Flying object launching system wireless driving control device and testing method thereof

Abstract

The invention provides a wireless drive control device of a flyer launching system and a test method thereof, and relates to the field of flyer launching system control. In the wireless driving control device, a power supply module supplies alternating current to an emission controller and supplies direct current to a remote controller; the remote controller can be in wireless communication with the emission controller so as to send an emission command to the emission controller, the emission controller transmits the received emission command to the electric igniter, and after the electric igniter receives an emission signal, the automaton is controlled to achieve emission of a flyer by the aircraft cannon. Wired connection shooting can be achieved through the launching controller, the 20-meter distance limitation defect of wired connection and the voltage attenuation problem of limited connection can be eliminated, wireless control shooting is achieved through remote operation (within 5 kilometers) of the far-end controller, on one hand, the safety of operators is improved, and on the other hand, the safety of the operators is improved. And on the other hand, the remote operation capability of the system is improved, and the arrangement performance of the system is optimized.

Description

Technical Field

[0001] The present invention belongs to the technical field of flying object launch system control, and in particular relates to a wireless drive control device for a flying object launch system and a testing method for the device. Background Art

[0002] A certain aircraft-borne flying object launch system uses a mechanical trigger-type starting mechanism to launch flying objects. During the complete working cycle, the gas working fluid drives the actuator assembly to complete a series of mechanical actions such as system unlocking, component reset, material removal, new part loading and system locking.

[0003] This system is primarily used for short-range defense missions, using an electronic control unit to remotely control detonation and energy loading. Its control unit includes a power supply module, a launch controller, wires, an electric ignition unit, and an automatic machine. The power supply module provides +24V power to the launch controller, which is responsible for energy loading and trigger command processing. Its output is connected to the electric ignition unit, which is installed inside the automatic machine. The electric ignition unit receives signals from the launch controller. When powered on, the electromagnetic field of the coil causes the electromagnet core of the electric ignition unit to move 2.4-2.7mm, lifting the trigger rocker arm. The trigger rocker arm rotates around its axis, pressing the trigger down. Pressing the trigger releases the striker barrel, actuating the system.

[0004] The existing flight control system uses wired connection, such as Figure 1 As shown, the launch controller is connected to the plug of an electric ignition machine via a wire. During operation, the operator operates the launch controller's load and fire buttons, transmitting signals via the wires to the electric ignition machine, thereby completing system control. Considering the safety requirements of dynamic testing and actual application scenarios, as well as the voltage attenuation characteristics of cable transmission, the current design limits the connection distance between the launch controller and the electric ignition machine to 20 meters.

[0005] The current wired control solution has significant limitations: first, the 20-meter physical connection distance severely restricts the system's remote operation capabilities and mobile deployment flexibility; second, operators must implement control within a close range, which poses potential safety risks; third, the reliability and anti-interference capabilities of the cable connection method in complex environments need to be improved, which restricts the overall performance optimization of the system. Summary of the Invention

[0006] The purpose of the present invention is to solve the above-mentioned problems existing in the existing aviation airborne flying object launch system using a wired control solution, and to provide a flying object launch system wireless drive control device and a testing method for the device.

[0007] To achieve the above objectives, the technical solutions provided by the present invention are:

[0008] On the one hand, a wireless drive control device for a flying object launch system is provided, comprising a power supply module, a remote controller, a launch controller, an electric igniter, and an automatic machine. The power supply module is used to supply alternating current (AC) to the launch controller and direct current (DC) to the remote controller. The remote controller is capable of wirelessly communicating with the launch controller to send a launch command to the launch controller. The launch controller transmits the received launch command to the electric igniter. After receiving the launch signal, the electric igniter controls the automatic machine to launch the flying object with the aircraft cannon.

[0009] The launch controller includes a housing A1 and a wireless transmission module WXA, a switching power supply module, a firing control circuit board, a first switch module, a relay module, and a first socket module mounted on the housing A1; the switching power supply module is used to convert AC power into DC power to provide power for the firing control circuit board and the electric igniter; the first switch module includes a firing switch SA1, a firing safety switch SA2, a remote control switch SA3, a charging switch SA4, and a system power-on switch SA5; the relay module includes relays K1, K2, K3, K4, and K5; the firing control circuit board is used to achieve single-shot firing of a flying object by controlling the duration of the relay K2 being on; the first socket module includes sockets XS2, XS3, and XS4; the remote control switch SA3 is used to control the on and off of the wireless transmission module WXA, and the system power-on switch SA5 is used to control the powering of the launch controller;

[0010] Relay K1 controls the on / off power of the solenoid valve for the nitrogen filling cylinder of the aircraft machine gun, and the charging switch SA4 controls the on / off power of relay K1; relay K2 controls the on / off power of the electromagnetic coil of the electric ignition machine; relay K3 controls the on / off power of the switching power supply module; relay K4 is connected in series with the power supply circuit of the electric ignition machine coil, and the firing safety switch SA2 controls the on / off power of relay K4; relay K5 is arranged at the signal input end of the firing control circuit board, and the firing switch SA1 controls the on / off power of relay K5; the jack at one end of the socket XS2 is electrically connected to the aircraft machine gun, and the jack at the other end is electrically connected to relays K1 and K4; the jack at one end of the socket XS3 is electrically connected to the switching power supply module, and the other end is plugged into the plug on the firing control circuit board; socket XS4 is used to connect a communication cable so that the wireless transmission module WXA receives wireless signals;

[0011] The remote controller includes a housing B1 and a wireless transmission module WXB, a second switch module, and a second socket module mounted on the housing B1. The second switch module includes a switch SB1, a system power switch SB2, a trigger protection switch SB3, a trigger switch SB4, and a charge switch SB5, all of which are connected to the wireless transmission module WXB. The second socket module includes a socket XS1 and a socket XS5.

[0012] Switch SB1 controls the power on and off of the wireless transmission module WXB; the system power switch SB2 is used to remotely control the power on of the launch controller; the firing protection switch SB3 remotely controls the firing protection relay; the firing switch SB4 remotely controls the firing of the flying object; the charging switch SB5 remotely controls the charging of the bullet; the socket XS1 is used to provide DC power and is electrically connected to the switch SB1; the socket XS5 is used to connect the communication cable to enable wireless transmission between the wireless transmission module WXB and the wireless transmission module WXA.

[0013] Furthermore, the switching power supply module includes a switching power supply DW1 and a switching power supply DW2. The switching power supply DW1 outputs +15V DC power to provide power for the shooting control circuit board, and the switching power supply DW2 outputs +27V DC power to provide power for the electric ignition machine.

[0014] Furthermore, the launch controller also includes a voltmeter V1 and an ammeter A. The voltmeter V1 is used to measure the working voltage of the switching power supply DW2. The ammeter A is connected to the socket XS2 and is used to measure the current value of the electric ignition coil when the launch controller is fired.

[0015] Furthermore, the launch controller also includes an indicator light module, which includes a power supply indicator light HL1, a front position indicator light HL3, a rear position indicator light HL4 and a charging indicator light HL5; the power supply indicator light HL1 indicates whether the power supply of the switching power supply DW2 is normal; the front position indicator light HL3 indicates the front position indication signal of the aircraft machine gun fed back by the electric ignition machine, and the light is on when the aircraft machine gun is in the front position; the rear position indicator light HL4 indicates the rear position indication signal of the aircraft machine gun fed back by the electric ignition machine, and the light is on when the aircraft machine gun is in the rear position; the charging indicator light HL5 indicates whether the launch controller is in the charging state, and the light is on when it is in the charging state.

[0016] Furthermore, the transmitting controller also includes a power filter XS for filtering the AC power provided by the power supply module.

[0017] Furthermore, the remote controller also includes a voltmeter V2 for measuring the voltage value of the direct current provided by the power supply module.

[0018] Furthermore, the remote controller is powered by a battery, and the socket XS1 is electrically connected to the battery.

[0019] Furthermore, the wireless drive control device also includes a shell, which is divided into two compartments by a partition, and the transmitting controller and the remote controller are respectively accommodated therein, and the battery and the remote controller are accommodated in the same compartment.

[0020] Furthermore, both the system power-on switch SA5 and the system power-on switch SB2 are provided with indicator lights for indicating whether the power-on of the transmitting controller is normal.

[0021] Another aspect provides a method for testing the wireless drive control device of the above-mentioned flying object launch system, comprising the following steps:

[0022] Step 1: Connect the launch controller, the aircraft cannon charging cylinder, and the electric ignition machine through wires;

[0023] Step 2: Connect the transmitter controller to an AC 220V power supply, and connect the remote controller to a DC power supply;

[0024] Step 3, using the launch controller to control the aircraft cannon to fire, includes the following sub-steps:

[0025] Step 3.1, turn on the system power switch SA5;

[0026] Step 3.2, operate the charging switch SA4 to perform the charging operation;

[0027] Step 3.3, turning on the firing safety switch SA2;

[0028] Step 3.4, turn on the firing switch SA1 to shoot;

[0029] Step 4, using the remote controller to control the aircraft cannon to fire, includes the following sub-steps:

[0030] Step 4.1: Turn on the remote control switch SA3 on the transmitter controller;

[0031] Step 4.2, turn on switch SB1 on the remote controller to power on the remote controller;

[0032] Step 4.3: Turn on the system power switch SB2 to remotely power on the transmitter controller.

[0033] Step 4.4, press the charging switch SB5 to start the charging operation;

[0034] Step 4.5, turn on the firing protection switch SB3;

[0035] Step 4.6, turn on the firing switch SB4 to shoot.

[0036] The advantages of the present invention are:

[0037] The wireless driving control device of the flying object launch system proposed in the present invention is equipped with a wireless transmission module in the launch controller, and also provides a remote controller also equipped with a wireless transmission module. The remote controller can communicate wirelessly with the launch controller. Therefore, the present invention can not only realize wired connection shooting through the launch controller, but also eliminate the 20-meter distance limitation defect of the wired connection and the voltage attenuation problem of the limited connection. Wireless control shooting is realized through remote operation (within 5 kilometers) of the remote controller, which on the one hand improves the safety of the operator, and on the other hand increases the remote operation capability of the system and optimizes the system sorting performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The above and / or other features and advantages of the present invention will become more readily understood through the following description with reference to the accompanying drawings, which are not drawn to scale and in which some features are exaggerated or minimized to show details of particular components.

[0039] Figure 1 This is a working block diagram of the control device using wired connection mode for the existing aircraft cannon firing control;

[0040] Figure 2 This is a working block diagram of the wireless drive control device of the flying object launch system of the present invention;

[0041] Figure 3 It is a schematic diagram of the panel of the transmitting controller in the present invention;

[0042] Figure 4 This is a wiring diagram of the transmitter controller panel in the present invention;

[0043] Figure 5 This is a wiring diagram of the transmitter controller box in the present invention;

[0044] Figure 6 is a schematic diagram of a panel of a remote controller in the present invention;

[0045] Figure 7 This is a wiring diagram of the remote controller in the present invention. DETAILED DESCRIPTION

[0046] The present invention will be described in detail below with reference to the accompanying drawings by means of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is only for the purpose of illustration and is not intended to limit the present invention.

[0047] It should be pointed out that, in the context of the present invention, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "inside", "outside", "clockwise" and "counterclockwise" etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operate in a specific direction, and therefore should not be understood as limiting the present invention.

[0048] Furthermore, terms such as "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or to implicitly indicate the quantity of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features.

[0049] The present invention provides a wireless driving control device for a flying object launching system and a testing method for the device. On the one hand, the wired connection between the launching controller and the electric ignition machine can be used to realize the wired connection shooting of the flying object by an aircraft machine gun. On the other hand, the wireless control shooting of the flying object by the aircraft machine gun can be realized by utilizing the wireless communication between the remote controller and the launching controller.

[0050] First, the wireless driving control device for the flying object launching system provided by the present invention is described.

[0051] Reference Figure 2 As an exemplary embodiment of the present invention, the wireless driving control device of the flying object launching system includes a power supply module, a remote controller, a launching controller, an electric igniter and an automatic machine. The power supply module is used to supply alternating current (AC) to the launching controller and direct current (DC) to the remote controller, in particular 220V AC. 24V DC can also be provided to the remote controller through a battery. The remote controller can communicate wirelessly with the launching controller to send a launch command to the launching controller. The launching controller transmits the received launch instruction to the electric igniter. After receiving the launch signal, the electric igniter controls the automatic machine to realize the launch of the flying object by the aircraft cannon. In addition, the aircraft cannon operation signal of the electric igniter can be fed back to the launching controller and fed back to the remote controller in real time. The operation status of the automatic machine can be determined by observing the indicator light of the remote controller.

[0052] Reference Figures 3 to 5The launch controller includes a housing A1 and a wireless transmission module WXA, a switching power supply module, a firing control circuit board, a first switch module, a relay module, and a first socket module installed on the housing A1. The housing A1 may include a box body and a panel for closing the box body, which cooperate to accommodate and fix the electronic components in the launch controller. A person skilled in the art will understand that the operating knobs and observation interfaces of the switches that need to be operated and the indicators that need to be observed in the launch control are installed on the panel for the operator to operate and observe. In addition, Chinese characters can be marked on the panel to explain the functions of the corresponding switches and indicator lights, such as Figure 3 shown.

[0053] The switching power supply module converts 220V AC power to DC power, which powers the firing control circuit board and the electric ignition device. Specifically, the switching power supply module includes switching power supply DW1 and switching power supply DW2. Switching power supply DW1 outputs +15V DC power to power the firing control circuit board, while switching power supply DW2 outputs +27V DC power to power the electric ignition device. The firing controller may also include a power filter XS to filter the AC power provided by the power supply module.

[0054] The first switch module includes a firing switch SA1, a firing safety switch SA2, a remote control switch SA3, a charging switch SA4, and a system power switch SA5. The relay module includes relays K1, K2, K3, K4, and K5. The firing control circuit board controls the duration of relay K2's on-state to enable single-shot firing of the flying object. The first socket module includes sockets XS2, XS3, and XS4. The remote control switch SA3 controls the power on and off of the wireless transmission module WXA, while the system power switch SA5 controls the power on of the launch controller. In other words, only when the system power switch SA5 is on can the other switches be turned on, thereby achieving the corresponding functions. The specific wiring method is well-known and mature technology.

[0055] Relay K1 controls the on / off power to the solenoid valve for the nitrogen filling cylinder of the aircraft cannon, while the charging switch SA4 controls the on / off power to relay K1. Relay K2 controls the on / off power to the electromagnetic coil of the electric igniter. Relay K3 controls the on / off power to the switching power supply module. Relay K4 is connected in series with the electric igniter coil power supply circuit, and the firing safety switch SA2 controls the on / off power to relay K4. Relay K5 is located at the signal input terminal of the firing control circuit board, and the firing switch SA1 controls the on / off power to relay K5. The socket XS2 at one end is electrically connected to the aircraft cannon to transmit firing signals and receive feedback signals indicating forward, rear, and charging positions. The socket at the other end is electrically connected to relays K1 and K4. The socket at one end of socket XS3 is electrically connected to the switching power supply module, while the other end connects to a plug on the firing control circuit board, allowing the switching power supply module, particularly switching power supply DW1, to power the firing control circuit board. Socket XS4 is used to connect a communication cable, allowing the wireless transmission module WXA to receive wireless signals.

[0056] In a specific embodiment of the present invention, the launch controller also includes a voltmeter V1 and an ammeter A. The voltmeter V1 is used to measure the working voltage of the switching power supply DW2. The ammeter A is connected to the socket XS2 and is used to measure the current value of the electric ignition coil when the launch controller is fired.

[0057] In order to facilitate the control of the launch controller and the aircraft machine gun during the control process, the launch controller may also include an indicator light module, which includes a power indicator light HL1, a front position indicator light HL3, a rear position indicator light HL4 and a charging indicator light HL5.

[0058] The power indicator HL1 indicates whether the switching power supply DW2 is supplying power normally. The forward position indicator HL3 indicates the forward position indication signal of the aircraft cannon fed back by the electric ignition device; the light on indicates that the aircraft cannon is in the forward position. The rear position indicator HL4 indicates the rear position indication signal of the aircraft cannon fed back by the electric ignition device; the light on indicates that the aircraft cannon is in the rear position. The charging indicator HL5 indicates whether the launch controller is charging; the light on indicates that the launch controller is charging. In addition, the system power switch SA5 may be equipped with an indicator light to indicate whether the launch controller is powered normally.

[0059] Reference Figures 6 and 7 The remote controller includes a housing B1 and a wireless transmission module WXB, a second switch module and a second socket module installed on the housing B1. Figure 6 As shown, similar to the housing A1, the housing B1 also realizes the installation of various components in the remote controller through the box body and the panel that closes the box body. Similarly, the operating knobs and observation interfaces of the switches that need to be operated and the indicators that need to be observed in the emission control are installed on the panel.

[0060] The second switch module includes a switch SB1, a system power switch SB2, a firing protection switch SB3, a firing switch SB4, and a charging switch SB5, all of which are connected to the wireless transmission module WXB. The second socket module includes a socket XS1 and a socket XS5.

[0061] Switch SB1 controls the power on and off of the wireless transmission module WXB. A switch with its own indicator light can be selected. In this way, when the wireless transmission module WXB is powered on, the indicator light of the switch SB1 will light up. The system power-on switch SB2 is used to remotely control the power-on of the launch controller. The system power-on switch SB2 can be equipped with an indicator light to indicate whether the power-on of the launch controller is normal. The firing protection switch SB3 remotely controls the firing safety switch SA2 and can also be equipped with an indicator light. The firing switch SB4 remotely controls the firing of the flying object. A button with its own indicator light can be selected as the firing switch SB4. The charging switch SB5 remotely controls the charging of the bullet. The socket XS1 is used to provide direct current and is electrically connected to the switch SB1. The socket XS5 is used to connect the communication cable to enable wireless transmission between the wireless transmission module WXB and the wireless transmission module WXA.

[0062] For ease of control, the remote controller is powered by a battery, and the socket XS1 is electrically connected to the battery. In addition, the remote controller also includes a voltmeter V2 for measuring the voltage value of the DC power provided by the power supply module.

[0063] To facilitate portability and transportation, the wireless drive control device provided herein may further include a housing (not shown). The housing is divided into two compartments by a partition. The transmitter controller and remote controller are housed in the two compartments, respectively. The battery and remote controller may be housed in the same compartment. The housing may comprise a housing and a lid, with the compartments located within the housing and the lid being capable of opening and closing relative to the housing.

[0064] Next, the test method of the wireless driving control device of the flying object launch system provided by the present invention is described, which includes the following steps:

[0065] Step S1, connecting the launch controller, the aviation cannon charging cylinder and the electric ignition machine together through wires;

[0066] Step S2, connecting the transmitting controller to an AC 220V power supply, and connecting the remote controller to a DC power supply;

[0067] Step S3, using a launch controller to control the aircraft cannon to fire;

[0068] Step S4, using the remote controller to control the aircraft machine gun to fire.

[0069] Step S3 may specifically include the following sub-steps:

[0070] Step S3.1, turn on the system power switch SA5;

[0071] Step S3.2, operate the charging switch SA4 to perform the charging operation;

[0072] Step S3.3, turning on the firing safety switch SA2;

[0073] Step S3.4: Turn on the firing switch SA1 to shoot, thereby realizing the wired shooting function.

[0074] In addition, step S4 may specifically include the following sub-steps:

[0075] Step S4.1, turning on the remote control switch SA3 on the transmitting controller;

[0076] Step S4.2: Turn on switch SB1 on the remote controller to power on the remote controller. After powering on, if the voltage on the remote controller display is within the range of +24V±1V, you can proceed to the next step of operating the "System Power On" button.

[0077] Step S4.3: Turn on the system power switch SB2 to remotely power on the transmitter controller. After the power is successfully powered on, a feedback information is fed back to the remote controller system power indicator. The indicator lights up, indicating that the transmitter controller is powered on normally.

[0078] Step S4.4: Press the charging switch SB5 to start the charging operation, and the gun responds to the charging;

[0079] Step S4.5: Turn on the firing protection switch SB3. The firing safety switch SA2 on the launch controller responds and transmits a notification message to the remote controller. The "firing protection" indicator light on the remote controller lights up.

[0080] Step S4.6, turn on the firing switch SB4 to shoot, the firing switch SA1 on the launch controller responds and transmits a feedback message to the remote controller, and the "firing" indicator light on the remote controller lights up, thereby realizing the wireless control shooting function.

[0081] Therefore, as described above, the wireless driving control device of the flying object launch system of the present invention is equipped with a wireless transmission module in the launch controller, and also provides a remote controller that is also equipped with a wireless transmission module. The remote controller can communicate wirelessly with the launch controller. Therefore, the present invention can not only realize wired connection shooting through the launch controller, but also eliminate the 20-meter distance limitation defect of the wired connection and the voltage attenuation problem of the limited connection. Wireless control shooting is achieved through remote operation (within 5 kilometers) of the remote controller, which on the one hand improves the safety of the operator, and on the other hand increases the remote operation capability of the system and optimizes the system sorting performance.

[0082] Finally, it should be noted that the features mentioned and / or illustrated in the above description of the exemplary embodiments of the present invention may be incorporated into one or more other embodiments in the same or similar manner, combined with features in other embodiments, or substituted for corresponding features in other implementations. The technical solutions obtained by such combination or substitution shall also be deemed to be included in the scope of protection of the present invention.

Claims

1. A wireless drive control device for a flying object launch system, characterized by: The invention comprises a power supply module, a remote controller, a launch controller, an electric igniter, and an automatic machine; the power supply module is used to supply alternating current to the launch controller and direct current to the remote controller; the remote controller is capable of wirelessly communicating with the launch controller to send a launch command to the launch controller, the launch controller transmits the received launch command to the electric igniter, and the electric igniter, upon receiving the launch signal, controls the automatic machine to enable the aircraft cannon to launch the flying object; The launch controller includes a shell A1 and a wireless transmission module WXA, a switching power supply module, a shooting control circuit board, a first switch module, a relay module and a first socket module installed on the shell A1; the switching power supply module is used to convert AC power into DC power to provide power for the shooting control circuit board and the electric igniter; the first switch module includes a firing switch SA1, a firing safety switch SA2, a remote control switch SA3, a charging switch SA4, and a system power-on switch SA5; the relay module includes relay K1, relay K2, relay K3, relay K4 and relay K5; the shooting control circuit board is used to achieve single-shot shooting of the flying object by controlling the connection time of relay K2; the first socket module includes socket XS2, socket XS3 and socket XS4; the remote control switch SA3 is used to control the power on and off of the wireless transmission module WXA, and the system power-on switch SA5 is used to control the power on of the launch controller; The relay K1 controls the on and off power of the solenoid valve of the nitrogen filling cylinder of the aviation machine gun, and the charging switch SA4 controls the on and off power of the relay K1; the relay K2 controls the on and off power of the electromagnetic coil of the electric ignition machine; the relay K3 controls the on and off power of the switching power supply module; the relay K4 is connected in series with the power supply circuit of the electric ignition machine coil, and the firing safety switch SA2 controls the on and off power of the relay K4; the relay K5 is arranged at the signal input end of the shooting control circuit board, and the firing switch SA1 controls the on and off power of the relay K5; the jack at one end of the socket XS2 is electrically connected to the aviation machine gun, and the jack at the other end is electrically connected to the relays K1 and K4; the jack at one end of the socket XS3 is electrically connected to the switching power supply module, and the other end is plugged into the plug on the shooting control circuit board; the socket XS4 is used to connect a communication cable so that the wireless transmission module WXA receives wireless signals; The remote controller includes a housing B1 and a wireless transmission module WXB, a second switch module, and a second socket module mounted on the housing B1; the second switch module includes a switch SB1, a system power switch SB2, a firing protection switch SB3, a firing switch SB4, and a charging switch SB5, all of which are connected to the wireless transmission module WXB; the second socket module includes a socket XS1 and a socket XS5; The switch SB1 controls the power on and off of the wireless transmission module WXB; The system power switch SB2 is used to remotely control the power-on of the launch controller; the firing protection switch SB3 remotely controls the firing protection relay; the firing switch SB4 remotely controls the firing of the flying object; the charging switch SB5 remotely controls the charging; the socket XS1 is used to provide direct current and is electrically connected to the switch SB1; the socket XS5 is used to connect a communication cable to enable the wireless transmission module WXB and the wireless transmission module WXA to perform wireless transmission.

2. The wireless driving control device for a flying object launch system according to claim 1, characterized in that: The switching power supply module includes a switching power supply DW1 and a switching power supply DW2. The switching power supply DW1 outputs +15V DC power to provide power for the shooting control circuit board, and the switching power supply DW2 outputs +27V DC power to provide power for the electric igniter.

3. The wireless driving control device for a flying object launch system according to claim 2, characterized in that: The launch controller also includes a voltmeter V1 and an ammeter A. The voltmeter V1 is used to measure the working voltage of the switching power supply DW2. The ammeter A is connected to the socket XS2 and is used to measure the current value of the electric ignition coil when the launch controller is fired.

4. The wireless driving control device for a flying object launch system according to claim 2 or 3, characterized in that: The launch controller also includes an indicator light module, which includes a power supply indicator light HL1, a front position indicator light HL3, a rear position indicator light HL4 and a charging indicator light HL5; The power supply indicator light HL1 indicates whether the power supply of the switching power supply DW2 is normal; the front position indicator light HL3 indicates the front position indication signal of the aircraft machine gun fed back by the electric ignition machine, and the light is on when the aircraft machine gun is in the front position; the rear position indicator light HL4 indicates the rear position indication signal of the aircraft machine gun fed back by the electric ignition machine, and the light is on when the aircraft machine gun is in the rear position; the charging indicator light HL5 indicates whether the launch controller is in the charging state, and the light is on when it is in the charging state.

5. The wireless driving control device for a flying object launch system according to claim 1 or 2, characterized in that: The transmitting controller further includes a power filter XS for filtering the alternating current provided by the power supply module.

6. The wireless driving control device for a flying object launch system according to claim 1 or 2, characterized in that: The remote controller further includes a voltmeter V2 for measuring the voltage value of the direct current provided by the power supply module.

7. The wireless driving control device for a flying object launch system according to claim 1 or 2, characterized in that: The remote controller is powered by a battery, and the socket XS1 is electrically connected to the battery.

8. The wireless driving control device for a flying object launch system according to claim 7, characterized in that: The wireless driving control device further comprises a shell, which is divided into two compartments by a partition, and the transmitting controller and the remote controller are respectively accommodated therein, and the battery and the remote controller are accommodated in the same compartment.

9. The wireless driving control device for a flying object launch system according to claim 1 or 2, characterized in that: The system power-on switch SA5 and the system power-on switch SB2 are both provided with indicator lights for indicating whether the power-on of the transmitting controller is normal.

10. A method for testing a wireless driving control device for a flying object launch system according to any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1: Connect the launch controller, the aircraft cannon charging cylinder, and the electric ignition machine through wires; Step 2: Connect the transmitter controller to an AC 220V power supply, and connect the remote controller to a DC power supply; Step 3, using the launch controller to control the aircraft cannon to fire, includes the following sub-steps: Step 3.1, turn on the system power switch SA5; Step 3.2, operate the charging switch SA4 to perform the charging operation; Step 3.3, turning on the firing safety switch SA2; Step 3.4, turn on the firing switch SA1 to shoot; Step 4, using the remote controller to control the aircraft cannon to fire, includes the following sub-steps: Step 4.1: Turn on the remote control switch SA3 on the transmitter controller; Step 4.2, turn on switch SB1 on the remote controller to power on the remote controller; Step 4.3: Turn on the system power switch SB2 to remotely power on the transmitter controller. Step 4.4, press the charging switch SB5 to start the charging operation; Step 4.5, turn on the firing protection switch SB3; Step 4.6, turn on the firing switch SB4 to shoot.

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