Anti-radiation unmanned aerial vehicle launching control system and method
By using an Ethernet-based distributed network architecture and optical MOS relays, the insufficient automation and safety issues in anti-radiation UAV launch technology have been resolved, enabling rapid deployment and safe launch in multiple UAV types and mission scenarios.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-09
- Publication Date
- 2026-04-07
Smart Images
Figure CN121799701A_ABST
Abstract
Description
Technical Field
[0001] The embodiments of this application relate to the field of unmanned aerial vehicle (UAV) launch technology, and in particular to an anti-radiation UAV launch control system and method. Background Technology
[0002] Anti-radiation drones are specialized drones designed to counter critical electronic equipment such as radar systems and communication nodes. Currently, the mainstream launch method uses a rocket-assisted system, deploying a single drone via a vehicle-mounted launcher. However, with breakthroughs in drone platform technology and artificial intelligence algorithms, these devices have evolved into multi-mission configurations, including radar-guided, satellite-positioned, and electro-optical reconnaissance types. Their operational mode is shifting from precise single-drone output to saturated, coordinated cluster output. This multi-drone, multi-mission parallel mode places higher demands on the automation, scalability, and security capabilities of the launch system.
[0003] While current multi-drone launch technology has achieved breakthroughs in basic functions, significant technical bottlenecks still exist: In terms of the launch process, the existing solution requires manual intervention from command verification and status feedback to anomaly handling, which places strict requirements on the professional skills of the operators and lacks automation. In terms of scalability, existing solutions generally adopt a topology of a single launch control device corresponding to multiple UAVs. Due to limitations in interface type and number of channels, the system has poor scalability and cannot dynamically adjust the UAV configuration according to actual needs, which seriously restricts the ability to quickly deploy equipment in multi-type and multi-mission scenarios. In terms of safety, the ignition circuit of traditional booster rockets is susceptible to vibration and impact interference, which can cause malfunctions. It also has switching delays, making it difficult to accurately control the ignition sequence. In addition, it lacks an electrical interlock protection mechanism, which poses a major safety hazard to anti-radiation drones. Summary of the Invention
[0004] To address the aforementioned technical problems, embodiments of this application propose an anti-radiation unmanned aerial vehicle (UAV) launch control system and method, aiming to improve the automation level and rapid deployment flexibility of UAV launch technology.
[0005] To achieve the above objectives, embodiments of this application propose an anti-radiation unmanned aerial vehicle (UAV) launch control system. The system employs an Ethernet-based distributed network architecture and includes: Ground control station; At least one launch transport vehicle, and each launch transport vehicle is communicatively connected to the ground control station; Each launch transport vehicle carries: A launch control computer, which is connected to a distributed network; Multiple launch boxes are used to load drones, and the launch angle of the launch boxes is adjustable; Multiple pluggable launch control units are configured in the launch control computer and correspond one-to-one with the launch box or are connected according to a preset configuration. The type and number of launch control units can be configured according to the loaded UAV. The launch control unit is used to conduct two-way data interaction with the UAV through a communication interface and to control the launch box corresponding to the launch control unit; The ground control station is used to send one-click self-test commands and one-click launch commands to all launch control computers; the one-click self-test command is used to instruct the drone and / or launch box to perform a self-test, and the one-click launch command is used to instruct the launch box to launch the drone. The launch control computer is used to control each launch control unit to perform a self-test process on the corresponding UAV and launch box in sequence after receiving a one-click self-test command. After the self-test process, it controls each launch box to launch the UAV in sequence based on the one-click launch command.
[0006] Optionally, the launch control unit establishes bidirectional communication with the UAV via an RS422 serial interface to send remote control commands, mission planning information and self-test commands to the UAV, and to receive telemetry data and status information transmitted back by the UAV.
[0007] Optionally, the system also includes a network switch; the launch and transport vehicles are interconnected via network cables through the network switch to form a distributed network architecture based on Ethernet; the launch and transport vehicles communicate with the ground control station via fiber optic cables.
[0008] Optionally, the launch control unit integrates the ignition control circuit of the booster rocket, and the ignition control circuit uses an optical MOS relay as a switching element.
[0009] Optionally, the ignition control circuit adopts a multi-safety interlock mechanism and performs the ignition operation when the conditions corresponding to the multi-safety interlock mechanism are met; wherein the conditions corresponding to the multi-safety interlock mechanism include: the pre-launch condition is valid, the pre-ignition state is ready, and the ignition command is triggered.
[0010] This application provides an anti-radiation unmanned aerial vehicle (UAV) launch control system. The system is based on a distributed network architecture using Ethernet and includes: a ground control station; at least one launch transport vehicle, each connected to the ground control station; each launch transport vehicle is equipped with: a launch control computer connected to the distributed network; multiple launch boxes for loading UAVs, with adjustable launch angles; and multiple pluggable launch control units configured in the launch control computer, corresponding one-to-one with each launch box or connected according to a preset configuration. The type and number of launch control units can be configured according to the loaded UAVs. The launch control units are used to communicate with the UAVs via communication interfaces. The system features two-way data interaction and controls the launch canisters corresponding to the launch control units. The ground control station sends one-click self-test commands and one-click launch commands to all launch control computers. The one-click self-test command instructs the UAV and / or launch canister to perform a self-test, while the one-click launch command instructs the launch canister to launch the UAV. Upon receiving the one-click self-test command, the launch control computer controls each launch control unit to sequentially perform a self-test on the corresponding UAV and launch canister. After the self-test, based on the one-click launch command, it controls each launch canister to launch the UAV sequentially. This eliminates the need for manual intervention, thus improving the automation level of multi-UAV launch technology. Because the launch control units are pluggable, it enhances the rapid deployment capability of equipment in multi-mission scenarios.
[0011] To achieve the above objectives, embodiments of this application propose a method for controlling the launch of anti-radiation unmanned aerial vehicles (UAVs). The method includes: establishing a communication connection between each launch transport vehicle and a ground control station; sending a one-click self-test command from the ground control station to the launch control computers on all launch transport vehicles; wherein the one-click self-test command instructs the UAVs and / or launch containers to perform a self-test and reports the self-test results to the ground control station; after the self-test process, based on task priority, sorting and configuring task data for UAVs with normal self-test results in formation; sending a one-click launch command from the ground control station to all launch control computers; wherein the one-click launch command instructs each launch container to launch UAVs; wherein UAVs in the same formation launch simultaneously, and UAVs in different formations launch sequentially at intervals.
[0012] Optionally, the UAV can perform a self-test, including: sequentially performing a self-test on the UAV's flight control computer, servo motor, and engine through the launch control unit, sending a self-test command to the mission payload, and determining whether the returned status parameters are within a preset threshold range to generate a UAV self-test result; the launch control computer summarizes the self-test results of each UAV and reports them to the ground control station.
[0013] Optionally, the launch container is self-tested, including: sending self-test commands sequentially to the launch container cover locking device, engine starter, clutch, and booster rocket through the launch control unit, and judging whether the feedback signals of the mechanisms are normal within a preset time to generate launch container self-test results; the launch control computer summarizes the self-test results of each launch container and reports them to the ground control station.
[0014] To achieve the above objectives, embodiments of this application also propose an electronic device, including a processor and a memory, wherein the memory stores instructions executable by the processor, and the processor is configured to execute the instructions such that the electronic device can implement the anti-radiation UAV launch control method described above.
[0015] To achieve the above objectives, embodiments of this application also propose a computer-readable storage medium storing a computer program that, when executed by a processor, enables the implementation of an anti-radiation UAV launch control method as described above. Attached Figure Description
[0016] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies of this application will be briefly introduced below. Obviously, the following drawings are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. The drawings described herein are only used to explain this application and are not intended to limit this application.
[0017] Figure 1 This is an architecture diagram of an anti-radiation unmanned aerial vehicle launch control system provided in one embodiment of this application; Figure 2 This is a schematic diagram of a launch control system provided in one embodiment of this application; Figure 3 This is a schematic diagram of a launch control computer provided in one embodiment of this application; Figure 4 This is a structural block diagram of a launch control system provided in one embodiment of this application; Figure 5 This is a schematic diagram of an ignition control circuit for a booster rocket provided in one embodiment of this application; Figure 6 This is a flowchart of an anti-radiation unmanned aerial vehicle launch control method provided in another embodiment of this application; Figure 7 This is a flowchart of another anti-radiation UAV launch control method provided in another embodiment of this application; Figure 8This is a schematic diagram of the structure of an anti-radiation UAV launch control device provided in another embodiment of this application; Figure 9 This is a schematic diagram of the structure of an electronic device provided in another embodiment of this application. Detailed Implementation
[0018] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the various embodiments of this application will be described in detail below with reference to the accompanying drawings. Those skilled in the art will understand that many technical details have been presented in the embodiments of this application to facilitate better understanding. However, the technical solutions claimed in this application can be implemented even without these technical details and various variations and modifications based on the following embodiments. The division of the following embodiments is for ease of description and should not constitute any limitation on the specific implementation of this application. The following embodiments can be combined with and referenced by each other without contradiction.
[0019] Anti-radiation drones are specialized drones designed to counter critical electronic equipment such as radar systems and communication nodes. Currently, the mainstream launch method uses a rocket-assisted system, deploying a single drone via a vehicle-mounted launcher. However, with breakthroughs in drone platform technology and artificial intelligence algorithms, these devices have evolved into multi-mission configurations, including radar-guided, satellite-positioned, and electro-optical reconnaissance types. Their operational mode is shifting from precise single-drone output to saturated, coordinated cluster output. This multi-drone, multi-mission parallel mode places higher demands on the automation, scalability, and security capabilities of the launch system.
[0020] While current multi-drone launch technology has achieved breakthroughs in basic functions, significant technical bottlenecks still exist: In terms of the launch process, the existing solution requires manual intervention from command verification and status feedback to anomaly handling, which places strict requirements on the professional skills of the operators and lacks automation. In terms of scalability, existing solutions generally adopt a topology of a single launch control device corresponding to multiple UAVs. Due to limitations in interface type and number of channels, the system has poor scalability and cannot dynamically adjust the UAV configuration according to actual needs, which seriously restricts the ability to quickly deploy equipment in multi-type and multi-mission scenarios. In terms of safety, the ignition circuit of traditional booster rockets is susceptible to vibration and impact interference, which can cause malfunctions. It also has switching delays, making it difficult to accurately control the ignition sequence. In addition, it lacks an electrical interlock protection mechanism, which poses a major safety hazard to anti-radiation drones.
[0021] In view of this, this application proposes an anti-radiation unmanned aerial vehicle (UAV) launch control system and method, aiming to improve the automation level and rapid deployment capability of UAV launch technology.
[0022] The following is a detailed description of an anti-radiation unmanned aerial vehicle (UAV) launch control system proposed in one embodiment of this application.
[0023] like Figure 1 As shown, an embodiment of this application presents an architecture diagram of an anti-radiation unmanned aerial vehicle (UAV) launch control system. Figure 1 The system adopts an Ethernet-based distributed network structure, which includes: a ground control station 110 and at least one launch transport vehicle 120; each launch transport vehicle 120 is communicatively connected to the ground control station 110.
[0024] Each launch vehicle 120 is equipped with: a launch control computer 121, multiple launch boxes 122, and multiple pluggable launch control units 123. The launch control computer 121 is connected to a distributed network; the multiple launch boxes 122 are used to load UAVs, and the launch angle of the launch boxes 122 is adjustable; the multiple pluggable launch control units 123 are configured in the launch control computer 121 and correspond one-to-one with the launch boxes 122 or are connected according to a preset configuration, and the type and number of launch control units 123 can be configured according to the UAVs loaded. For example, such as Figure 2 As shown, Figure 2 This is a schematic diagram of a launch control system. Figure 2 At least one launch transport vehicle may include launch transport vehicle 1, launch transport vehicle 2, launch transport vehicle 3, ..., launch transport vehicle N.
[0025] For example, such as Figure 3 As shown, Figure 3 This is a schematic diagram of a launch control computer. Figure 3 The transmission control computer may include transmission control unit 1, transmission control unit 2, transmission control unit 3, transmission control unit 4, transmission control unit 5, ..., transmission control unit M. Where M ≤ N.
[0026] In one possible embodiment, the system further includes a network switch; the launch vehicles are interconnected via network cables through the network switch to form an Ethernet-based distributed network architecture; and the launch vehicles communicate with the ground control station via fiber optic cables.
[0027] For example, the system consists of a ground control station and several launch transport vehicles. These vehicles are interconnected via network cables and communicate with the ground control station via fiber optic cables. Each launch transport vehicle carries a launch control computer and N launch containers. Each launch container can hold one UAV, and the UAV mission types can be configured in various ways (e.g., radar-guided, satellite-positioned, and electro-optical reconnaissance). UAV status monitoring and launch operations are integrated within the launch container, and the launch angle can be adaptively adjusted according to the site environment. The launch control computer has M pluggable launch control units (M≤N) built-in. These units are connected via network switches, and their type and number can be flexibly configured, depending on the type and number of UAVs actually loaded.
[0028] In one possible embodiment, the launch control unit establishes bidirectional communication with the UAV via an RS422 serial interface to send remote control commands, mission planning information and self-test commands to the UAV, and to receive telemetry data and status information transmitted back by the UAV.
[0029] For example, the launch control unit establishes bidirectional communication with the UAV through an RS422 serial port: on the one hand, the ground control station sends remote control commands and mission planning information to the UAV through this interface, and at the same time receives telemetry data and mission planning results transmitted back by the UAV; on the other hand, the launch control unit can send self-test commands to the UAV through this serial port to perform pre-flight tests on key equipment such as the UAV flight control computer.
[0030] For example, Figure 4 This is a structural block diagram of a launch control system provided in one embodiment of this application; the ground control station communicates with each launch transport vehicle via Ethernet. The ground control station is mainly used for: formation, sorting, and flight path planning of all UAVs according to the UAV mission; issuing global commands to all launch transport vehicles, such as one-click self-test commands and one-click launch commands; receiving and displaying the self-test status and telemetry data of all UAVs and launch containers; issuing alarms (red warnings) for units with abnormal self-tests and making isolation decisions. In the launch transport vehicle, the launch control computer has M pluggable launch control units built-in, used for ignition control, launch container control, launch container detection, UAV detection, UAV remote control, and telemetry information transmission and reception. The self-test of the launch container may include detection of the launch container front cover, launch container rear cover, engine starter, booster rocket, and pre-launch detection of the launch angle. The self-test of the UAV may include pre-flight detection of key equipment such as the UAV flight control computer, inertial navigation system, servo equipment, power unit, and mission payload.
[0031] Before launching a drone, the first step is to select the appropriate drone model and quantity based on mission requirements and load them into the launch containers of each launch transport vehicle. Then, based on the type and quantity of drones, select the corresponding type and quantity of launch control units, insert them into the launch control computer's chassis, and connect them to a network switch via a network cable.
[0032] During site deployment and self-inspection, upon arrival at the launch site, the first step is to... Figure 2 As shown, the launch control computers on each launch transport vehicle are connected via a distributed network architecture and then connected to the network terminal of the ground control station via fiber optic cable. Next, the launch angles of each launch transport vehicle are adjusted according to the site deployment. After preparation, the ground control station sends a one-click self-test command to all launch transport vehicles to control the UAVs to perform self-tests. The launch control computer then performs pre-flight checks on key equipment such as the UAV flight control computer, inertial navigation system, servo equipment, power unit, and mission payload, and reports the results to the ground control station. Immediately afterwards, the ground control station sends a one-click self-test command to control the launch box to perform a self-test. The launch control computer performs pre-launch checks on the launch box front cover, launch box rear cover, engine starter, booster rocket, and launch angle, and reports the results. The entire self-test process strictly follows a request-response-acknowledgement mechanism to ensure that the test results meet the preset launch conditions. For UAVs or launch boxes with abnormal self-test results, on-site troubleshooting can be performed through the fault information displayed on the ground control station; if the fault cannot be resolved, the system will automatically isolate it and exclude it from subsequent processes. After all self-check procedures are completed, the ground control station organizes and sorts all the UAVs on the launch transport vehicle according to mission priority, and binds the mission planning data to each UAV. Finally, it enters the one-click launch control process. All self-checks and launch procedures are completed automatically by the launch control computer without human intervention.
[0033] In one possible embodiment, the launch control unit integrates the ignition control circuit of the booster rocket, and the ignition control circuit uses an opto-MOS relay as a switching element.
[0034] For example, an optical MOS relay is an electronic switch that uses light to control its on / off state. Because the input side (control signal) and the output side (rocket circuit) are isolated by light and have no electrical connection, this effectively prevents the high current and high voltage generated during rocket ignition from damaging the sensitive control chip, thereby improving the safety of the drone.
[0035] In one possible embodiment, the ignition control circuit employs a multiple safety interlock mechanism and performs the ignition operation only when the conditions corresponding to the multiple safety interlock mechanism are met. These conditions include: valid pre-launch conditions, pre-ignition readiness, and triggering of the ignition command.
[0036] like Figure 5 As shown, Figure 5 This is a schematic diagram of a booster rocket ignition control circuit provided in one embodiment of this application. In the booster rocket ignition control circuit, Q1 is a MOSFET, and OC1 is a dual-channel opto-MOSFET relay. These three opto-MOSFET relays are connected in series in the booster rocket's power supply circuit, meaning that current must flow through these three switches sequentially to ultimately reach the booster rocket. Specifically, the booster rocket's ignition circuit is directly integrated into the launch control unit, using opto-MOSFET relays instead of traditional electromagnetic relays. The ignition control employs a triple safety interlock protection mechanism, requiring the simultaneous fulfillment of three conditions: valid pre-launch conditions, pre-ignition readiness, and ignition command triggering, before the ignition operation can be executed.
[0037] Mission Planning and Launch: After the self-check passes, the ground control station, based on mission priority, groups, sorts, and plans the flight paths of all UAVs on the launch transport vehicle, and binds the mission planning data to each UAV. For example, A-1 represents the first UAV in formation A, B-2 represents the second UAV in formation B, and so on. At this point, the system enters the pre-launch phase, and the booster rocket pre-launch signal becomes active. Finally, the ground control station sends a "one-click launch" command. The launch control computer sequentially controls the opening of the launch canister, engine start, booster rocket pre-ignition, and ignition for launch. UAVs in the same formation launch simultaneously, with each formation executing sequentially at intervals according to the order A→B→C→D… until all UAVs have been launched. Successful ignition can only occur when the pre-launch conditions are valid, the pre-ignition status is active, and the ignition command is triggered—all three signals are simultaneously active (e.g., all three signals are high).
[0038] It is understood that, compared with existing technologies, the embodiments of this application adopt an Ethernet-based distributed architecture, which has high scalability, does not limit the type and number of UAVs, and can adapt to the rapid equipment deployment needs of multiple types and multiple mission scenarios. The launch control computer adopts a modular design, which can flexibly configure the launch control unit as needed, reducing hardware costs and enabling single-unit launch through a single launch control unit and a simple launcher when the launch transport vehicle cannot approach the target area, significantly improving the flexibility and convenience of mission deployment.
[0039] Moreover, the system possesses full-process self-testing capabilities, supports online fault diagnosis and isolation, and employs a strict request-response-acknowledgment mechanism for command transmission. All operations can be completed autonomously with a single click, resulting in a higher degree of automation. Furthermore, the booster rocket ignition circuit design utilizes optical MOS instead of electromagnetic relays, offering superior vibration and shock resistance, eliminating switching delays, and enabling precise control of ignition timing to ensure synchronization during multi-rocket coordinated launches. The ignition control employs a multi-level safety protection mechanism, significantly enhancing system reliability and safety.
[0040] This application provides an anti-radiation unmanned aerial vehicle (UAV) launch control system. The system is based on a distributed network architecture using Ethernet and includes: a ground control station; at least one launch transport vehicle, each connected to the ground control station; each launch transport vehicle is equipped with: a launch control computer connected to the distributed network; multiple launch boxes for loading UAVs, with adjustable launch angles; and multiple pluggable launch control units configured in the launch control computer, corresponding one-to-one with each launch box or connected according to a preset configuration. The type and number of launch control units can be configured according to the loaded UAVs. The launch control units are used to communicate with the UAVs via communication interfaces. The system features two-way data interaction and controls the launch canisters corresponding to the launch control units. The ground control station sends one-click self-test commands and one-click launch commands to all launch control computers. The one-click self-test command instructs the UAV and / or launch canister to perform a self-test, while the one-click launch command instructs the launch canister to launch the UAV. Upon receiving the one-click self-test command, the launch control computer controls each launch control unit to sequentially perform a self-test on the corresponding UAV and launch canister. After the self-test, based on the one-click launch command, it controls each launch canister to launch the UAV sequentially. This eliminates the need for manual intervention, thus improving the automation level of multi-UAV launch technology. Because the launch control units are pluggable, it enhances the rapid deployment capability of equipment in multi-mission scenarios.
[0041] One embodiment of this application proposes a method for controlling the launch of an anti-radiation drone, applied to an electronic device, wherein the electronic device can be a terminal or a server. This embodiment and the following embodiments will use a server as an example for illustration. The implementation details of the anti-radiation drone launch control method proposed in this embodiment are described below. The following implementation details are provided for ease of understanding and are not essential for implementing this solution.
[0042] The specific process of the anti-radiation UAV launch control method proposed in this embodiment can be described as follows: Figure 6 As shown, it includes: Step 601: With communication established between each launch transport vehicle and the ground control station, a one-click self-test command is sent from the ground control station to the launch control computer on all launch transport vehicles.
[0043] The one-click self-test command is used to instruct the drone and / or launch box to perform a self-test and report the self-test results to the ground control station.
[0044] In one possible embodiment, the self-test of the UAV includes: sequentially performing self-tests on the UAV's flight control computer, servo motor, and engine through the launch control unit, sending self-test commands to the mission payload, and determining whether the returned status parameters are within a preset threshold range to generate UAV self-test results; the launch control computer summarizes the self-test results of each UAV and reports them to the ground control station.
[0045] For example, the preset threshold range can be a manually set value or a value pre-configured by the transmission control unit. This application embodiment does not impose specific limitations on this.
[0046] For example, when entering the UAV self-test process, the launch control unit first reads the UAV's attitude, angular rate, airspeed, and altitude information, tests the flight control computer, determines whether each parameter is within a reasonable threshold range, and reports the test results to the ground control station in the form of status words. Subsequently, the launch control unit sequentially sends commands such as level flight, climb, glide, left turn, and right turn to test the servos, determining whether the servo control and feedback quantities are within a reasonable range, and reports the test results to the ground station. Next, the launch control unit sends commands such as fuel pump on / off, low horsepower, medium horsepower, and high horsepower to test the engine, checking whether the fuel pump switch status and throttle opening report meet the requirements, and sends the status information back to the ground station. Finally, the launch control unit sends payload self-test commands in the same manner to test the mission equipment, and the self-test progress is displayed in real time on the progress bar on the ground control station. For equipment with abnormal self-test results, the ground station will issue a red warning. Operators can troubleshoot the corresponding equipment based on the fault information in the warning, focusing on checking whether the connectors are loose. For faulty components that are difficult to locate, specialized testing equipment can be used for further diagnosis, or spare parts can be directly replaced. If the fault cannot be resolved on-site, the corresponding drone will be marked and will no longer participate in the subsequent launch process.
[0047] In one possible embodiment, the launch box performs a self-test, which includes: sending self-test commands sequentially to the launch box cover locking device, engine starter, clutch, and booster rocket through the launch control unit, and determining whether the feedback signals of the mechanisms are normal within a preset time to generate launch box self-test results; the launch control computer summarizes the self-test results of each launch box and reports them to the ground control station.
[0048] For example, after entering the launch box self-test process, the launch control unit sequentially sends on / off (or start / stop) self-test commands to components such as the front cover, rear cover, engine starter, and clutch, and determines whether each signal is responding correctly within a specified time. The test results are transmitted back to the ground control station in the form of status words. Subsequently, the launch control unit measures the booster rocket to determine whether its resistance is within a reasonable threshold range and reports the result back to the ground station. Finally, the launch control unit detects the launch box angle to confirm that the UAV launch angle meets the launch requirements and uploads the test result to the ground station. Similar to the UAV self-test process, if an abnormality is found in the equipment self-test, the operator can troubleshoot according to the fault prompts. If the fault cannot be resolved on-site, the corresponding launch box is marked and will not participate in the subsequent launch process.
[0049] Step 602: After the self-check process, based on task priority, the drones with normal self-check results are sorted into formations and task data is configured.
[0050] For example, after the self-test process is completed, the ground control station will form and sort all the drones on the launch transport vehicle according to the mission priority, bind the mission planning data to each drone, and finally enter the one-click launch control process.
[0051] Understandably, both the self-test and launch processes are completed automatically by the launch control computer without human intervention.
[0052] Step 603: Send a one-click launch command to all launch control computers via the ground control station.
[0053] The one-click launch command is used to instruct and control each launch box to launch drones. Drones in the same formation launch simultaneously, while drones in different formations launch sequentially at intervals.
[0054] like Figure 7 As shown, Figure 7 This is a flowchart of another anti-radiation drone launch control method.
[0055] In the first phase, pre-launch preparations and regional deployment can be carried out. For example, pre-launch preparations that can be performed in the target area may include vehicle inspections, system power-up, and communication testing; then, the launch unit moves to the designated launch site, deploys equipment, performs positioning and calibration, and puts the system into a launch-ready state.
[0056] In the second phase, both UAV self-tests and launcher self-tests can be performed. For example, in the UAV self-test process, if no abnormalities are found, the launcher self-test is performed after all UAVs have passed their self-tests. If an abnormality is detected, troubleshooting is performed on the abnormal UAV. If the fault is resolved, the launcher self-test is performed after all UAVs have passed their self-tests. If the fault remains, the UAV is marked as abnormal, and this marked UAV is considered a faulty UAV and will not participate in the subsequent launch process. Similarly, in the launcher self-test process, if no abnormalities are found, mission planning is performed after all launcher self-tests. If an abnormality is detected, troubleshooting is performed on the abnormal launcher. If the fault is resolved, mission planning is performed after all launcher self-tests. If the fault remains, the launcher is marked as abnormal, and this marked launcher is considered a faulty UAV and will not participate in the subsequent launch process.
[0057] In the third phase, mission planning and one-click launch can be performed. After all drones and launch containers undergo self-checks, the ground control station, based on the mission plan, loads mission data such as flight paths and search areas for each functioning drone. Then, after the ground control station sends a one-click launch command, all functioning launch containers can be controlled to ignite their booster rockets sequentially to launch the drones.
[0058] The steps described above are for clarity only. In implementation, they can be combined into one step, or some steps can be broken down into multiple steps, as long as they involve the same logical relationship, they are all within the scope of protection of this application. Adding insignificant modifications or introducing insignificant designs to the algorithm or process, without changing the core design of the algorithm and process, are also within the scope of protection of this application.
[0059] Another embodiment of this application proposes an anti-radiation drone launch control device. The details of this anti-radiation drone launch control device are described below. The following implementation details are provided for ease of understanding and are not essential for implementing this example. Figure 8 This is a schematic diagram of the structure of an anti-radiation UAV launch control device proposed in this embodiment, including: a transmitting unit 810 and a configuration unit 820. Wherein, The transmitting module 810 is used to send a one-click self-test command to the launch control computer on all launch vehicles through the ground control station when a communication connection is established between each launch transport vehicle and the ground control station; wherein, the one-click self-test command is used to instruct the UAV and / or launch box to perform a self-test and report the self-test results to the ground control station. Configuration unit 820 is used to sort and configure task data for drones with normal self-test results after the self-test process, based on task priority. The transmitting unit 810 is also used to send a one-click launch command to all launch control computers via the ground control station; wherein the one-click launch command is used to instruct each launch box to launch the UAV; wherein UAVs in the same formation are launched simultaneously, and UAVs in different formations are launched sequentially at intervals.
[0060] It is not difficult to see that this embodiment is a system embodiment corresponding to the above method embodiments, and this embodiment can be implemented in conjunction with the above method embodiments. The relevant technical details and technical effects mentioned in the above method embodiments are still valid in this embodiment, and will not be repeated here to reduce repetition. Accordingly, the relevant technical details mentioned in this embodiment can also be applied to the above method embodiments.
[0061] It is worth mentioning that all modules and units involved in this embodiment are logical modules. In practical applications, a logical unit can be a physical unit, a part of a physical unit, or a combination of multiple physical units. Furthermore, to highlight the innovative aspects of this application, this embodiment does not introduce units that are not closely related to solving the technical problems proposed in this application; however, this does not mean that other units do not exist in this embodiment.
[0062] Another embodiment of this application provides an electronic device, such as Figure 9 As shown, it includes a processor 91 and a memory 92. The memory 92 stores instructions that the processor 91 can execute. When the processor 91 is configured to execute the instructions, the electronic device can implement an anti-radiation UAV launch control method as described in the above method embodiment.
[0063] The memory and processor are connected via a bus, which includes any number of interconnecting buses and bridges, connecting various circuits of one or more processors and the memory. The bus can also connect various other circuits such as peripheral devices, voltage regulators, and power management circuits, which are well known in the art and will not be described further herein. The bus interface provides an interface between the bus and the transceiver. The transceiver can be a single component or multiple components, such as multiple receivers and transmitters, providing a unit for communicating with various other devices over a transmission medium. Data processed by the processor is transmitted over the wireless medium via an antenna, which further receives data and transmits it to the processor.
[0064] The processor manages the bus and general processing, and also provides various functions, including timing, peripheral interfaces, voltage regulation, power management, and other control functions. Memory is used to store data used by the processor during operation.
[0065] Another embodiment of this application proposes a computer-readable storage medium storing a computer program that, when executed by a processor, can implement an anti-radiation UAV launch control method as described in the above method embodiments.
[0066] That is, those skilled in the art will understand that all or part of the steps in the above method embodiments can be implemented by a program instructing related hardware. The program is stored in a storage medium and includes several instructions to cause a device (such as a microcontroller, chip, etc.) or processor to execute all or part of the steps of the method described in the method embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory, random access memory, magnetic disks, or optical disks.
[0067] Those skilled in the art will understand that the above embodiments are specific implementations of this application, and in practical applications, various changes can be made in form and detail without departing from the spirit and scope of this application. For those skilled in the art, several improvements and modifications can be made without departing from the principles of this application, and these improvements and modifications are also considered to be within the scope of protection of this application.
Claims
1. A launch control system for an anti-radiation unmanned aerial vehicle (UAV), characterized in that, The system adopts an Ethernet-based distributed network architecture, including: Ground control station; At least one launch transport vehicle, and each launch transport vehicle is communicatively connected to the ground control station; Each launch transport vehicle carries: A launch control computer, which is connected to a distributed network; Multiple launch boxes are used to load drones, and the launch angle of the launch boxes is adjustable; Multiple pluggable launch control units are configured in the launch control computer and correspond one-to-one with the launch box or are connected according to a preset configuration. The type and number of launch control units can be configured according to the loaded UAV. The launch control unit is used to conduct two-way data interaction with the UAV through a communication interface and to control the launch box corresponding to the launch control unit; The ground control station is used to send one-click self-test commands and one-click launch commands to all launch control computers; the one-click self-test command is used to instruct the drone and / or launch box to perform a self-test, and the one-click launch command is used to instruct the launch box to launch the drone. The launch control computer is used to control each launch control unit to perform a self-test process on the corresponding UAV and launch box in sequence after receiving a one-click self-test command. After the self-test process, it controls each launch box to launch the UAV in sequence based on the one-click launch command.
2. The system according to claim 1, characterized in that, The launch control unit establishes bidirectional communication with the UAV via an RS422 serial interface. It is used to send remote control commands, mission planning information and self-test commands to the UAV, and to receive telemetry data and status information transmitted back by the UAV.
3. The system according to claim 1, characterized in that, The system also includes a network switch; The launch and transport vehicles are interconnected via network cables and network switches, forming a distributed network architecture based on Ethernet. The launch vehicle communicates with the ground control station via fiber optic cable.
4. The system according to claim 1, characterized in that, The launch control unit integrates the ignition control circuit of the booster rocket, which uses an optical MOS relay as a switching element.
5. The system according to claim 4, characterized in that, The ignition control circuit adopts multiple safety interlock mechanisms and performs ignition operation when the conditions corresponding to the multiple safety interlock mechanisms are met. The conditions corresponding to the multiple safety interlocking mechanisms include: valid pre-launch conditions, ready pre-ignition status, and triggered ignition command.
6. A method for controlling the launch of an anti-radiation unmanned aerial vehicle (UAV), characterized in that, include: Once a communication connection is established between each launch vehicle and the ground control station, a one-click self-test command is sent from the ground control station to the launch control computer on all launch vehicles. The one-click self-test command is used to instruct the UAV and / or launch container to perform a self-test and report the self-test results back to the ground control station. After the self-inspection process, based on task priority, the drones with normal self-inspection results are sorted into groups and task data is configured. The ground control station sends a one-click launch command to all launch control computers; the one-click launch command is used to instruct each launch box to launch the UAV; UAVs in the same formation launch simultaneously, while UAVs in different formations launch sequentially at intervals.
7. The method according to claim 6, characterized in that, Perform a self-check on the drone, including: The launch control unit sequentially performs self-tests on the UAV's flight control computer, servo motor, and engine, sends self-test commands to the mission payload, and determines whether the returned status parameters are within the preset threshold range to generate UAV self-test results. The launch control computer summarizes the self-test results of each UAV and reports them back to the ground control station.
8. The method according to claim 6, characterized in that, Perform a self-test on the launcher, including: The launch control unit sequentially sends self-test commands to the launch box cover locking device, engine starter, clutch, and booster rocket, and judges whether the feedback signals of the mechanism are normal within a preset time to generate the launch box self-test result. The launch control computer summarizes the self-test results of each launch box and reports them to the ground control station.
9. An electronic device, characterized in that, include: A processor and a memory, wherein the memory stores instructions executable by the processor, and the processor is configured to, when executing the instructions, enable the electronic device to implement an anti-radiation unmanned aerial vehicle launch control method as described in any one of claims 6 to 8.
10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it can implement an anti-radiation unmanned aerial vehicle launch control method as described in any one of claims 6 to 8.