than 800 nanoseconds, and then igniting the engine.

2. The method according to claim 1, characterized in that The frequency range of the pulse width modulation signal is 20-60 kHz, and the positive duty cycle range is 10%-30%.

3. The method according to claim 2, characterized in that The pulse width modulation signal is a pulse width modulation signal with a frequency of 33 kHz, a duty cycle of 16.5%, and a voltage amplitude of 3.3 volts.

4. A solid rocket engine safety and ignition control device, characterized in that: include: A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the energy storage capacitor is charged and stored through the flyback circuit, and the high-voltage pulse capacitor is boosted to a first high-voltage range, the first insurance signal is a power positive electrode connection signal, the second insurance signal is a power negative electrode connection signal, and the third insurance signal is a pulse width modulation signal, and the first high-voltage range is 1200 to 1300 volts; A safety status feedback unit, the safety status feedback unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an output safety indication signal to the outside, the safety indication signal includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established; An energy release control unit, which is connected to the boost and energy storage unit through the high-voltage pulse capacitor and is used to generate an ignition signal for the rocket engine, and the ignition signal is used to release the ignition energy of the rocket engine.

5. The device according to claim 4, characterized in that The boost and energy storage unit also includes: A positive power input port (VIN), used for receiving the first insurance signal; A negative input port (GND) for receiving the second insurance signal; A pulse width modulation signal input port (PWM), used for receiving the third insurance signal; Switch enable signal output port (SW_ENABLE), used to output switch enable signal; A flyback circuit, the flyback circuit comprising: A positive power input port (VIN) for connecting a primary first terminal of a transformer (a first transformer, L1), a second resistor (R1) and a second capacitor (C2); A negative power input port (GND) for the S pin of the transistor (U1), the first resistor (R2) and the anode of the second diode (D1); A pulse width modulation signal input port (PWM), used for connecting a third resistor (R3); A first transformer (L1), wherein a first terminal of the primary side is connected to a positive input port (VIN) of a power supply, a second terminal of the primary side is connected to a D pin of a transistor (U1), a third terminal of the secondary side is connected to an anode of a first diode (D2), and a fourth terminal of the secondary side is connected to a negative terminal of the high-voltage pulse capacitor (first capacitor, C1); A high-voltage pulse capacitor (first capacitor, C1), with a positive terminal connected to the cathode of the first diode (D2) and a negative terminal connected to a high-voltage ground (AGND); The second resistor (R1) and the second capacitor (C2) are connected in parallel and are used to connect the positive input port (VIN) of the power supply and the cathode of the second diode (D1); A second diode (D1), used to connect the second resistor (R1), the second capacitor (C2) and the S pin of the transistor (U1); A transistor (U1), whose pins are marked as D, S, and G, wherein the G terminal is used to connect to the switch enable signal output port (SW_ENABLE), the S terminal is used to connect to the ground (GND), and the D terminal is used to connect to the primary second terminal of the first transformer (L1); The first resistor (R2) and the third resistor (R3) are used to connect the pulse width modulation signal input port (PWM), the switch enable signal output port (SW_ENABLE) and the ground (GND).

6. The device according to claims 4-5, characterized in that: The safety status feedback unit comprises: A resistor voltage divider circuit, used for dividing the voltage across the high-voltage pulse capacitor (first capacitor, C1), with a voltage division ratio of 120 times, the resistor voltage divider circuit comprising a first resistor (R4) and a second resistor (R5); a first comparator, whose positive input terminal is connected to the first reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a switch enable signal (SW_ENABLE) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 1250 volts; a second comparator, whose positive input terminal is connected to the second reference voltage terminal and whose negative input terminal is connected to the output terminal of the resistor voltage divider circuit, for generating a safety feedback state output signal (SEC_FB) when the voltage across the high-voltage pulse capacitor (the first capacitor, C1) is higher than 800 volts; A first voltage stabilizing diode (D6), used for providing a first reference voltage, wherein the first reference voltage terminal is connected to a positive electrode of a power supply through the first voltage stabilizing diode (D6); The second voltage stabilizing diode (D7) is used to provide a second reference voltage, and the second reference voltage terminal is connected to the positive electrode of the power supply through the second voltage stabilizing diode (D7). The first resistor (R4), the second resistor (R5) and the first voltage stabilizing diode (D6) are all made of components with an accuracy error of less than 5%.

7. The device according to claims 4-5, characterized in that: The safety status feedback unit comprises: a first capacitor (C5), connected between the resistor voltage divider circuit and the ground (GND), for smoothing the voltage signal; An operational amplifier (U3.2), whose inverting input terminal is connected to a connection point of a first resistor (R7), a second resistor (R8) and a first capacitor (C5), and whose non-inverting input terminal is used to output a safety feedback state signal (SEC_FB); The operational amplifier (U3.2) is used to provide an accurate analog output signal according to input voltage conditions.

8. The device according to claims 4 to 7, characterized in that The energy release control unit comprises: The positive input port of the power supply (VIN) is used to receive the power supply signal; Ground (GND), used to receive the negative pole signal of the power supply; Logic ground port (DGND), single-point grounding is adopted; Rocket engine ignition signal ports (FIRE+ and FIRE-), including: the rocket engine ignition signal port positive signal port (FIRE+) and the rocket engine ignition signal port negative port (FIRE-); Polycrystalline silicon doped silicon (MCT, U4), whose pins are marked as D, S, G, GS, respectively, wherein the D terminal is connected to the positive electrode of the high-voltage pulse capacitor (first capacitor, C1), the G terminal is connected to the output terminal of the differential gate driver (U5), the GS terminal is connected to the ground (GND), and the S terminal is connected to the positive electrode of the detonator (LG); A differential gate driver (U5) includes five pins, namely: a first pin (VDD) is used for power supply access of the differential gate driver (U5) and is connected to the positive power input port (VIN); a second pin (GND) is used for connecting to the ground (GND); a third pin (IN+) is used for connecting to the positive signal terminal (FIRE+) of the rocket engine ignition signal port; a fourth pin (IN-) is used for connecting to the negative signal terminal (FIRE-) of the rocket engine ignition signal port; and a fifth pin (OUT) is used for outputting a signal connected to the G terminal of the polysilicon doped silicon (MCT, U4); A high-voltage pulse capacitor (first capacitor, C1), with its positive electrode connected to the D terminal of the polysilicon-doped silicon (MCT, U4), and its negative electrode connected to the high-voltage ground (AGND); A second capacitor (C6), used as a decoupling capacitor of the differential gate driver (U5), connected in parallel between the positive input port (VIN) of the power supply and the ground (GND), and placed close to the first pin (VDD) of the differential gate driver (U5) in the circuit; A first resistor (R9), one end of which is connected to the ground (GND), and the other end of which is connected between the fifth pin (OUT) of the differential gate driver (U5); The second resistor (R10) is a 0 ohm resistor, one end of which is connected to the logic ground port (DGND) and the other end of which is connected to the ground (GND); A first transient voltage suppression diode (D3), comprising three pins, wherein a first pin is connected to a positive signal terminal (FIRE+) of the rocket engine ignition signal port, a second pin is connected to a negative signal terminal (FIRE-) of the rocket engine ignition signal port, and a third pin is connected to the logic ground (DGND); A second transient voltage suppression diode (D4), a first pin of which is connected to the G terminal of the polycrystalline silicon doped silicon (MCT, U4), and a second pin of which is connected to the ground (GND); a high-speed current transient blocker (D5) having an anode connected to the fifth pin (OUT) of the differential gate driver (U5) and a cathode connected to the ground (GND); A detonator (LG), used for performing an ignition action, is connected in series between the negative electrode of the high-voltage pulse capacitor (the first capacitor, C1) and the S terminal of the polycrystalline silicon doped silicon (MCT, U4). Wherein, the energy release control unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor (first capacitor, C1) to release the ignition energy of the rocket engine.

9. The device according to claims 4 to 8, characterized in that: The resistors and voltage-stabilizing diodes used for voltage division in the device are components with an error of less than 5%.

10. A solid rocket engine safety and ignition control device, characterized in that: include: A solid rocket engine safety and ignition control device, the solid rocket engine safety and ignition control device comprising: A boost and energy storage unit, the boost and energy storage unit includes a flyback circuit and a high-voltage pulse capacitor, and is used to receive a first insurance signal, a second insurance signal, and a third insurance signal. After receiving the insurance signal, the flyback circuit charges the energy storage capacitor and stores energy, and boosts the high-voltage pulse capacitor to a first high-voltage range, the first insurance signal is a power positive electrode connection signal, the second insurance signal is a power negative electrode connection signal, and the third insurance signal is a pulse width modulation signal, and the first high-voltage range is 1200 to 1300 volts; A safety status feedback unit, the safety status feedback unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an output safety indication signal to the outside, the safety indication signal includes an analog voltage signal of 0 to 3 volts and / or an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established; An energy release control unit, the energy release control unit is connected to the boost and energy storage unit through the high-voltage pulse capacitor, and is used to generate an ignition signal, and the ignition signal is used to release the ignition energy of the rocket engine; An external control interface, used to receive external control signals and transmit them to the solid rocket motor safety and ignition control device; A power module, used to provide operating voltage for the solid rocket motor safety and ignition control device; The signal processing module is used to process and convert signals from the solid rocket motor safety and ignition control device.

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