Modular airborne booster rocket initiator

Abstract

This invention discloses a modular airborne booster rocket initiator, belonging to the field of unmanned aerial vehicles (UAVs). It includes a shell and an integrated main control CPU module, connected to an isolated power supply module, an isolated drive module, an isolated communication module, a resistance measurement module, and an ignition detection module. The main control CPU module receives ignition commands and converts them into control signals, sending them to the isolated drive module to provide a continuous and stable ignition drive current to the pyrotechnic device. The pyrotechnic device generates thrust through ignition, enabling rocket boosting, parachute door opening control, airbag door opening control, or parachute jettisoning. After successful ignition, the drive current flows back to the ignition detection module through a current-limiting protection module. The current-limiting protection module employs a dual-redundant ignition circuit, ensuring that either individual circuit can guarantee ignition of the pyrotechnic device, while the parallel connection of the two circuits improves circuit reliability. The resistance measurement module measures the internal resistance of the pyrotechnic device before ignition, providing a milliampere-level detection current to ensure that ignition is not accidentally triggered during the measurement process.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicles (UAVs), specifically a modular airborne booster rocket initiator. Background Technology

[0002] Traditional booster rocket initiators are mostly used for rocket ignition during ground launches, and have core problems such as large size, single function, insufficient reliability, and poor compatibility with UAVs.

[0003] Existing technologies often employ discrete components or non-modular designs, making it difficult to meet the lightweight requirements of drones in terms of size, weight, and power consumption. Moreover, the equipment only supports basic ignition functions, lacking real-time monitoring and current limiting protection for the ignition status of pyrotechnics, and is unable to provide feedback on the ignition results of pyrotechnics or prevent short circuits after ignition. The equipment is characterized by limited functionality and a lack of intelligence.

[0004] In addition, most booster rocket initiators are designed for use in ground-launched or fixed-platform launch environments, without considering the environmental adaptability issues faced by equipment in airborne environments, such as high and low temperatures, strong vibrations, and complex electromagnetic interference. They also have poor compatibility with commonly used airborne electrical interfaces for UAVs. Summary of the Invention

[0005] To address the problems of bulky size, limited functionality, inconvenience, and low reliability of commonly used UAV booster rocket initiators, this invention proposes a modular airborne booster rocket initiator. By using dual-path current-limiting resistors to achieve redundant protection, pre-ignition pyrotechnic internal resistance measurement, and ignition result detection, the adaptability, reliability, and safety of the booster rocket initiator in airborne environments are significantly improved.

[0006] The airborne booster rocket initiator includes a shell and internally integrated power supply and communication connectors, ignition output connectors, an isolated power supply module, a main control CPU module, an isolated drive module, an isolated communication module, a current limiting protection module, an ignition detection module, and a resistance measurement module. The main control CPU module is simultaneously connected to the isolated power supply module, the isolated drive module, the isolated communication module, the resistance measurement module, and the ignition detection module.

[0007] The onboard battery of the external drone connects to the power supply and communication socket of the detonator via the drone's own power supply and communication connector, providing a continuous and stable external power supply to the isolation power module, and after processing, providing a stable and reliable electrical isolation power supply to all internal functional modules.

[0008] After receiving the pyrotechnic ignition command sent by the ground operator, the flight control computer of the external drone connects to the power supply and communication socket of the detonator through the drone's own power supply and communication connector, and then sends the pyrotechnic ignition command to the isolation communication module and the pyrotechnic ignition command with stable and reliable electrical isolation to the main control CPU module.

[0009] The main control CPU module converts the received pyrotechnic ignition command into an ignition control signal and sends it to the isolation drive module. The isolation drive module controls the MOSFET or solid-state relay to conduct the circuit, and connects to the external ignition output connector through the initiator's ignition output connector to provide a continuous and stable ignition drive current to the pyrotechnic. Under the action of the continuous and stable ignition drive current, the pyrotechnic undergoes a chemical reaction and ignites, which is converted into force to boost the rocket, or to control the opening of the parachute and airbag doors, or to control the ejection of the parachute.

[0010] After the ignition drive current passes through the pyrotechnic device, it will flow back to the ignition detection module through the ignition output connector and the current limiting protection module.

[0011] The current limiting protection module includes N×2 current limiting circuits for pyrotechnics, corresponding to the ignition circuits of N pyrotechnics. That is, for each pyrotechnic, the current limiting protection module includes circuit 1 and circuit 2 connected in parallel. Each circuit is connected in series with a current limiting resistor. Any single circuit can ensure the ignition of the pyrotechnic. The two circuits connected in parallel form a redundant protection circuit, which improves the ignition reliability.

[0012] For any pyrotechnic device, when circuit 1 is working normally and circuit 2 is faulty, the formula for calculating the ignition drive current 1 is as follows:

[0013] I21 std =V1 std / (R1 std +R21 std +R3 std );

[0014] I21 min =V1 min / (R1 max +R21 max +R3 max );

[0015] I21 max =V1 max / (R1 min +R21 min +R3 min );

[0016] I20 std =I21 std ;

[0017] I20 min =I21 min ;

[0018] I20 max =I21 max ;

[0019] V1 std R1 is the standard value of the external power supply voltage. std R21 is the standard internal resistance value for pyrotechnic components. std R3 is the standard resistance value of current-limiting resistor 1; std This refers to the standard resistance value of the onboard circuitry; I21 std V1 in the circuit std R1 std R21 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for current-limiting resistor 1;

[0020] V1 min R1 represents the minimum external power supply voltage. max R21 represents the maximum internal resistance of the pyrotechnic component. max R3 represents the maximum resistance of current-limiting resistor 1. max I21 represents the maximum internal resistance of the onboard circuitry. min V1 in the circuit min R1 max R21 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for current-limiting resistor 1;

[0021] V1 max R1 represents the maximum value of the external power supply voltage. min R21 is the minimum internal resistance of the pyrotechnic component. min R3 is the minimum resistance value of current-limiting resistor 1; min I21 represents the minimum internal resistance of the onboard circuitry. max V1 in the circuit max R1 min R21 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to current-limiting resistor 1;

[0022] When circuit 2 is working normally and circuit 1 is faulty, the formula for calculating the ignition drive current 2 is as follows:

[0023] I22 std =V1 std / (R1 std +R22 std +R3 std );

[0024] I22 min =V1 min / (R1 max +R22 max +R3 max);

[0025] I22 max =V1 max / (R1 min +R22 min +R3 min );

[0026] I20 std =I22 std ;

[0027] I20 min =I22 min ;

[0028] I20 max =I22 max ;

[0029] R22 std I22 is the standard resistance value of current-limiting resistor 2. std V1 in the circuit std R1 std R22 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for the current-limiting resistor 2;

[0030] R22 max I22 represents the maximum resistance of current-limiting resistor 2. min V1 in the circuit min R1 max R22 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for the current-limiting resistor 2;

[0031] R22 min I22 is the minimum resistance value of current-limiting resistor 2. max V1 in the circuit max R1 min R22 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to the current-limiting resistor 2;

[0032] When both circuit 1 and circuit 2 are operating normally, the two current-limiting resistors are connected in parallel. According to the characteristics of parallel circuits, the sum of the ignition drive currents is the sum of the two independent currents flowing through them. The calculation formula is as follows:

[0033] I20 std =V1 std / (R1 std +1 / (1 / R21 std +1 / R22 std)+R3 std );

[0034] I20 min =V1 min / (R1 max +1 / (1 / R21 max +1 / R22 max )+R3 max );

[0035] I20 max =V1 max / (R1 min +1 / (1 / R21 min +1 / R22 min )+R3 min );

[0036] The ignition detection module detects the ignition result of the pyrotechnic device and transmits the ignition result back to the flight control computer via the main control CPU module, and finally back to the ground control station.

[0037] Specifically, the ignition detection module collects the current value in the ignition drive circuit and the temperature value near the current-limiting resistor of the pyrotechnic device; and transmits the current value and temperature value to the main control CPU module. The ignition result is detected through the preset ignition result judgment logic. When the pyrotechnic device is judged to have failed to ignite, in order to avoid misjudgment caused by command transmission failure, the system will automatically send the pyrotechnic device ignition command several times.

[0038] After the main control CPU module completes the ignition result detection, it sends the ignition result to the isolation communication module; through the externally connected power supply and communication connector, it sends a stable and reliable electrically isolated ignition result to the flight control computer.

[0039] After receiving the internal resistance measurement command for the pyrotechnic device transmitted by the main control CPU module (this command is sent by the ground operator via the flight control computer), the resistance measurement module sends a resistance measurement signal to the solid-state relay or MOSFET in the resistance measurement module, thereby turning on the constant current source circuit and providing a DC current I. test The internal resistance of the pyrotechnic device to be measured is supplied, and a voltage V is simultaneously generated across the pyrotechnic device. test The analog-to-digital converter (ADC) sends the voltage values ​​across the pyrotechnic device to the main control CPU module; the main control CPU module then calculates R... test =V test / I test The internal resistance value R of the pyrotechnic device is obtained. test ;

[0040] The main control CPU module transmits the internal resistance of the pyrotechnic device to the flight control computer via the isolation communication module and the externally connected power supply and communication connector, and finally back to the ground control station.

[0041] The advantages of this invention are:

[0042] 1. This invention provides a modular airborne booster rocket initiator that integrates the control capabilities of other pyrotechnics necessary for the recovery of unmanned aerial vehicles (UAVs). The onboard pyrotechnic ignition equipment is simplified into a separate device, eliminating the need for additional equipment. It can provide a larger ignition drive current without the need for additional supporting equipment.

[0043] 2: This invention provides a modular airborne booster rocket initiator that uses an onboard battery, eliminating the need for a ground-based battery; the airborne rocket booster initiator can measure the rocket's internal resistance before ignition to prevent ignition failure and provide early warning.

[0044] 3: This invention provides a modular airborne booster rocket initiator, which uses a dual-redundant ignition circuit design to ensure ignition success rate;

[0045] 4: The present invention provides a modular airborne booster rocket initiator with modular replacement capability. When a rocket with greater thrust or a pyrotechnic device with greater current is required, the current-limiting resistor module can be replaced independently, reducing the cost of equipment use. Attached Figure Description

[0046] Figure 1 This is a structural diagram of a modular airborne booster rocket initiator according to the present invention;

[0047] Figure 2 This is a schematic diagram of a modular airborne booster rocket initiator according to the present invention.

[0048] Figure 3 This is a schematic diagram of the current limiting protection module described in this invention;

[0049] Figure 4 This is a schematic diagram of the ignition detection module of the present invention, which collects temperature and current to determine whether ignition is successful.

[0050] Figure 5 This is a schematic diagram illustrating the principle of measuring the internal resistance of pyrotechnic components using the resistance measurement module of this invention.

[0051] Figure 6 This is a schematic diagram illustrating the working principle of a modular airborne booster rocket initiator according to the present invention. Detailed Implementation

[0052] The specific implementation method of the present invention will be further described in detail below with reference to the accompanying drawings.

[0053] This invention proposes a modular airborne booster rocket initiator that integrates power supply, communication, drive, and detection functions into a single housing. It adopts a highly integrated and reliable design, and achieves dual-path redundancy protection through a dual-path parallel current limiting circuit. It also integrates resistance measurement and ignition detection modules to monitor the status of pyrotechnics in real time, and has the ignition function of pyrotechnics necessary for booster rocket ignition and various types of parachute recovery.

[0054] like Figure 1 As shown, the airborne booster rocket initiator includes a shell and internally integrated power supply and communication connectors, ignition output connectors, an isolated power supply module, a main control CPU module, an isolated drive module, an isolated communication module, a current limiting protection module, an ignition detection module, and a resistance measurement module. The main control CPU module is simultaneously connected to the isolated power supply module, the isolated drive module, the isolated communication module, the resistance measurement module, and the ignition detection module.

[0055] like Figure 2 As shown, the onboard battery of the external drone connects to the power supply and communication socket of the detonator via the drone's own power supply and communication connector, providing a continuous and stable external power supply to the isolated power module, and providing a stable and reliable electrically isolated power supply to all functional modules inside the detonator that require power.

[0056] After receiving the pyrotechnic ignition command sent by the ground operator, the flight control computer of the external drone connects to the power supply and communication socket of the detonator through the drone's own power supply and communication connector, and sends the pyrotechnic ignition command to the isolation communication module, and sends the stable and reliable electrically isolated pyrotechnic ignition command to the main control CPU module.

[0057] The main control CPU module converts the received pyrotechnic ignition command into an ignition control signal and sends it to the isolation drive module. The isolation drive module controls the MOSFET or solid-state relay to conduct the circuit, and connects to the external ignition output connector through the initiator's ignition output connector to provide a continuous and stable ignition drive current to the pyrotechnic. Under the action of the continuous and stable ignition drive current, the pyrotechnic undergoes a chemical reaction and ignites, converting the force into rocket booster, or controlling the opening of the parachute and airbag doors, or controlling the ejection of the parachute.

[0058] After the ignition drive current passes through the pyrotechnic device, it will flow back to the ignition detection module through the ignition output connector and the current limiting protection module.

[0059] like Figure 3 As shown, the current limiting protection module includes N×2 current limiting circuits for pyrotechnics, corresponding to the ignition circuits of N pyrotechnics; that is, for each pyrotechnic, the current limiting protection module includes circuit 1 and circuit 2 connected in parallel; each circuit is connected in series with a current limiting resistor, and any single circuit can ensure the ignition of the pyrotechnic, while the parallel connection of the two circuits improves the reliability of the circuit.

[0060] The ignition drive current I21 in the circuit containing the current-limiting resistor 1 of the pyrotechnic device is determined by the internal resistance R1 of the pyrotechnic device, the resistance R21 of the current-limiting resistor, the internal resistance R3 of the onboard circuit, and the external power supply voltage V. The ignition drive current I22 in the circuit containing the current-limiting resistor 2 of the pyrotechnic device is determined by the internal resistance R1 of the pyrotechnic device, the resistance R22 of the current-limiting resistor, the internal resistance R3 of the onboard circuit, and the external power supply voltage V. The total ignition drive current I20 in the ignition drive circuit composed of the current-limiting resistors 1 and 2 is determined by the ignition drive currents I21 and I22.

[0061] When designing the drive circuit for pyrotechnic devices, the minimum required drive current I1 of the pyrotechnic device should be taken into account. min Ensure that the ignition drive circuit can provide the ignition drive current I21 min Ignition drive current I22 min and ignition drive total current I20 min All are greater than the minimum driving current I1 required for pyrotechnic devices. min In addition, the ignition drive circuit can provide an ignition drive current I21. max Ignition drive current I22 max and ignition drive total current I20 max All currents should be within the safe current range of the circuit and should not exceed the upper limit of the current threshold of the internal circuit and main components.

[0062] Under the premise of N-channel pyrotechnic devices, for any pyrotechnic device, when circuit 1 is working normally and circuit 2 is faulty, the calculation formula for ignition drive current 1 is as follows:

[0063] I21 std =V1 std / (R1 std +R21 std +R3 std );

[0064] I21 min =V1 min / (R1 max +R21 max +R3 max );

[0065] I21 max =V1 max / (R1 min +R21 min +R3 min );

[0066] I20 std =I21 std ;

[0067] I20 min =I21 min ;

[0068] I20 max =I21 max ;

[0069] V1 std R1 is the standard value of the external power supply voltage. std R21 is the standard internal resistance value for pyrotechnic components. std R3 is the standard resistance value of current-limiting resistor 1; std This refers to the standard resistance value of the onboard circuitry; I21 std V1 in the circuit std R1 std R21 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for current-limiting resistor 1;

[0070] V1 min R1 represents the minimum external power supply voltage. max R21 represents the maximum internal resistance of the pyrotechnic component. max R3 represents the maximum resistance of current-limiting resistor 1. max I21 represents the maximum internal resistance of the onboard circuitry. min V1 in the circuit min R1 max R21 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for current-limiting resistor 1;

[0071] V1 max R1 represents the maximum value of the external power supply voltage. min R21 is the minimum internal resistance of the pyrotechnic component. min R3 is the minimum resistance value of current-limiting resistor 1; min I21 represents the minimum internal resistance of the onboard circuitry. max V1 in the circuit max R1 min R21 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to current-limiting resistor 1;

[0072] I20 std The value is the value of V1 in the circuit when circuit 1 is working normally and circuit 2 is faulty. std R1 std R21 std R3 stdUnder typical conditions, the ignition drive circuit can provide the standard total ignition drive current for pyrotechnic devices;

[0073] I20 min The value is the value of V1 in the circuit when circuit 1 is working normally and circuit 2 is faulty. min R1 max R21 max R3 max Under typical conditions, the minimum total ignition drive current that the ignition drive circuit can provide to the pyrotechnic device;

[0074] I20 max The value is the value of V1 in the circuit when circuit 1 is working normally and circuit 2 is faulty. max R1 min R21 min R3 min Under typical conditions, the maximum total ignition drive current that the ignition drive circuit can provide to the pyrotechnic device;

[0075] When circuit 2 is working normally and circuit 1 is faulty, the formula for calculating the ignition drive current 2 is as follows:

[0076] I22 std =V1 std / (R1 std +R22 std +R3 std );

[0077] I22 min =V1 min / (R1 max +R22 max +R3 max );

[0078] I22 max =V1 max / (R1 min +R22 min +R3 min );

[0079] I20 std =I22 std ;

[0080] I20 min =I22 min ;

[0081] I20 max =I22 max ;

[0082] V1 std R1 is the standard value of the external power supply voltage. std R22 is the standard internal resistance value for pyrotechnic components.std R3 is the standard resistance value of current-limiting resistor 2; std This is the standard resistance value of the onboard circuitry; I22 std V1 in the circuit std R1 std R22 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for the current-limiting resistor 2;

[0083] V1 min R1 represents the minimum external power supply voltage. max R22 represents the maximum internal resistance of the pyrotechnic component. max R3 represents the maximum resistance of current-limiting resistor 2. max I22 represents the maximum internal resistance of the onboard circuitry. min V1 in the circuit min R1 max R22 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for the current-limiting resistor 2;

[0084] V1 max R1 represents the maximum value of the external power supply voltage. min R22 is the minimum internal resistance of the pyrotechnic component. min R3 is the minimum resistance value of current-limiting resistor 2; min I22 represents the minimum internal resistance of the onboard circuitry. max V1 in the circuit max R1 min R22 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to the current-limiting resistor 2;

[0085] I20 std The value is V1 in the circuit when circuit 2 is working normally and circuit 1 is faulty. std R1 std R22 std R3 std Under typical conditions, the ignition drive circuit can provide the standard total ignition drive current for pyrotechnic devices;

[0086] I20 min The value is V1 in the circuit when circuit 2 is working normally and circuit 1 is faulty. min R1 max R22 max R3 max Under typical conditions, the minimum total ignition drive current that the ignition drive circuit can provide to the pyrotechnic device;

[0087] I20 max The value is V1 in the circuit when circuit 2 is working normally and circuit 1 is faulty. max R1 min R22 min R3 min Under typical conditions, the maximum total ignition drive current that the ignition drive circuit can provide to the pyrotechnic device;

[0088] When both circuit 1 and circuit 2 are working normally, the two current-limiting resistors are connected in parallel. According to the characteristics of parallel circuits, the sum of the ignition drive currents is the sum of the two independent currents. The calculation formula is as follows:

[0089] I20 std =V1 std / (R1 std +R21 std +R3 std )+V1 std / (R1 std +R22 std +R3 std );

[0090] I20 min =V1 min / (R1 max +R21 max +R3 max )+V1 min / (R1 max +R22 max +R3 max );

[0091] I20 max =V1 max / (R1 min +R21 min +R3 min )+V1 max / (R1 min +R22 min +R3 min );

[0092] The airborne booster rocket initiator has a pyrotechnic ignition detection function. After the pyrotechnic ignites, it can detect the ignition result and transmit the ignition result back to the flight control computer.

[0093] The ignition detection function for pyrotechnics is performed by the ignition detection module together with the ignition function and the current limiting protection function for pyrotechnics.

[0094] The ignition detection module detects the ignition result of the pyrotechnic device and transmits the ignition result back to the flight control computer via the main control CPU module, and finally back to the ground control station.

[0095] like Figure 4 As shown, specifically: under the action of the ignition drive current, the pyrotechnic device begins to ignite. The ignition duration is typically tens to hundreds of milliseconds, and the ignition current is typically several amperes to tens of amperes. The ignition drive current flows back to the ignition detection module through the ignition output connector, the pyrotechnic device, and the current limiting protection module. The ignition detection module collects the current value in the ignition drive circuit through the current isolation sampling circuit and sends the current value to the main control CPU module through the internal connection circuit of the circuit board.

[0096] Simultaneously, the temperature value near the current-limiting resistor of the pyrotechnic device in the ignition drive circuit is collected through the temperature acquisition circuit; the temperature value is sent to the main control CPU module through the internal connection circuit of the circuit board; the main control CPU module detects the ignition result through the preset ignition result judgment logic. When the pyrotechnic device is judged to have failed to ignite, in order to avoid ignition failure or detection misjudgment caused by command transmission failure, and to ensure that the ignition command is sent successfully, the pyrotechnic device ignition command is sent repeatedly several times.

[0097] After the main control CPU module completes the ignition result detection, it sends the ignition result to the isolation communication module. Through the externally connected power and communication connector, it sends a stable and reliable electrically isolated ignition result to the flight control computer. Upon receiving the ignition result, the external flight control computer sends it back to the ground control station via the external device's onboard data link. Simultaneously, the flight control computer uses the ignition result to perform corresponding logical judgments.

[0098] The airborne booster rocket initiator has a pyrotechnic internal resistance measurement function. Before pyrotechnic ignition, it is responsible for receiving and executing the pyrotechnic internal resistance measurement command from the flight control computer, measuring the internal resistance of the pyrotechnic, and transmitting the resistance value back to the flight control computer.

[0099] like Figure 5 As shown, after receiving the internal resistance measurement command for the pyrotechnic device transmitted from the main control CPU module (this command is transmitted from the ground operator via the flight control computer), the resistance measurement module sends a resistance measurement signal to the solid-state relay or MOSFET within the module, thereby turning on the constant current source circuit and providing a DC current I in the range of several milliamps. test The internal resistance of the pyrotechnic device to be measured is supplied, and a voltage V is simultaneously generated across the pyrotechnic device. test The analog-to-digital converter (ADC) sends the voltage values ​​across the pyrotechnic device to the main control CPU module; the main control CPU module then calculates R... test =V test / I test The internal resistance value R of the pyrotechnic device is obtained. test ;

[0100] The typical internal resistance of pyrotechnic devices is in the range of several ohms, while the typical ignition current is in the range of several to tens of amperes. By selecting a suitable linear constant current chip in the constant current source circuit and matching appropriate resistors, the typical DC current provided by the constant current source circuit is guaranteed to be in the range of several milliamperes, which differs from the typical ignition current of the pyrotechnic device by a factor of a thousand. This ensures that the pyrotechnic device will not be falsely triggered during internal resistance measurement.

[0101] The main control CPU module transmits the internal resistance of the pyrotechnic device to the flight control computer via the isolation communication module and the externally connected power supply and communication connector, and finally back to the ground control station.

[0102] The working principle of the airborne booster rocket initiator is as follows: Figure 6 As shown, the main control CPU module receives the control signal for ignition of the pyrotechnic device and determines whether ignition is required. If so, the isolation drive module provides ignition drive current to the pyrotechnic device and determines whether it is within the ignition control time range. If so, the ignition detection module collects the current value in the ignition drive circuit and the temperature value near the current-limiting resistor of the pyrotechnic device. When both values ​​are normal, it indicates that ignition is successful and the ignition process ends.

[0103] The isolated power supply module isolates and regulates the external power input voltage through a DC / DC power converter, converting it into internal operating power. The function of the isolated power supply module is to isolate the internal working ground from the external ground, preventing interference from the external power grid. By adding an EMI input filter to the circuit, not only can common-mode current be attenuated and filtered out, but common-mode EMI interference can also be suppressed bidirectionally. Adding devices such as TVS diodes and PMOS transistors before the DC / DC power converter provides circuit protection functions such as reverse polarity protection, voltage spike protection, and short-circuit protection. Connecting a TVS diode in parallel at the input of the DC / DC power converter absorbs ESD and surge voltages, clamping the voltage to a predetermined level, thereby effectively protecting the precision components in the electronic circuit from damage. The PMOS transistor reverse polarity protection circuit features low voltage drop and low loss.

[0104] The main control CPU module receives control commands sent by the flight control computer through the commonly used RS422 / RS232 / CAN interfaces, and after parsing and identifying them, controls the on / off of the corresponding pyrotechnic ignition control channels to realize the power distribution output of each pyrotechnic ignition circuit.

[0105] The isolation drive module uses N×2 pyrotechnic ignition control channels, connected in parallel, to control the ignition outputs of N pyrotechnic devices. Employing mature optocoupler isolation circuits and MOSFET drive circuits, the module requires only external circuitry to meet isolation drive requirements, enabling solid-state ignition switch drive functionality within a small area.

[0106] The isolated communication module uses a commonly used isolated RS422 / RS232 / CAN transceiver chip. This chip isolates the input and output signals and integrates internal transient suppression transistors and ESD protection, which can reduce the interference of the system to other systems through the bus.

[0107] The current limiting protection module consists of a dedicated pyrotechnic current limiting resistor, a current isolation sampling circuit, and a main control CPU circuit. Each pyrotechnic control channel has a current limiting resistor connected in series, for a total of N×2 current limiting resistors. Each channel is independent and does not interfere with each other.

[0108] The ignition detection module, through a current isolation sampling circuit, a temperature acquisition circuit, and a main control CPU circuit, acquires the current value in the ignition drive circuit and the temperature value near the current-limiting resistor of the pyrotechnic device. The current isolation sampling circuit is responsible for acquiring the current value in the ignition drive circuit, and the temperature acquisition circuit is responsible for acquiring the temperature value near the current-limiting resistor of the pyrotechnic device, and sending them to the main control CPU. The main control CPU determines whether the pyrotechnic device has successfully ignited by judging the changes in the main circuit current value and the temperature value near the current-limiting resistor of the pyrotechnic device, thus realizing the detection of the ignition result, and periodically sends the ignition result of the pyrotechnic device back to the flight control computer.

Claims

1. A modular airborne booster rocket initiator, characterized in that, It includes the housing and internally integrated power supply and communication aviation connectors, ignition output aviation connectors, isolated power supply module, main control CPU module, isolated driver module, isolated communication module, current limiting protection module, ignition detection module and resistance measurement module; The main control CPU module is simultaneously connected to the isolated power supply module, isolated driver module, isolated communication module, resistance measurement module and ignition detection module; The main control CPU module receives the ignition command of the pyrotechnics and converts it into an ignition control signal for the isolation drive module. The MOSFET or solid-state relay controlling the circuit of the isolation drive module turns on the circuit and connects to the external ignition output connector through the ignition output connector of the detonator, providing a continuous and stable ignition drive current to the pyrotechnics. Under the action of the continuous and stable ignition drive current, the pyrotechnics undergo a chemical reaction and ignite, converting the force into rocket booster, or controlling the opening of the parachute and airbag doors, or controlling the ejection of the parachute. After the ignition drive current passes through the pyrotechnic device, it will flow back to the ignition detection module through the ignition output connector and the current limiting protection module. The ignition detection module detects the ignition result of the pyrotechnic device and transmits the ignition result back to the flight control computer through the main control CPU module, and finally back to the ground control station.

2. The modular airborne booster rocket initiator as described in claim 1, characterized in that, The onboard battery of the external drone connects to the power and communication socket of the detonator via the drone's own power and communication connector, providing a continuous and stable external power supply to the isolated power module, and providing a stable and reliable electrically isolated power supply to all functional modules inside the detonator that require power.

3. A modular airborne booster rocket initiator as described in claim 1, characterized in that, After receiving the pyrotechnic ignition command from the ground operator, the flight control computer of the external drone connects to the power supply and communication socket of the detonator via the drone's built-in power and communication connector, sends the pyrotechnic ignition command to the isolation communication module, and sends a stable and reliable electrically isolated pyrotechnic ignition command to the main control CPU module.

4. A modular airborne booster rocket initiator as described in claim 1, characterized in that, The current limiting protection module includes N×2 current limiting circuits for pyrotechnics, corresponding to the ignition paths of N pyrotechnics; that is, for each pyrotechnic, the current limiting protection module includes circuit 1 and circuit 2 connected in parallel; each circuit is connected in series with a current limiting resistor, and any single circuit can ensure the ignition of the pyrotechnic, while the parallel connection of the two circuits improves the reliability of the circuit. For any pyrotechnic device, when circuit 1 is working normally and circuit 2 is faulty, the formula for calculating the ignition drive current 1 is as follows: I21 std =V1 std / (R1 std +R21 std +R3 std ); I21 min =V1 min / (R1 max +R21 max +R3 max ); I21 max =V1 max / (R1 min +R21 min +R3 min ); I20 std =I21 std ; I20 min =I21 min ; I20 max =I21 max ; V1 std R1 is the standard value of the external power supply voltage. std R21 is the standard internal resistance value for pyrotechnic components. std R3 is the standard resistance value of current-limiting resistor 1; std This refers to the standard resistance value of the onboard circuitry; I21 std V1 in the circuit std R1 std R21 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for current-limiting resistor 1; V1 min R1 represents the minimum external power supply voltage. max R21 represents the maximum internal resistance of the pyrotechnic component. max R3 represents the maximum resistance of current-limiting resistor 1. max I21 represents the maximum internal resistance of the onboard circuitry. min V1 in the circuit min R1 max R21 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for current-limiting resistor 1; V1 max R1 represents the maximum value of the external power supply voltage. min R21 is the minimum internal resistance of the pyrotechnic component. min R3 is the minimum resistance value of current-limiting resistor 1; min I21 represents the minimum internal resistance of the onboard circuitry. max V1 in the circuit max R1 min R21 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to current-limiting resistor 1; When circuit 2 is working normally and circuit 1 is faulty, the formula for calculating the ignition drive current 2 is as follows: I22 std =V1 std / (R1 std +R22 std +R3 std ); I22 min =V1 min / (R1 max +R22 max +R3 max ); I22 max =V1 max / (R1 min +R22 min +R3 min ); I20 std =I22 std ; I20 min =I22 min ; I20 max =I22 max ; R22 std I22 is the standard resistance value of current-limiting resistor 2. std V1 in the circuit std R1 std R22 std R3 std Under typical conditions, the ignition drive circuit can provide the standard operating drive current for the current-limiting resistor 2; R22 max I22 represents the maximum resistance of current-limiting resistor 2. min V1 in the circuit min R1 max R22 max R3 max Under typical conditions, the minimum operating drive current that the ignition drive circuit can provide for the current-limiting resistor 2; R22 min I22 is the minimum resistance value of current-limiting resistor 2. max V1 in the circuit max R1 min R22 min R3 min Under typical conditions, the ignition drive circuit can provide the maximum operating drive current to the current-limiting resistor 2; When both circuits 1 and 2 are working normally, the formula for calculating the total ignition drive current is as follows: I20 std =V1 std / (R1 std +1 / (1 / R21 std +1 / R22 std )+R3 std ); I20 min =V1 min / (R1 max +1 / (1 / R21 max +1 / R22 max )+R3 max ); I20 max =V1 max / (R1 min +1 / (1 / R21 min +1 / R22 min )+R3 min )。 5. A modular airborne booster rocket initiator as described in claim 1, characterized in that, The ignition detection module simultaneously collects the current value in the ignition drive circuit and the temperature value near the current-limiting resistor of the pyrotechnic device; and transmits the current value and temperature value to the main control CPU module. The ignition result is detected through the preset ignition result judgment logic. When it is determined that the pyrotechnic device has failed to ignite, the pyrotechnic device ignition command is sent repeatedly several times. The failure to transmit the command leads to the ignition failure.

6. A modular airborne booster rocket initiator as described in claim 1, characterized in that, After receiving the internal resistance measurement command for the pyrotechnic device transmitted by the main control CPU module, the resistance measurement module sends a resistance measurement signal to the solid-state relay or MOSFET within the module, thereby turning on the constant current source circuit and providing a DC current I. test The internal resistance of the pyrotechnic device to be measured is supplied, and a voltage V is simultaneously generated across the pyrotechnic device. test The analog-to-digital converter (ADC) sends the voltage values ​​across the pyrotechnic device to the main control CPU module; the main control CPU module then calculates R... test =V test / I test The internal resistance value R of the pyrotechnic device is obtained. test ; The main control CPU module transmits the internal resistance of the pyrotechnic device to the flight control computer via the isolation communication module and the externally connected power supply and communication connector, and finally back to the ground control station.

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