High-speed target aircraft formation launching control method and device, medium and equipment

Abstract

The invention discloses a high-speed target aircraft formation launching control method and device, a medium and equipment. The method comprises the following steps: S10, acquiring a parameter instruction; s20, the transmitting state is detected, if the transmitting state is a transmittable state, the step S40 is executed, and if the transmitting state is a non-transmittable state, the step S30 is executed; s30, carrying out special situation disposal; s40, transmitting state confirmation is carried out; s50, launching the target drone; and S60, carrying out boosting result detection. According to the invention, by detecting the transmitting state and confirming the transmitting state, the target drones can be autonomously and sequentially transmitted, the problem of inaccurate transmitting of the target drones is solved, the transmitting state can be autonomously judged, special situation handling can be timely carried out, the standby drones can be switched, and the problem of poor reliability of formation transmitting is solved. The method is an autonomous and controllable intelligent target drone launching method, manual loop control is not needed, and the problem that workers may be injured during target drone launching is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned target drone control, and in particular to a high-speed target drone formation launch control method, device, medium and equipment. Background Art

[0002] A target drone is an unmanned aerial vehicle designed and manufactured specifically for military purposes. It can pre-set flight routes and action modes. It is used to simulate enemy aircraft, missiles and other imaginary aerial targets during military exercises or weapon tests, and provides a realistic target environment for military training, weapon testing and combat effectiveness evaluation. It is a type of military drone. The formation and cluster flight of multiple target drones can achieve the construction of a multi-batch, multi-target, multi-direction and multi-situation system confrontation combat environment, and plays an important role in military fields such as battlefield assessment, military reconnaissance, decoy deception, communication relay, electronic countermeasures and target strike.

[0003] At present, when the target drone is taking off with a boost, the DC power supply is used to ignite and launch it through manual control. Specifically, the target drone and the booster are installed on the launch pad, and the launch site is manually equipped with pre-flight inspection, wire testing, booster resistance testing, booster ignition and other steps. Under the thrust of the booster, the target drone completes the takeoff and launch process.

[0004] However, in the prior art, when the target drones are launched in formation, it is required to ignite and launch multiple target drones in sequence and densely in a very short time, shorten the time interval between the target drones as much as possible, and reduce the distance difference between the multiple target drones in three-dimensional space, so as to ensure that the target drones form a formation in the air in the fastest time. Complex operating steps, short-time dense ignition and launch, special situation handling, noisy on-site noise environment, late operation, misoperation and untimely special situation handling of booster ignition by close-range manual methods, etc., will bring unstable factors to the timeliness of the target drone formation launch, resulting in poor reliability of the formation launch, and may cause the target drone to be launched on time. In addition, the prior art requires people to control in the loop, which may cause harm to the staff. Summary of the invention

[0005] The main purpose of the present invention is to provide a high-speed target drone formation launch control method and device to solve the technical problems in the prior art that the reliability of target drone formation launch is poor and may cause the target drone launch to be untimely.

[0006] To achieve the above-mentioned purpose, the present invention provides a high-speed target drone formation launch control method, which includes the following steps: S10, obtaining parameter instructions; S20, detecting the launch status, if it is a launchable state, entering step S40, if it is a non-launchable state, entering step S30; S30, handling special situations; S40, confirming the launch status; S50, launching the target drone; S60, detecting the boost result.

[0007] Optionally, the step S10 includes the following steps: S110, obtaining the target aircraft launch timing table, backup plan sequence table and launch unlocking instruction.

[0008] Optionally, the step S20 includes the following steps: S210, obtaining the current Beijing time, and comparing the current Beijing time with the launch schedule to confirm the space and timing of the target aircraft launch; S220, performing booster resistance detection, target aircraft system status and timeout status detection on the target aircraft to be launched to determine whether the target aircraft is ready for launch.

[0009] Optionally, the step S30 includes the following steps: S310, handling an emergency situation, switching to a standby machine and performing a transmission status detection.

[0010] Optionally, the step S40 includes the following steps: S410, obtaining the launch unlock instruction status of the target aircraft to be launched; S420, based on the acquired launch unlock instruction status, confirming that the target aircraft is in a launchable state.

[0011] Optionally, the step S50 includes the following steps: S510, obtaining a launch unlock instruction; S520, the intelligent launch controller takes off the target drone in sequence according to the launch timing table. Optionally, the step S60 includes the following steps: S610, obtaining the system status of the target aircraft after takeoff; S620, judging the target aircraft boost launch result based on the system status; S630, if the boost is successful, executing the next target aircraft launch process; if the boost fails, performing special situation handling.

[0012] In addition, to achieve the above-mentioned purpose, an embodiment of the present application also provides a high-speed target drone formation launch control device, which includes: a parameter instruction receiving module for obtaining parameter instructions; a launch status detection module for detecting the launch status; a special situation handling module for handling special situations; a launch confirmation module for confirming the launch status; an ignition launch module for launching the target drone; and a boost result detection module for detecting the boost result.

[0013] In addition, to achieve the above-mentioned purpose, an embodiment of the present application also provides a computer-readable storage medium, which includes instructions, which, when executed on a computer, enables the computer to execute the high-speed target drone formation launch control method described in any embodiment of the present application.

[0014] In addition, to achieve the above-mentioned purpose, an embodiment of the present application also provides a computing device, which includes: at least one microprocessor, a memory and an input and output unit; wherein the memory is used to store computer programs, the microprocessor is used to burn program firmware containing control logic, and call the computer program stored in the memory to execute the high-speed target drone formation launch control method described in any embodiment of the present application.

[0015] Compared with the prior art, the present invention has the following beneficial effects: The high-speed target drone formation launch control method provided by the embodiment of the present application can realize autonomous sequential launch of target drones by detecting the launch status and confirming the launch status, solving the problem of untimely launch of target drones, and can autonomously judge the launch status, timely handle special situations and switch to standby drones, solving the problem of poor reliability of formation launch. This method is an autonomous and controllable intelligent target drone launch method that does not require human control in the loop, solving the problem of possible harm to staff when the target drone is launched. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A flow chart of a high-speed target drone formation launch control method provided in an embodiment of the present application; Figure 2 Another flow chart of the high-speed target drone formation launch control method provided in the embodiment of the present application; Figure 3 A structural block diagram of a high-speed target drone formation launch control device provided in an embodiment of the present application; Figure 4 A schematic diagram of the structure of the medium provided in the embodiment of the present application; Figure 5 A schematic diagram of the structure of a computing device provided in an embodiment of the present application.

[0017] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0018] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application. On the contrary, these embodiments are provided to make the present disclosure more thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art.

[0019] In order to solve the above technical problems, the present application embodiment provides a high-speed target drone formation launch control method, such as Figure 1 and Figure 2 As shown, the method may include the following steps: S10, obtain parameter instructions.

[0020] In an exemplary embodiment, step S10 may specifically include the following steps: S110, obtaining the target aircraft launch timing table, backup plan sequence table and launch unlocking instruction.

[0021] Specifically, the target aircraft launch timing table, backup plan sequence table and launch unlocking command refer to the control parameters and control commands passively received by the ground operating station according to the operator's instructions.

[0022] Furthermore, the target drone launch sequence table is an important parameter table for the intelligent launch controller to sequentially launch the target drones, including the target drone number, the target drone launch time, the flight route number, the launch throttle threshold and other parameters. According to the comparison between the current Beijing time and the launch sequence table, the target drones are launched according to the target drone number and the launch time sequence in the launch sequence table and the set time sequence; at the same time, the flight route number query and launch throttle limit are performed for the target drone to be launched to determine whether the target drone is ready for launch. The backup plan sequence table is an important parameter table that requires emergency disposal when special circumstances occur: adjusting the takeoff sequence or switching to the standby aircraft for launch, including the target drone number, the takeoff time of the virtual lead aircraft, the available standby aircraft number, the flight route number, the launch throttle threshold and other parameters. The intelligent launch controller matches the standby target drone number and the flight route number according to the current target drone number, and switches to the standby target drone for launch status detection. The launch unlock command is the last soft insurance before the target drone is launched. After the target drone is ready to launch, it will automatically detect the launch unlock command uploaded by the ground operating station. When the launch unlock command is detected, the target drone is allowed to launch and take off, and the intelligent launch controller takes off the target drone according to the launch sequence. If the launch unlock command is not detected, the target drone is not allowed to launch and take off, even if the target drone meets the take-off conditions, the intelligent launch controller will not ignite the booster for launch.

[0023] The high-speed target drone formation launch control method provided by the embodiment of the present invention can realize autonomous sequential launch of target drones by detecting the launch state and confirming the launch state, thereby solving the problem of untimely launch of target drones, and can autonomously judge the launch state, timely handle special situations and switch to standby drones, thereby solving the problem of poor reliability of formation launch. The method is an autonomous and controllable intelligent target drone launch method that does not require human control in the loop, thereby solving the problem of possible harm to staff when the target drone is launched.

[0024] S20, detect the transmission state, if it is a transmission state, go to step S40, if it is a non-transmission state, go to step S30.

[0025] In an exemplary embodiment, step S20 may specifically include the following steps: S210, obtaining the current Beijing time, and comparing the current Beijing time with the launch schedule to confirm the space and timing of the target aircraft launch; S220, performing a booster resistance test, a target drone system status and a timeout status test on the target drone to be launched, and determining whether the target drone is ready for launch.

[0026] Among them, in step S220, the target machine launch timing detection can also be performed to determine whether the target machine is in the launch state.

[0027] Specifically, the target drone system status detection is to detect the target drone's onboard avionics system, power system, actuators, etc., such as whether the target drone's navigation system status is normal, whether the onboard power supply voltage is normal, whether the engine is on, whether the engine throttle has reached the launch threshold, whether the steering gear and control surfaces are actuated normally, etc.; the target drone launch timing detection is to compare the current Beijing time with the target drone launch timing table to determine whether the target drone has reached the take-off time, and output whether the target drone is in a launchable state; the booster resistance detection is to detect the booster resistance of the current target drone, The intelligent launch controller can control the ignition of the booster only when the resistance value of the ignition cartridge is within the specified range. If the resistance value of the ignition cartridge exceeds or is lower than the specified range, the booster cannot be ignited normally, resulting in the failure of the target aircraft to take off. The launch timeout detection is based on the launch schedule, and a timeout detection is performed on the delayed launch target aircraft. If the launch delay time exceeds the normal flight time of the target aircraft, the current target aircraft launch status will be set to non-launchable. Conversely, if the launch delay time does not exceed the normal flight time of the target aircraft, the current target aircraft launch status will be set to launchable.

[0028] S30, handle special situations.

[0029] In an exemplary embodiment, step S30 may specifically include the following steps: S310, handle the special situation, switch to the standby machine and perform the launch status detection.

[0030] Specifically, special situation handling is divided into special situation handling before takeoff and special situation handling after takeoff. Special situation handling before takeoff means that the target aircraft is in a non-launchable state during the launch status detection. First, the launch mark of the target aircraft will be cancelled, and then the launch status of the backup target aircraft will be detected according to the backup plan sequence table process, and the standby aircraft launch process will be executed; special situation handling after takeoff means that the target aircraft system status fails after the boost launch, such as engine shutdown, abnormal boost attitude, abnormal boost speed, abnormal boost altitude, and boost execution structure jamming, which will cause the target aircraft to be unable to complete the mission. First, the target aircraft will be subjected to emergency handling of parachute opening, and then the launch status of the backup target aircraft will be detected according to the backup plan sequence table process, and the standby aircraft launch process will be executed.

[0031] S40, confirm the transmission status.

[0032] Specifically, this step is the last soft insurance before the target drone is launched. After the target drone is ready to launch, it will automatically detect the launch unlock command uploaded by the ground operating station. When the launch unlock command is detected, the target drone is allowed to launch and take off, and the intelligent launch controller takes off the target drone according to the launch sequence. If the launch unlock command is not detected, the target drone is not allowed to launch and take off, even if the target drone meets the take-off conditions, the intelligent launch controller will not ignite the booster for launch.

[0033] In an exemplary embodiment, step S40 may specifically include the following steps: S410, obtaining the launch unlocking instruction status of the current target drone to be launched; S420, based on the acquired launch unlock instruction status, confirm that the target drone is in a launchable state.

[0034] S50, launching the target drone.

[0035] Specifically, this step is a key step in promoting the launch of the target drone. When the target drone is in a launchable state and the ground operation station unlocks the launch of the target drone, the intelligent launch controller connects the solid-state battery and the booster ignition box according to the preset program logic, and the current stimulates the booster ignition box to ignite the charge, thereby converting chemical energy into kinetic energy to promote the launch of the target drone.

[0036] In an exemplary embodiment, step S50 may specifically include the following steps: S510, obtaining a transmission unlock instruction; S520, the intelligent launch controller takes off the target drone according to the launch sequence table.

[0037] S60, performing boost result detection.

[0038] Specifically, this step is to establish a MESH network through data link to obtain the target aircraft's launch and takeoff status in real time, such as flight attitude angle, flight speed, climb rate, flight altitude, engine status, actuator status, etc., to determine whether the target aircraft's boost launch is successful. If the target aircraft's boost launch is successful, the intelligent launch controller executes the next target aircraft launch process; if the target aircraft's boost launch fails, the intelligent launch controller executes the special situation handling process. When the pitch angle of the target aircraft exceeds the range of -10° to 50°, or the roll angle exceeds the range of -70° to 70° after the boost, the target aircraft's boost launch is determined to have failed; when the flight speed is continuously lower than 90m / s and the climb rate is continuously lower than 5m / s within 20 seconds of the target aircraft's boost takeoff, the target aircraft's boost launch is determined to have failed; when the flight altitude is continuously lower than the ground altitude before takeoff within 20 seconds of the target aircraft's boost takeoff, the target aircraft's boost launch is determined to have failed; when the target aircraft's engine stops after the boost and the engine speed is 0r / min, the target aircraft's boost launch is determined to have failed; when the servo and other actuators do not continuously send back angle values ​​within 20 seconds of the target aircraft's boost takeoff, the target aircraft's boost launch is determined to have failed.

[0039] Among them, the ‌Mesh network‌ is a new type of wireless network architecture, the core idea of ​​which is to allow each node in the network to send and receive signals, thereby solving the problems of low scalability and poor robustness of traditional wireless networks. The Mesh network is also called a "multi-hop network", in which any wireless device node can act as an access point (AP) and a router at the same time, and each node in the network can communicate directly with one or more peer nodes.

[0040] In an exemplary embodiment, step S60 may specifically include the following steps: S610, obtaining the system status of the target drone after taking off; S620, judging the boost launch result of the target drone based on the system status; S630: If the boost is successful, the next target drone launch process will be executed; if the boost fails, special situation handling will be carried out.

[0041] Specifically, the special situation handling is that when the target aircraft is not in the launch state or the boost takeoff fails, the corresponding standby aircraft launch process is executed according to the preset process in the backup plan sequence table to ensure the success rate of the formation launch. The specific processing process has been explained in step S30 and will not be repeated here.

[0042] Based on the above embodiments, Figure 3 Another embodiment of the present application further provides a high-speed target drone formation launch control device, and the high-speed target drone formation launch control device 300 may include the following modules: A parameter instruction receiving module 310 is used to obtain parameter instructions; A transmitting state detection module 320, used to detect the transmitting state; The special situation handling module 330 is used to handle special situations; The transmission confirmation module 340 is used to confirm the transmission status; An ignition launch module 350 is used to launch the target drone; The boosting result detection module 360 ​​is used to perform boosting result detection.

[0043] Based on the above embodiments, the present application also provides a computer-readable storage medium, referring to Figure 4 , the computer readable storage medium shown is a CD 50, on which a computer program (i.e., a program product) is stored. When the computer program is executed by the processor, each step recorded in the above method implementation will be implemented, for example, S10, obtaining parameter instructions; S20, detecting the launch state, if it is a launchable state, entering step S40, if it is a non-launchable state, entering step S30; S30, handling special situations; S40, confirming the launch state; S50, launching the target drone; S60, detecting the boost result. The specific implementation of each step will not be repeated here.

[0044] It should be noted that examples of the computer-readable storage medium may also include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other optical or magnetic storage media, which are not listed here one by one.

[0045] In addition, based on the above embodiments, the present application also provides a computing device, Figure 5 A block diagram of an exemplary computing device 60 suitable for implementing embodiments of the present application is shown. The computing device 60 may be a computer system or a server. Figure 5 The computing device 60 shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0046] like Figure 5 As shown, the components of the computing device 60 may include, but are not limited to: one or more microprocessors or processing units 601 , a system memory 602 , and a bus 603 connecting various system components (including the system memory 602 and the processing unit 601 ).

[0047] The computing device 60 typically includes a variety of computer system readable media. These media can be any available media that can be accessed by the computing device 60, including volatile and non-volatile media, removable and non-removable media.

[0048] The system memory 602 may include computer system readable media in the form of volatile memory, such as random access memory (RAM) 6021 and / or cache memory 6022. The computing device 60 may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, the ROM 6023 may be used to read and write non-removable, non-volatile magnetic media ( Figure 5 is not shown in the Figure 5 As shown in the figure, a disk drive for reading and writing a removable non-volatile disk (such as a "floppy disk") and an optical disk drive for reading and writing a removable non-volatile optical disk (such as a CD-ROM, DVD-ROM or other optical media) can be provided. In these cases, each drive can be connected to a bus 603 connecting different system components through one or more data medium interfaces. The system memory 602 may include at least one program product, which has a set (such as at least one) of program modules, which are configured to perform the functions of each embodiment of the present application.

[0049] A program / utility 6025 having a set (at least one) of program modules 6024 may be stored, for example, in system memory 602, and such program modules 6024 include, but are not limited to, an operating system, one or more application programs, other program modules, and program data, each of which or some combination may include an implementation of a network environment. Program modules 6024 generally perform the functions and / or methods of the embodiments described herein.

[0050] The computing device 60 may also communicate with one or more external devices 604 (e.g., a keyboard, a pointing device, a display, etc.). Such communication may be performed via an input / output (I / O) interface 605. In addition, the computing device 60 may also communicate with one or more networks (e.g., a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) via a network adapter 606. Figure 5 As shown, the network adapter 606 communicates with other modules (such as the processing unit 601, etc.) of the computing device 60 via the bus 603 that connects the different system components. Figure 5 Not shown, other hardware and / or software modules may be used in conjunction with computing device 60 .

[0051] The processing unit 601 executes various functional applications and data processing by running the program stored in the system memory 602, for example, S10, obtains parameter instructions; S20, detects the launch state, if it is a launchable state, enters step S40, if it is a non-launchable state, enters step S30; S30, performs special situation handling; S40, confirms the launch state; S50, launches the target drone; S60, performs boost result detection. The specific implementation of each step is not repeated here. It should be noted that although several units / modules or sub-units / sub-modules of the high-speed target drone formation launch control device are mentioned in the above detailed description, this division is only exemplary and not mandatory. In fact, according to the embodiment of the present application, the features and functions of two or more units / modules described above can be concretized in one unit / module. Conversely, the features and functions of one unit / module described above can be further divided into multiple units / modules to be concretized.

[0052] In the description of the present application, it should be noted that the terms "first", "second" and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0053] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0054] In the several embodiments provided in the present application, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some communication interfaces, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.

[0055] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0056] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0057] If the function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a non-volatile computer-readable storage medium that is executable by a processor. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc. Various media that can store program codes.

[0058] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present application, which are used to illustrate the technical solutions of the present application, rather than to limit them. The protection scope of the present application is not limited thereto. Although the present application is described in detail with reference to the above-described embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-described embodiments within the technical scope disclosed in the present application, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

[0059] In addition, although the operations of the method of the present application are described in a specific order in the drawings, this does not require or imply that the operations must be performed in this specific order, or that all the operations shown must be performed to achieve the desired results. Additionally or alternatively, some steps may be omitted, multiple steps may be combined into one step, and / or one step may be decomposed into multiple steps.

Claims

1. A high-speed target drone formation launch control method, characterized in that: The high-speed target drone formation launch control method comprises the following steps: S10, obtaining parameter instructions; S20, detect the transmitting state, if it is in the transmitting state, go to step S40, if it is in the non-transmitting state, go to step S30; S30, handle special situations; S40, confirming the transmission status; S50, launching the target drone; S60, performing boost result detection.

2. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S10 comprises the following steps: S110, obtaining the target aircraft launch timing table, backup plan sequence table and launch unlocking instruction.

3. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S20 comprises the following steps: S210, obtaining the current Beijing time, and comparing the current Beijing time with the launch schedule to confirm the space and timing of the target aircraft launch; S220, performing a booster resistance test, a target drone system status and a timeout status test on the target drone to be launched, and determining whether the target drone is ready for launch.

4. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S30 comprises the following steps: S310, handle the special situation, switch to the standby machine and perform the launch status detection.

5. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S40 comprises the following steps: S410, obtaining the launch unlocking instruction status of the current target drone to be launched; S420, based on the acquired launch unlock instruction status, confirm that the target drone is in a launchable state.

6. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S50 comprises the following steps: S510, obtaining a transmission unlock instruction; S520, the intelligent launch controller takes off the target drone according to the launch sequence table.

7. The high-speed target drone formation launch control method according to claim 1, characterized in that: The step S60 comprises the following steps: S610, obtaining the system status of the target drone after taking off; S620, judging the boost launch result of the target drone based on the system status; S630: If the boost is successful, the next target drone launch process will be executed; if the boost fails, special situation handling will be carried out.

8. A high-speed target drone formation launch control device, characterized in that: include: A parameter instruction receiving module is used to obtain parameter instructions; A transmitting state detection module, used for detecting the transmitting state; Special situation handling module, used for handling special situations; A launch confirmation module, used to confirm the launch status; Ignition launch module, used for launching the target drone; The boosting result detection module is used to perform boosting result detection.

9. A computer-readable storage medium, characterized in that: It includes instructions, which, when running on a computer, enable the computer to execute the high-speed target drone formation launch control method described in any one of claims 1-7.

10. A computing device, characterized in that The computing device comprises: at least one microprocessor, memory and input-output unit; Wherein, the memory is used to store computer programs, the microprocessor is used to burn program firmware containing control logic, and the computer program stored in the memory is called to execute the high-speed target drone formation launch control method described in any one of claims 1-7.

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