A solid rocket engine safety and ignition control method, device and equipment

Abstract

This application relates to a solid rocket engine safety and ignition control method, apparatus, and device. The method includes determining whether three safety signals have been triggered; if triggered, charging a high-voltage pulse capacitor within one second; outputting a safety indication signal; and receiving a differential ignition control electrical signal and outputting an ignition signal. This application satisfies high-energy ignition requirements, improves technical maturity, simplifies voltage regulation, and meets the requirements of miniaturization, low cost, and universality.

Description

Technical Field

[0001] The present 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] Traditional solid rocket motor ignition systems typically achieve safety control through mechanical isolation, resulting in a staggered safety ignition system. Their ignition element typically utilizes a spurious-sense electric igniter tube that meets the misfire requirement of 1A / 1W / 5 minutes. Due to the mechanical structure's limitations in terms of size, mass, production, and assembly process, miniaturization and integrated design are difficult to achieve.

[0003] In recent years, with the continuous advancement of ignition / initiation technology, inline safety ignition systems based on pulsed power control circuits have been recognized as a key approach to achieving next-generation ignition / initiation systems and have been widely adopted in ammunition fuze safety systems. Inline safety ignition systems typically consist of electrical connectors, ignition control circuitry, and impact plate ignition tubes. The initiation conditions for impact plate ignition tubes are extremely stringent, requiring high energies of several thousand volts and several thousand amperes to activate them and ensure inherent safety. This places high technical demands on the ignition control circuitry.

[0004] Currently, due to the limited maturity and implementation costs 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 application 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 functions of the controller MCU to achieve voltage regulation. It fails to achieve functional decoupling and simplification, and cannot meet the requirements of miniaturization, low cost, and universality in practical applications.

[0005] Therefore, based on the above background technology, the main issues that need to be addressed include the following: Difficulties in miniaturization and integrated design: Due to mechanical structural limitations, traditional solid rocket engine ignition devices are difficult to achieve miniaturization and integrated design. This poses new challenges to the requirements of modern solid rocket engines.

[0006] High-energy ignition conditions are difficult to meet: The initiation conditions for impact-plate ignition tubes are extremely stringent, requiring high energies of several thousand volts and several thousand amperes to ignite and maintain inherent safety. This places high technical demands on the ignition control circuit, requiring a design that can provide high energy and rapid response.

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

[0008] Insufficiently simplified voltage stabilization control schemes: In existing technologies, voltage stabilization control schemes often rely on the functionality of the controller MCU, as described in patent application CN112523899A. This approach fails to achieve functional decoupling and simplification, increasing implementation complexity and cost.

[0009] The performance of high-voltage switching components is poor: The cold-cathode tubes used in existing technologies as high-voltage switches have poor performance and require the use of pulse transformers. This not only increases system complexity but also affects overall performance.

[0010] Unable to meet the requirements of miniaturization, low cost, and universality: Existing solutions cannot meet the requirements of miniaturization, low cost, and universality in practical applications. New technologies and designs are needed 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 motor safety and ignition control method is proposed, characterized by comprising:

[0013] Step S1: Determine whether the safety signal has a modulation signal, if so, release the safety, if not, wait for the modulation signal to be connected, said step S1 also includes:

[0014] Step S1001: obtaining a first safety signal and / or a second safety signal and / or a third safety signal, wherein the first safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety 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 executing step S1;

[0016] Step S2: Raising the voltage across a high-voltage pulse capacitor with a capacity of 0.24 microfarads to within a first high-voltage range of 1200 to 1300 volts within 1 second, wherein the high-voltage pulse capacitor is stabilized by voltage or current negative feedback.

[0017] Step S3: Outputting a safety indication signal, 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. When the differential ignition control electrical signal is received, the polysilicon 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.

[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 motor safety and ignition control device is provided, comprising:

[0022] A boost and energy storage unit, comprising a flyback circuit and a high-voltage pulse capacitor, configured to receive a first safety signal, a second safety signal, and a third safety signal. Upon receiving the safety 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 safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety signal is a pulse-width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0023] A safety status feedback unit, the safety status feedback unit being connected to the boost and energy storage unit via the high-voltage pulse capacitor and configured to generate and output a safety indication signal, the safety indication signal comprising 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 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 power positive input port (VIN), configured to receive the first fuse signal;

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

[0028] a pulse width modulation signal input port (PWM), configured to receive the third safety signal;

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

[0030] A flyback circuit, comprising:

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

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

[0033] Pulse width modulation signal input port (PWM), used to connect the third resistor (R3);

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

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

[0036] A second resistor (R1) and a 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 for connecting the second resistor (R1), the second capacitor (C2), and the S pin of the transistor (U1);

[0038] A transistor (U1), whose pins are marked 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 second terminal of the primary side 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 for dividing the voltage across a high-voltage pulse capacitor (a first capacitor, C1) by a factor of 120, the resistor voltage divider circuit comprising a first resistor (R4) and a second resistor (R5);

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

[0043] a second comparator, having a positive input terminal connected to the second reference voltage terminal and a negative input terminal connected to the output terminal of the resistor 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 greater than 800 volts;

[0044] A first voltage stabilizing diode (D6) is used to provide 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);

[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 components with an accuracy error of less than 5 percent.

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

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

[0049] an operational amplifier (U3.2), having an inverting input terminal connected to a connection point of a first resistor (R7), a second resistor (R8) and a first capacitor (C5), and a non-inverting input terminal for outputting a safety feedback status 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] Power positive input port (VIN), used to receive power signal;

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

[0054] Logic ground port (DGND) uses single-point grounding;

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

[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) for connecting the power supply of the differential gate driver (U5) and connected to the positive power input port (VIN); a second pin (GND) for connecting to the ground (GND); a third pin (IN+) for connecting to the positive signal terminal (FIRE+) of the rocket engine ignition signal port; a fourth pin (IN-) for connecting to the negative signal terminal (FIRE-) of the rocket engine ignition signal port; and a fifth pin (OUT) 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), serving as a decoupling capacitor for 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] A 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 the positive signal terminal (FIRE+) of the rocket engine ignition signal port, a second pin is connected to the 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] 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 both components with an error of less than 5%.

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

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

[0070] A boost and energy storage unit, comprising a flyback circuit and a high-voltage pulse capacitor, configured to receive a first safety signal, a second safety signal, and a third safety signal. Upon receiving the safety signals, 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 safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety signal is a pulse-width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0071] A safety status feedback unit, the safety status feedback unit being connected to the boost and energy storage unit via the high-voltage pulse capacitor and configured to generate and output a safety indication signal, the safety indication signal comprising 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 being connected to the boost and energy storage unit via the high-voltage pulse capacitor and configured to generate an ignition signal, the ignition signal being configured to release the ignition energy of the rocket engine;

[0073] an external control interface for receiving external control signals and transmitting them to the solid rocket motor safety and ignition control device;

[0074] a power supply module, configured 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] The relevant technical solutions based on this application are suitable for 12~18V 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 application and, together with the description, serve to explain the principles of the 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 Shown is a main structural diagram of a solid rocket engine safety and ignition control device according to an embodiment of the present application;

[0080] 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;

[0081] Figure 4 The figure shows a circuit 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 FIG2 is a schematic diagram showing a circuit principle of an analog voltage 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;

[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 indicated.

[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, numerous specific details are provided in the detailed description below to better illustrate the present disclosure. Those skilled in the art will appreciate that the present application can be practiced without certain specific details. In some instances, methods, means, components, and circuits well known to those skilled in the art are not described in detail in order to highlight the main purpose 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 safety signal has a modulation signal. If so, release the safety. If not, wait for the modulation signal to be connected. Step S1 also includes:

[0090] Step S1001: obtaining a first safety signal and / or a second safety signal and / or a third safety signal, wherein the first safety signal is a power positive electrode connection signal, the second safety signal is a power negative electrode connection signal, and the third safety 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 so, proceed to step S2; otherwise, proceed to step S1.

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

[0093] Step S3: Outputting a safety indication signal externally, the safety indication signal including: 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 embodiment]

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

[0099] A boost and energy storage unit, comprising a flyback circuit and a high-voltage pulse capacitor, for receiving a first safety signal, a second safety signal, and a third safety signal. Upon receiving the safety signal, the flyback circuit charges the energy storage capacitor and stores energy, and boosts the voltage of the high-voltage pulse capacitor to a first high-voltage range. The first safety signal is a power supply positive electrode connection signal, the second safety signal is a power supply negative electrode connection signal, and the third safety signal is a pulse width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0100] A safety status feedback unit is connected to the boost and energy storage unit via a high-voltage pulse capacitor and is used to generate and output a safety indication signal. 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.

[0101] The energy release control unit 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] Power positive input port (VIN), used to receive the first insurance signal;

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

[0105] Pulse width modulation signal input port (PWM), used to receive the 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 the first primary terminal of a transformer (a first transformer, L1), a second resistor (R1), and a second capacitor (C2);

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

[0110] Pulse width modulation signal input port (PWM), used to connect the third resistor (R3);

[0111] a first transformer (L1), a first primary terminal connected to a positive input port (VIN) of a power supply, a second primary terminal connected to a D pin of a transistor (U1), a third secondary terminal connected to an anode of a first diode (D2), and a fourth secondary terminal 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 its positive terminal connected to the cathode of the first diode (D2) and its negative terminal connected to the high-voltage ground (AGND);

[0113] A second resistor (R1) and a 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) for connecting a second resistor (R1), a second capacitor (C2) and an S pin of a transistor (U1);

[0115] A transistor (U1) having pins labeled D, S, and G, wherein the G terminal is connected to a switch enable signal output port (SW_ENABLE), the S terminal is connected to a ground (GND), and the D terminal is connected to a second terminal of the primary side 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 figure shows a schematic diagram of the circuit principle 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 for dividing the voltage across a high-voltage pulse capacitor (a first capacitor, C1) by a factor of 120, the resistor voltage divider circuit comprising a first resistor (R4) and a second resistor (R5);

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

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

[0121] A first voltage stabilizing diode (D6) is used to provide a first reference voltage, and 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 percent.

[0124] In another preferred embodiment, Figure 5 FIG. 1 is a schematic diagram illustrating a circuit principle for outputting an analog voltage signal 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:

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

[0126] an operational amplifier (U3.2), having an inverting input terminal connected to a connection point of a first resistor (R7), a second resistor (R8) and a first capacitor (C5), and a non-inverting input terminal for outputting a safety feedback status 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 figure 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] Power positive input port (VIN), used to receive power signal;

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

[0131] Logic ground port (DGND) uses single-point grounding;

[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, and GS, where D is connected to the positive terminal of the high-voltage pulse capacitor (first capacitor, C1), G is connected to the output of the differential gate driver (U5), GS is connected to ground (GND), and S is connected to the positive terminal 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; the fifth pin (OUT) is used for the output signal and is connected to the G terminal of the polysilicon doped silicon (MCT, U4);

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

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

[0137] A first resistor (R9) has one end connected to the ground (GND) and the other end 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 ground (GND);

[0141] A high-speed current transient blocker (D5) with its anode connected to the fifth pin (OUT) of the differential gate driver (U5) and its 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 (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 both components with an error of less than 5%.

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

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

[0147] [Equipment Example]

[0148] A solid rocket motor 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, comprising a flyback circuit and a high-voltage pulse capacitor, for receiving a first safety signal, a second safety signal, and a third safety signal. Upon receiving the safety signals, 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 safety signal is a power supply positive electrode connection signal, the second safety signal is a power supply negative electrode connection signal, and the third safety signal is a pulse-width modulation signal. The first high-voltage range is 1200 to 1300 volts.

[0151] A safety status feedback unit is connected to the boost and energy storage unit via a high-voltage pulse capacitor and is used to generate and output a safety indication signal. 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.

[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, which is used to release the ignition energy of the rocket engine;

[0153] An external control interface, used to receive external control signals and transmit them to the solid rocket motor safety and ignition control device;

[0154] Power module, used to provide operating voltage for solid rocket motor safety and ignition control devices;

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

[0156] While various embodiments of the present disclosure have been described above, the above descriptions are illustrative, non-exhaustive, and not intended to be limiting of the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is selected to best explain the principles of the embodiments, their practical applications, or improvements to existing technologies, or to enable others skilled 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 safety signal has a modulation signal, if so, release the safety, if not, wait for the modulation signal to be connected, said step S1 also includes: Step S1001: obtaining a first safety signal, a second safety signal, and a third safety signal, wherein the first safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety 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 executing step S1; Step S2: Raising the voltage across a high-voltage pulse capacitor with a capacity of 0.24 microfarads to within a first high-voltage range of 1200 to 1300 volts within 1 second, wherein the high-voltage pulse capacitor is voltage-regulated by a voltage or current negative feedback voltage stabilization method; Step S3: Outputting a safety indication signal externally, the safety indication signal including: an analog voltage signal of 0 to 3 volts and an open-drain output signal reflecting whether the high voltage in step S2 is successfully established; Step S4: receiving a differential ignition control electrical signal. When the differential ignition control electrical signal is received, the polysilicon 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.

2. The solid rocket motor safety and ignition control method according to claim 1, characterized in that: The PWM signal frequency range is 20 to 60 kHz, and the positive duty cycle range is 10% to 30%.

3. The solid rocket engine safety and ignition control 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, comprising a flyback circuit and a high-voltage pulse capacitor, configured to receive a first safety signal, a second safety signal, and a third safety signal. Upon receiving the first, second, and third safety signals, the flyback circuit charges and stores energy in the high-voltage pulse capacitor and boosts the voltage of the high-voltage pulse capacitor to a first high-voltage range. The first safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety signal is a pulse-width modulation signal. 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 via the high-voltage pulse capacitor, and is used to generate and output a safety indication signal. The safety indication signal includes an analog voltage signal of 0 to 3 volts and an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established. The safety status feedback unit also includes: a resistor voltage divider circuit, for dividing the voltage across the high-voltage pulse capacitor (C1) at 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 when the voltage across the high-voltage pulse capacitor (C1) is higher than 1250 volts, and outputting the switch enable signal to an output port (SW_ENABLE); a second comparator, the positive input of which is connected to the second reference voltage terminal, the negative input of which is connected to the output of the resistor divider circuit, and is used to generate a safety feedback state output signal (SEC_FB) when the voltage across the high-voltage pulse capacitor (C1) is higher than 800 volts; A first voltage stabilizing diode (D6) is used to provide 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); A second voltage stabilizing diode (D7) is used to provide a second reference voltage, wherein the second reference voltage terminal is connected to the positive electrode of the power supply via the second voltage stabilizing diode (D7); The first resistor (R4), the second resistor (R5) and the first voltage stabilizing diode (D6) are all components with an accuracy error of less than 5 percent; a first capacitor (C5), connected between the resistor voltage divider circuit and the negative input port (GND) of the power supply, for smoothing the voltage signal; an operational amplifier (U3.2), having an inverting input terminal connected to a connection point of a fourth resistor (R7), a fifth resistor (R8) and a first capacitor (C5), and a non-inverting input terminal for outputting a safety feedback state output signal (SEC_FB); Wherein, the operational amplifier (U3.2) is used to provide an accurate analog output signal according to input voltage conditions; An 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 for the rocket engine, and the ignition signal is used to release the ignition energy of the rocket engine.

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

6. The solid rocket motor safety and ignition control device according to claim 5, characterized in that: The energy release control unit includes: Power positive input port (VIN), used to receive power signal; The negative electrode input port of the power supply (GND) is used to receive the negative electrode signal of the power supply; Logic ground port (DGND) uses single-point grounding; Rocket engine ignition signal port (FIRE+, FIRE-), including: rocket engine ignition signal port positive signal port (FIRE+) and rocket engine ignition signal port negative signal port (FIRE-); Polysilicon doped silicon (U4), whose pins are marked as D, S, G, and GS, wherein the D terminal is connected to the positive electrode of the high-voltage pulse capacitor (C1), the G terminal is connected to the output terminal of the differential gate driver (U5), the GS terminal is connected to the negative input port (GND) of the power supply, 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) for connecting the power supply of the differential gate driver (U5) and connected to the positive power input port (VIN); a second pin (GND) for connecting to the negative power input port (GND); a third pin (IN+) for connecting to the positive signal port (FIRE+) of the rocket engine ignition signal port; a fourth pin (IN-) for connecting to the negative signal port (FIRE-) of the rocket engine ignition signal port; and a fifth pin (OUT) for outputting a signal connected to the G end of the polysilicon-doped silicon (U4); a high-voltage pulse capacitor (C1), the positive electrode of which is connected to the D terminal of the polysilicon-doped silicon (U4), and the negative electrode of which is connected to the high-voltage ground (AGND); a third capacitor (C6), serving as a decoupling capacitor for the differential gate driver (U5), connected in parallel between the positive power input port (VIN) and the negative power input port (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 negative input port (GND) of the power supply, and the other end of which is connected between the fifth pin (OUT) of the differential gate driver (U5); A 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 power supply negative input port (GND); a first transient voltage suppression diode (D3), comprising three pins, wherein a first pin is connected to the positive signal port (FIRE+) of the rocket engine ignition signal port, a second pin is connected to the negative signal port (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 polysilicon-doped silicon (U4), and a second pin of which is connected to the negative input port (GND) of the power supply; a high-speed current transient blocker (D5), an anode of which is connected to the fifth pin (OUT) of the differential gate driver (U5) and a cathode of which is connected to the negative input port (GND) of the power supply; a detonator (LG), used for performing an ignition action, connected in series between the negative electrode of the high-voltage pulse capacitor (C1) and the S terminal of the polysilicon-doped silicon (U4); The energy release control unit is connected to the boost and energy storage unit via the high-voltage pulse capacitor (C1) and is used to release the ignition energy of the rocket engine.

7. The solid rocket motor safety and ignition control device according to any one of claims 4 to 6, 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%.

8. A solid rocket engine safety and ignition control device, characterized in that: include: A solid rocket motor safety and ignition control device, the solid rocket motor safety and ignition control device comprising: A boost and energy storage unit, comprising a flyback circuit and a high-voltage pulse capacitor, configured to receive a first safety signal, a second safety signal, and a third safety signal. Upon receiving the first, second, and third safety signals, the flyback circuit charges and stores energy in the high-voltage pulse capacitor and boosts the voltage of the high-voltage pulse capacitor to a first high-voltage range. The first safety signal is a positive power supply connection signal, the second safety signal is a negative power supply connection signal, and the third safety signal is a pulse-width modulation signal. 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 via the high-voltage pulse capacitor, and is used to generate and output a safety indication signal. The safety indication signal includes an analog voltage signal of 0 to 3 volts and an open-drain output signal indicating whether the high-voltage pulse capacitor is successfully established. The safety status feedback unit also includes: a resistor voltage divider circuit, for dividing the voltage across the high-voltage pulse capacitor (C1) at 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, a positive input terminal of which is connected to the first reference voltage terminal, a negative input terminal of which is connected to the output terminal of the resistor voltage divider circuit, and is used to generate a switch enable signal (SW_ENABLE) when the voltage across the high-voltage pulse capacitor (C1) is higher than 1250 volts; a second comparator, the positive input of which is connected to the second reference voltage terminal, the negative input of which is connected to the output of the resistor divider circuit, and is used to generate a safety feedback state output signal (SEC_FB) when the voltage across the high-voltage pulse capacitor (C1) is higher than 800 volts; A first voltage stabilizing diode (D6) is used to provide 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); A second voltage stabilizing diode (D7) is used to provide a second reference voltage, wherein the second reference voltage terminal is connected to the positive electrode of the power supply via the second voltage stabilizing diode (D7); The first resistor (R4), the second resistor (R5) and the first voltage stabilizing diode (D6) are all components with an accuracy error of less than 5 percent; a first capacitor (C5), connected between the resistor voltage divider circuit and the negative input port (GND) of the power supply, for smoothing the voltage signal; an operational amplifier (U3.2), having an inverting input terminal connected to a connection point of a fourth resistor (R7), a fifth resistor (R8) and a first capacitor (C5), and a non-inverting input terminal for outputting a safety feedback state output signal (SEC_FB); Wherein, the operational amplifier (U3.2) is used to provide an accurate analog output signal according to input voltage conditions; An energy release control unit, the energy release control unit being connected to the boost and energy storage unit via the high-voltage pulse capacitor and configured to generate an ignition signal, the ignition signal being configured to release the ignition energy of the rocket engine; an external control interface for receiving external control signals and transmitting them to the solid rocket motor safety and ignition control device; a power supply module, configured 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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