An airborne release timing control system with multiple control modes

Abstract

The utility model discloses an airborne drop timing control system with multiple control modes relates to on -the -air timing control power distribution technical field, include: ignition power supply circuit and working power supply circuit, ignition power supply circuit's output end connects ignition power supply line, and ignition voltage current detection circuit sets up on ignition power supply line, and ignition power supply line passes through the isolation drive circuit and connects the load of ignition, and output detection circuit sets up in the output end position of isolation drive circuit, the output end of working power supply circuit is connected with controller, and the input end of on -off quantity input detection circuit is connected with flight control computer and ignition load, and the output end of on -off quantity input detection circuit accesses controller, and the control end of controller is connected with isolation drive circuit, and controller still is connected with communication circuit, application programming circuit and board temperature detection circuit respectively, and communication circuit still is connected with flight control computer, the utility model has alleviated the technical problem of low reliability, control difficult of prior art.

Description

Technical Field

[0001] This utility model relates to the field of onboard timing control and power distribution technology, specifically an airborne deployment timing control system with multiple control modes. Background Technology

[0002] In recent years, with the increasing number of onboard devices, low-cost, highly integrated multi-channel ignition timing control systems have gained popularity among users, resulting in an unprecedentedly broad market prospect. "Low cost, high reliability, modularity, integration, low maintenance, and ease of maintenance" have become the guiding principles for aircraft research and development. As a component module of the airborne integrated controller, the timing control system is a core unit of the aircraft's integrated control system. It receives timing control commands from the host computer, issues ignition timing control signals, and collects timing status information, online information of pyrotechnic components, and measurement information of ignition current and voltage. Existing timing control systems face drawbacks such as the large number of onboard devices across various aircraft models, high control difficulty, limited monitoring methods, and low reliability. Utility Model Content

[0003] The purpose of this invention is to provide an airborne delivery timing control system with multiple control modes in order to solve at least one of the above-mentioned technical problems.

[0004] In a first aspect, this utility model provides an airborne deployment timing control system with multiple control modes, including: a controller, a power supply circuit, a switch input detection circuit, an ignition voltage and current detection circuit, an isolation drive circuit, an output detection circuit, a communication circuit, an in-application programming circuit, and an onboard temperature detection circuit; wherein, the power supply circuit includes an ignition power supply circuit and a working power supply circuit; the output terminal of the ignition power supply circuit is connected to the ignition power supply line, the ignition voltage and current detection circuit is disposed on the ignition power supply line, the other end of the ignition power supply line is connected to the input terminal of the isolation drive circuit, the output terminal of the isolation drive circuit is connected to the load to be ignited, and the output detection circuit is disposed at the output terminal of the isolation drive circuit; the output terminal of the working power supply circuit is connected to the controller, the input terminal of the switch input detection circuit is connected to the flight control computer and the ignition load, and the output terminal of the switch input detection circuit is connected to the controller; the controller is connected to the control terminal of the isolation drive circuit, and the controller is also connected to the communication circuit, the in-application programming circuit, and the onboard temperature detection circuit respectively, and the communication circuit is also connected to the flight control computer.

[0005] Optionally, the controller includes an ARM chip.

[0006] Optionally, the isolation drive circuit includes a multi-channel ignition load isolation drive circuit and a negative terminal master control isolation drive circuit; the multi-channel ignition load isolation drive circuit is disposed on the positive line of the ignition power line, and the negative terminal master control isolation drive circuit is disposed on the negative line of the ignition power line; the multi-channel ignition load isolation drive circuit includes a high-side field-effect transistor and an optocoupler; the negative terminal master control isolation drive circuit includes a low-side field-effect transistor and an optocoupler.

[0007] Optionally, the ignition voltage and current detection circuit includes an ignition current data acquisition circuit and an ignition voltage data acquisition circuit; the ignition current data acquisition circuit is connected in series on the ignition power line, and the ignition voltage data acquisition circuit is connected in parallel on the two poles of the ignition power line.

[0008] Optionally, it also includes a bus current and voltage acquisition circuit, which is located at the input end of the power supply circuit and is used to acquire the voltage and current values ​​of the input voltage source of the power supply circuit.

[0009] Optionally, the switch input detection circuit includes multiple identical detection branches, each of which is composed of an optocoupler.

[0010] Optionally, the communication circuit includes a CAN communication circuit and an RS422 communication circuit.

[0011] Optionally, the onboard temperature detection circuit includes a temperature sensor disposed on the PCB board of the controller.

[0012] This invention provides an airborne deployment timing control system with multiple control modes, including optical isolation drive technology, ARM-based multi-bus integrated design technology, and multi-channel voltage / state feedback detection integrated design technology. It successfully achieves product integration, miniaturization, lightweighting, and cableless operation, alleviating the technical problems of low reliability and high control difficulty in existing technologies. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0014] Figure 1 A schematic diagram of an airborne delivery timing control system with multiple control modes provided for an embodiment of this utility model; Figure 2 An ignition load isolation drive circuit diagram provided for an embodiment of this utility model; Figure 3 A negative terminal master control isolation drive circuit diagram provided for an embodiment of this utility model; Figure 4 A circuit diagram of a 5V power supply provided for an embodiment of this utility model; Figure 5 A circuit diagram of a 3.3V power supply provided for an embodiment of this utility model; Figure 6 An ignition power supply circuit diagram provided for an embodiment of this utility model; Figure 7 An ignition voltage and current detection circuit diagram provided for an embodiment of this utility model; Figure 8 A bus current and voltage acquisition circuit diagram provided for an embodiment of this utility model; Figure 9 A circuit diagram for detecting switch input is provided for an embodiment of this utility model; Figure 10 A CAN communication circuit diagram provided for an embodiment of this utility model; Figure 11 An RS422 communication circuit diagram provided for an embodiment of this utility model; Figure 12 A circuit diagram of an onboard temperature detection circuit provided for an embodiment of this utility model; Figure 13 A block diagram of a self-organizing network system provided for an embodiment of this utility model; Figure 14 An encoding logic diagram provided for an embodiment of this utility model; Figure 15 A power-on self-test flowchart provided for embodiments of this utility model; Figure 16 A periodic self-test flowchart is provided for embodiments of this utility model; Figure 17 A maintenance self-test flowchart is provided for an embodiment of this utility model.

[0015] In the diagram: 1. Controller; 2. Power supply circuit; 21. Ignition power supply circuit; 22. Working power supply circuit; 23. Ignition power supply line; 3. Switch input detection circuit; 4. Ignition voltage and current detection circuit; 41. Ignition current data acquisition circuit; 42. Ignition voltage data acquisition circuit; 5. Isolation drive circuit; 51. Ignition load isolation drive circuit; 52. Negative terminal master control isolation drive circuit; 6. Output detection circuit; 7. Communication circuit; 71. CAN communication circuit; 72. RS422 communication circuit; 8. In-application programming circuit; 9. Onboard temperature detection circuit; 10. Flight control computer; 11. Bus current and voltage acquisition circuit; 12. Lightning protection circuit. Detailed Implementation

[0016] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0017] Figure 1 This is a schematic diagram of an airborne deployment timing control system with multiple control modes according to an embodiment of the present utility model. For example... Figure 1 As shown, it includes: controller 1, power supply circuit 2, switch input detection circuit 3, ignition voltage and current detection circuit 4, isolation drive circuit 5, output detection circuit 6, communication circuit 7, in-application programming circuit 8, and onboard temperature detection circuit 9.

[0018] Specifically, the power supply circuit 2 includes an ignition power supply circuit 21 and a working power supply circuit 22; the output terminal of the ignition power supply circuit 21 is connected to the ignition power supply line 23, the ignition voltage and current detection circuit 4 is set on the ignition power supply line 23, the other end of the ignition power supply line 23 is connected to the input terminal of the isolation drive circuit 5, the output terminal of the isolation drive circuit 5 is connected to the load to be ignited, and the output detection circuit 6 is set at the output terminal of the isolation drive circuit 5.

[0019] The output of the power supply circuit 22 is connected to the controller 1. The input of the switch input detection circuit 3 is connected to the flight control computer 10 and the ignition load. The output of the switch input detection circuit 3 is connected to the controller 1. The controller 1 is connected to the control terminal of the isolation drive circuit 5. The controller 1 is also connected to the communication circuit 7, the application programming circuit 8 and the onboard temperature detection circuit 9 respectively. The communication circuit 7 is also connected to the flight control computer 10.

[0020] Preferably, the controller 1 includes an ARM chip. Optionally, the model number is CS32F407ZG.

[0021] Specifically, the isolation drive circuit 5 includes a multi-channel ignition load isolation drive circuit 51 and a negative terminal master control isolation drive circuit 52; the multi-channel ignition load isolation drive circuit 51 is located on the positive line of the ignition power line 23, and the negative terminal master control isolation drive circuit 52 is located on the negative line of the ignition power line 23.

[0022] Figure 2 This is a circuit diagram of an ignition load isolation drive according to an embodiment of the present invention. Figure 3 This is a diagram of a negative-terminal master control isolation drive circuit according to an embodiment of the present invention. Figure 2and Figure 3 As shown, the multi-channel ignition load isolation drive circuit 51 includes a high-side MOSFET and an optocoupler; the negative-side master control isolation drive circuit 52 includes a low-side MOSFET and an optocoupler. Specifically, the isolation drive circuit 5 uses the same circuit, employing both high-side and low-side MOSFETs as power switches to improve reliability. The MOSFET driver uses an opto-isolated circuit, which minimizes size and PCB area. The power switch is controlled by bus commands.

[0023] When the ARM receives a control command from the front end, it first checks if the low-side MOSFET is off, then checks if the high-side MOSFET is off. When both the high-side and low-side MOSFETs are off, the low-side MOSFETs Q40 and Q39 are turned on first. The ARM can determine the on / off state via pin 4 of U76; a low level indicates on, and a high level indicates off. When pin 4 of U76 is low, the bus command is executed to control the high-side MOSFET via optocoupler U7. The control timing can be directly sampled back through circuit U12. When the ignition power supply outputs 7V, optocoupler U12 is turned on, and pin 4 will change from high to low. The duration of this transition is read in real time by the ARM chip; this information represents the ignition on / off time. The control timing is checked for correctness based on the sampled information in the periodic and maintenance BITs, and the execution and feedback data are recorded to the internal FLASH.

[0024] Preferably, the operating power supply 22 includes a 5V power supply and a 3.3V power supply. Figure 4 This is a circuit diagram of a 5V power supply according to an embodiment of the present invention. Figure 5 This is a circuit diagram of a 3.3V power supply according to an embodiment of the present invention. Figure 6 This is a circuit diagram of an ignition power supply according to an embodiment of the present invention. The power supply circuit 2 provided in this embodiment of the present invention uses three power supplies, and power conversion is achieved through a dedicated power supply module.

[0025] Specifically, such as Figure 1 As shown, the ignition voltage and current detection circuit 4 includes an ignition current data acquisition circuit 41 and an ignition voltage data acquisition circuit 42; wherein, the ignition current data acquisition circuit 41 is connected in series on the ignition power line 23, and the ignition voltage data acquisition circuit 42 is connected in parallel on the two poles of the ignition power line 23.

[0026] Figure 7 This is a circuit diagram for detecting ignition voltage and current according to an embodiment of the present utility model. Figure 7As shown, the ignition voltage and current detection circuit 4 uses a dedicated current isolation sampling chip to sample the ignition current. Since the ignition power supply is a constant voltage power supply, too many resistors in series in the ignition circuit can lead to insufficient ignition power and the risk of failure to ignite. Using this circuit for sampling can reduce the power loss of the ignition power supply and improve the reliability of the timing control system. Ignition voltage sampling uses voltage divider resistors.

[0027] Specifically, such as Figure 1 As shown, it also includes a bus current and voltage acquisition circuit 11, which is located at the input end of the power supply circuit 2 and is used to acquire the voltage and current values ​​of the input voltage source of the power supply circuit 2. Figure 8 This is a circuit diagram for acquiring bus current and voltage according to an embodiment of the present utility model. Figure 8 As shown, the bus current and voltage acquisition circuit 11 acquires the voltage and current output data of the 28V input power supply and ignition power supply, records them to the internal FLASH, and uploads them to the front-end device via the bus during maintenance self-test.

[0028] Specifically, such as Figure 1 As shown, the input terminal of the bus current and voltage acquisition circuit 11 is also equipped with a lightning protection circuit 12.

[0029] Figure 9 This is a circuit diagram for detecting a switch input according to an embodiment of the present utility model. Figure 9 As shown, the digital input detection circuit 3 includes multiple identical detection branches, each composed of an optocoupler. Specifically, the digital input detection circuit 3 uses optocouplers to isolate external signals when acquiring the input signal. When the external signal is high, the fourth pin of the optocoupler changes from high to low, transmitting the signal to the ARM for acquisition, thus completing the signal isolation and conversion. The timing control system internally employs multiple identical circuits to acquire external input signals, isolating other external interference signals and improving the stability of module operation.

[0030] Specifically, such as Figure 1 As shown, the communication circuit 7 includes a CAN communication circuit 71 and an RS422 communication circuit 72. Figure 10 This is a CAN communication circuit diagram provided according to an embodiment of the present utility model. Figure 11 This is an RS422 communication circuit diagram provided according to an embodiment of the present utility model. For example... Figure 10 and Figure 11 As shown, the RS422 bus and CAN bus use dedicated interface chips with isolation capabilities. Both chips operate in a high-impedance state when there is no data transmission requirement, ensuring no impact on other nodes in the bus network. The ARM processor uses a self-developed serial communication protocol to control the communication process. The RS422 communication rate can reach a minimum of 16 Mbps, while the CAN communication rate can reach 1 Mbps.

[0031] Preferably, in this embodiment of the invention, the circuit diagram of the output detection circuit 6 is the same as that of the ignition voltage and current detection circuit 4. Figure 1 To that end, I will not elaborate further here.

[0032] Preferably, in this embodiment of the invention, the application programming circuit 8 uses a CAN communication circuit, and the IAP download communication protocol is used to perform secure read and write operations on the ARM's internal FLASH. The IAP program based on the CAN communication protocol, along with an upgraded host computer, supports the burning and uninstallation of executable programs in bin and hex formats, is compatible with STM32F4 and STM32F1 hardware platforms, can independently upgrade the device software according to the CAN communication node, and supports downloading and reading internal FLASH data within the node.

[0033] Specifically, the onboard temperature detection circuit 9 includes a temperature sensor mounted on the PCB of the controller 1. Figure 12 This is a circuit diagram of an onboard temperature detection circuit according to an embodiment of the present utility model. Figure 12 As shown, the onboard temperature detection circuit 9 uses a dedicated onboard temperature sensor to collect the temperature on the PCB board. The measurement range is -40℃ to 125℃, with an error range of ±1.5℃. It measures and records the temperature data, and generates and records the temperature change rate at each BIT cycle.

[0034] Based on the network collaborative working logic of the timing control system, and leveraging the internally integrated CAN bus communication circuit, eight timing control systems are internally self-organized into a network. The self-organizing network system block diagram is as follows: Figure 13 As shown. Based on the predetermined CAN address issued by the system, upon initial power-on, the system self-checks whether it already contains timing control system encoding and broadcasts it to other timing control systems via the MCU and the system's CAN protocol. If it does not contain encoding, it will... Figure 14 The encoding logic diagram extracts its own encoded value and records it.

[0035] When an emergency control command is detected, the network working mode is triggered (the network working mode will only be triggered when two or more timing control systems receive an emergency command signal). The network working mode is based on the sequence number extracted in the self-test BIT program for fixed address self-matching and networking. The host executes the command sent by the host computer via the CAN bus and the preset command inside the software and parses it. After parsing, the host sends the command to the seven slave devices via the CAN bus. The slave devices only receive and execute the host command via the CAN bus, ensuring that there is only one pulse output for the same load.

[0036] The timing control system provided in this embodiment integrates three BIT modes to perform BIT and module health monitoring on various parameters within the equipment during power-on self-test, periodic self-test during control, and maintenance self-test. During the timing output interval, the periodic self-test BIT is used to confirm the online status of the pyrotechnic device. When the status of the pyrotechnic device is inconsistent with the command requirements, the equipment stops working, ensuring the stability of the timing control system and real-time monitoring and controllable status of various parameters. Power-on self-test, such as... Figure 15 As shown. Periodic self-test as follows. Figure 16 As shown, maintenance self-test is as follows Figure 17 As shown.

[0037] As can be seen from the above description, the airborne delivery timing control system with multiple control modes provided by this utility model embodiment has the following technical effects: 1. It has the function of identifying load type, including dozens of types of loads such as actual loads and simulated loads, and uploads the data to the front-end control equipment via RS422 bus; II. It has pulse output control function, with a command issuance to pulse output response time of ≤60ms, pulse width of 40(1+2.5%)ms, pulse interval of an integer multiple of 0.1s, not exceeding 10s, and pulse interval accuracy of ≤±5%. Third, it supports two control output modes: communication control and emergency button control; IV. Emergency mode self-matching function: Under CAN communication bus conditions, in emergency working mode, the 8 delivery control circuit boards can coordinate and match the pulse generation timing in a 1 master and 7 slave configuration to ensure that only one pulse is output within the same micro-time. 5. It has health management functions, which can monitor and record basic status parameters of the equipment such as temperature, current and voltage, and support fault analysis and health management; VI. It has data recording and playback functions, enabling the measurement and storage of key information such as pulse width, response time, and pulse generation time; VII. It has supporting data offloading and ground playback analysis functions; 8. It has an online loading function to support online loading and upgrading of internal software (including microcontroller programs, etc.).

[0038] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0039] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An airborne delivery timing control system with multiple control modes, characterized in that, include: The circuit includes a controller, power supply circuit, digital input detection circuit, ignition voltage and current detection circuit, isolation drive circuit, output detection circuit, communication circuit, in-process programming circuit, and onboard temperature detection circuit; among which, The power supply circuit includes an ignition power supply circuit and a working power supply circuit; the output terminal of the ignition power supply circuit is connected to the ignition power supply line, the ignition voltage and current detection circuit is set on the ignition power supply line, the other end of the ignition power supply line is connected to the input terminal of the isolation drive circuit, the output terminal of the isolation drive circuit is connected to the load to be ignited, and the output detection circuit is set at the output terminal of the isolation drive circuit. The output terminal of the power supply circuit is connected to the controller; the input terminal of the switch input detection circuit is connected to the flight control computer and the ignition load; the output terminal of the switch input detection circuit is connected to the controller; the controller is connected to the control terminal of the isolation drive circuit; the controller is also connected to the communication circuit, the in-application programming circuit and the onboard temperature detection circuit respectively; the communication circuit is also connected to the flight control computer.

2. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The controller includes an ARM chip.

3. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The isolation drive circuit includes a multi-channel ignition load isolation drive circuit and a negative terminal master control isolation drive circuit; the multi-channel ignition load isolation drive circuit is disposed on the positive line of the ignition power line, and the negative terminal master control isolation drive circuit is disposed on the negative line of the ignition power line. The multi-channel ignition load isolation drive circuit includes a high-side field-effect transistor and an optocoupler; the negative-side master control isolation drive circuit includes a low-side field-effect transistor and an optocoupler.

4. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The ignition voltage and current detection circuit includes an ignition current data acquisition circuit and an ignition voltage data acquisition circuit; the ignition current data acquisition circuit is connected in series on the ignition power line, and the ignition voltage data acquisition circuit is connected in parallel on the two poles of the ignition power line.

5. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: It also includes a bus current and voltage acquisition circuit, which is located at the input end of the power supply circuit and is used to acquire the voltage and current values ​​of the input voltage source of the power supply circuit.

6. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The switch input detection circuit includes multiple identical detection branches, each of which is composed of an optocoupler.

7. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The communication circuit includes a CAN communication circuit and an RS422 communication circuit.

8. The airborne delivery timing control system with multiple control modes according to claim 1, characterized in that: The onboard temperature detection circuit includes a temperature sensor mounted on the PCB of the controller.

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