Processing system for realizing missile parameter binding switching based on launching control equipment

Abstract

The invention discloses a processing system for realizing missile parameter binding switching based on launch control equipment, the processing system runs on the missile launch control equipment, and the processing system comprises a launch control module and a launch control execution module; the launch control module is used for performing data interaction with the command control system, receiving the first binding parameter, generating a second binding parameter, executing missile parameter adjustment timing, and updating the first binding parameter into a historical first binding parameter; and the launch control execution module obtains the second binding parameter from the launch control module, performs data interaction with a control device on a launch missile of the missile, executes parameter binding consistency judgment, returns a parameter binding consistency judgment result, and stores the second binding parameter as a historical second binding parameter. According to the technical scheme, safety control can be ensured when the missile launch control equipment has the problem that the bounded parameters of the missile launch control equipment are inconsistent with the execution parameters of the missile launch control equipment, that is, the launch control equipment does not execute a launch program when an exception occurs, so that the missile is in a safe state.

Description

Technical Field

[0001] The invention relates to the field of launch control of a ground-to-air missile weapon system, and in particular to a processing system for realizing missile parameter binding switching based on a launch control device. Background Art

[0002] The use of new bus and communication technologies in the surface-to-air missile weapon system can meet the needs of large data volumes and high-speed transmission. However, in the process of using Ethernet data transmission, occasional network packet loss often occurs, and some important status and data messages will be missed. Especially when wireless communication data is transmitted, in order to ensure the minimum exposure time, the communication system sends electromagnetic signals irregularly with the minimum available signal power. The communication between the launch control module and the launch control execution module uses non-periodic real-time trigger messages, such as sending three consecutive beats at an interval of 10ms and then stopping. However, if occasional messages are lost during the transmission process, and the lost message content is important status information, causing the launch control device to upload the parameters of the missile control device to be abnormal, it may cause serious consequences.

[0003] In order to ensure the correctness of the transmission of important control information and status information between the transmission control module and the transmission control execution module, and to avoid the consequences of inevitable occasional network packet loss during data transmission, it is necessary to adopt a feedback retransmission mechanism to protect such messages during design.

[0004] At the same time, when the weapon system is in combat, the launch waiting time from when the missile is powered on and ready to when the missile can execute the irreversible launch procedure is relatively long. Parameters such as the operating frequency of the launch control device bound to the on-board control device may change with the parameter calculation of the upper-level system. Therefore, a technical solution is also needed to assist the launch control device in performing data comparison on the correctness of the missile parameter binding during the change of the missile binding parameters to protect the missile from being launched by mistake. Summary of the invention

[0005] To achieve the above-mentioned purpose, the present application provides a processing system for realizing missile parameter binding switching based on a launch control device, the processing system runs on the missile launch control device, and includes a launch control module and a launch control execution module;

[0006] Among them, the launch control module is used to interact with the command and control system data, receive the first binding parameter, generate the second binding parameter, execute the missile parameter adjustment timing, and update the first binding parameter to the historical first binding parameter; before generating the second binding parameter, the launch control module compares the first binding parameter with the historical first binding parameter, and generates the second binding parameter if the first binding parameter changes compared with the historical first binding parameter; if the second binding parameter is generated, execute the missile parameter adjustment timing according to the binding parameter adjustment flag; execute the missile parameter adjustment timing indicator, judge the status information after waiting for a specified time, and generate a sending decision according to the status information; the sending decision includes: updating the status information content, sending the second binding parameter to the launch control execution module; the status information content includes: missile binding parameter adjustment, missile binding parameter adjustment end.

[0007] The launch control execution module obtains the second binding parameter from the launch control module, performs data interaction with the control device on the missile, performs parameter binding consistency judgment, returns the parameter binding consistency judgment result, and stores the second binding parameter as the historical second binding parameter; wherein the parameter binding consistency judgment result includes: missile parameter binding status;

[0008] The second binding parameters include the missile's ready state, a binding parameter adjustment flag, and the missile parameter binding state returned by the launch control execution module.

[0009] The processing system also includes a launch control power supply for providing direct current to the launch control execution module and the missile. The launch control module is installed in the command and control vehicle, and the launch control power supply module and the launch control execution module are installed in the missile launch vehicle.

[0010] Generating the second binding parameter includes: setting the missile's ready state to invalid, setting the missile parameter binding state to unbound, and setting the binding parameter adjustment flag to valid.

[0011] The judgment status information includes: if the missile parameter binding status is binding, the on-board control equipment working status is working well, the binding parameter adjustment flag is set to invalid, and the update status information content is that the missile binding parameter adjustment is completed.

[0012] If the launch control module captures that the parameter binding status in the binding result is abnormal or the working status of the onboard control device is abnormal, the status information content is updated to indicate that the missile binding parameter adjustment is completed and the binding parameter adjustment flag is invalid, and a missile release command is sent to the launch control execution module to stop executing the missile parameter adjustment timing.

[0013] The execution parameter binding consistency judgment of the transmission control execution module includes:

[0014] Determine whether the second binding parameter has changed compared with the historical second binding parameter. If so, set the missile parameter binding state to unbound. Otherwise, set the missile parameter binding state to bound. Generate a parameter binding consistency judgment result according to the missile parameter binding state.

[0015] After the launch control execution module performs parameter binding consistency judgment, if the missile parameter binding status is not bound, the launch control execution module locks the second binding parameter, binds the second binding parameter to the missile's onboard control device, and obtains the binding result returned by the onboard control device.

[0016] Furthermore, after the spring-loaded control device obtains the second binding parameter, it completes the parameter binding and returns the binding result to the transmission control execution module.

[0017] According to the present invention, safety control can be ensured when the launch control execution module does not receive the missile binding parameters sent by the launch control module, or when the launch control execution module binds the parameters to the on-board control device inconsistent with the execution parameters of the on-board control device, that is, the launch control device does not execute the launch program, automatically cuts off the ground power supply of the missile, and puts the missile into a safe state. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the structure of a processing system provided according to an embodiment of the present invention;

[0019] Figure 2 is a control flow chart of a processing system provided according to an embodiment of the present invention;

[0020] Figure 3 It is a structural diagram of the missile binding parameter message format provided according to an embodiment of the present invention. DETAILED DESCRIPTION

[0021] The processing system provided by the present invention realizes missile parameter binding switching based on a launch control device. The launch control device receives the missile binding parameters sent by the upper system (such as the command and control system), judges the change of the missile binding parameters in the system, protects the missile's ready state, and prohibits the execution of the launch control program before it is determined that the on-board control device completes the parameter binding. On the other hand, the missile parameters are bound to the on-board control device, and the execution parameters returned by the on-board control device are compared and confirmed. The processing system provided by the present invention can protect the function of the launch control system to bind parameters to the missile, thereby preventing the missile from being launched by mistake.

[0022] The specific implementation of the present invention is described in detail below with reference to the accompanying drawings.

[0023] The present invention provides a processing system for realizing missile parameter binding switching based on a launch control device, the processing system runs on the missile launch control device, and includes a P100 launch control module and a P110 launch control execution module;

[0024] The P100 launch control module is installed in the command and control vehicle and consists of a launch control computer, launch control software, etc. The launch control module provides a data interface to the command and control system and a data communication interface to the missile launch vehicle. It is the center of missile launch vehicle control and missile launch control. It can determine the status of the missile launch vehicle and the missile and decide whether the missile can be launched.

[0025] In actual applications, after the missile is ready, the launch control module interacts with the command and control system data and receives the binding parameters (i.e., the first binding parameters) from the command and control system. After that, it determines whether the missile binding parameters in the first binding parameters have changed, and performs the missile binding parameter change control logic based on the change. The second binding parameters are generated based on the changed missile binding parameters, the missile parameter adjustment timing is executed, and the first binding parameters are updated to the historical first binding parameters.

[0026] At this time, the missile binding parameter change control logic can protect the missile's ready state to prevent the missile from being accidentally launched due to the missile's failure to complete parameter binding;

[0027] The second binding parameters are important contents of the missile binding parameter message and parameter binding status message transmitted between the launch control module and the launch control execution module, including the missile's ready state, binding parameter adjustment flag and missile parameter binding state. When generating the second binding parameters, the launch control module compares the first binding parameters with the historical first binding parameters. If the first binding parameters change compared with the historical first binding parameters, the missile's ready state is set to invalid, the missile parameter binding state is set to unbound, and the binding parameter adjustment flag is set to valid. When the missile's binding parameter adjustment flag is valid, if the missile binding parameter change is received again from the upper-level system, the launch control module immediately sends the latest missile binding parameters to the launch control execution module and restarts the missile parameter adjustment timing;

[0028] Among them, executing the missile parameter adjustment timing means waiting for a specified time to judge the status information and generating a sending decision based on the status information; the sending decision includes updating the status information content and sending the second binding parameter to the launch control execution module; specifically, the status information content includes: missile binding parameter adjustment, missile binding parameter adjustment end.

[0029] The specified duration includes the first specified duration and the second specified duration:

[0030] 1) After the missile parameter adjustment timing of the launch control module reaches the first specified time (e.g., 0.5s), the status information content is updated;

[0031] 2) After the missile parameter adjustment timing of the launch control module reaches the second specified time length (for example, 1.5s), a launch decision is generated.

[0032] When judging the status information: if the missile parameter binding state is binding, and the onboard control device working state is working well, the binding parameter adjustment flag is set to invalid, the status information content is updated to the missile binding parameter adjustment is completed, and the second binding parameter is generated and sent to the launch control execution module;

[0033] When generating a sending decision, if there is any abnormality in the missile parameter binding status or the working status of the onboard control equipment, the launch control module will set the "binding parameter adjustment flag" to invalid, stop the adjustment timing, and report the missile preparation abnormality to the upper-level system, and send a missile release command to the launch control execution module. The launch control execution module stops the missile ground power supply, and the missile parameter adjustment is completed.

[0034] During the control process of the processing system, the launch control module generates a second binding parameter according to the first binding parameter and the parameter binding consistency judgment result received last time and provided by the launch control execution module, and executes the missile parameter adjustment timing according to the binding parameter adjustment flag;

[0035] When the transmission control module sends a message to the transmission control execution module, it uses a non-periodic real-time trigger message that is triggered only when an event changes, for example, it stops sending after sending three times continuously at an interval of 10ms. Through the non-periodic real-time trigger message, information transmission between the modules of the transmission control device is realized. In the present invention, the communication message format structure diagram is as follows Figure 3 As shown, the main content of the message is shown in Table 1 and Table 2.

[0036] Table 1

[0037]

[0038]

[0039] Table 2

[0040]

[0041] After receiving the instruction sent by the launch control module, the P110 launch control execution module converts the instruction, outputs the signal required by the missile, and executes the missile power connection and launch control. Specifically, the launch control execution module obtains the second binding parameter from the launch control module, exchanges data with the control device on the missile, performs parameter binding consistency judgment, and returns the parameter binding consistency judgment result; at this time, the second binding parameter is stored as the historical second binding parameter; the parameter binding consistency judgment result includes: missile parameter binding status;

[0042] The execution parameter binding consistency judgment of the transmission control execution module includes:

[0043] Determine whether the second binding parameter has changed compared with the historical second binding parameter. If so, set the missile parameter binding state to unbound. Otherwise, set the missile parameter binding state to bound, and generate a parameter binding consistency judgment result according to this state; send the parameter binding consistency judgment result to the launch control module;

[0044] If the missile parameter binding status is not bound, the launch control execution module locks the second binding parameter, binds the second binding parameter to the onboard control device of the P120 missile, and obtains the binding result returned by the onboard control device. During the interaction process, the launch control execution module locks the changed missile binding parameters, binds the locked missile parameters to the onboard control device in real time, and after the onboard control device completes the parameter binding, it returns the execution value to the launch control execution module, which performs parameter binding comparison and confirmation, generates the missile parameter binding status, and returns it to the launch control execution module.

[0045] If the launch control module captures that the parameter binding status in the binding result is abnormal or the working status of the onboard control device is abnormal, the status information is updated to indicate that the missile binding parameter adjustment is completed and the binding parameter adjustment flag is invalid, and a missile release command is sent to the launch control execution module, and the missile parameter adjustment timing is stopped at the same time.

[0046] After the launch control execution module obtains the command to release the missile, it stops the ground power supply to the missile, and stops executing after the missile parameter adjustment is completed.

[0047] In addition, the processing system also includes a launch control power module, which is installed in the missile launch vehicle with the launch control execution module to provide DC current to the launch control execution module and the missile.

[0048] The present invention performs multiple rounds of consistency confirmation on the transmission of important control information and state information between the launch control module, the launch control execution module and the missile equipment, identifies and discovers the inevitable network packet loss phenomenon in the data transmission process, and avoids the possible consequences of this phenomenon. Through the processing system, a feedback retransmission mechanism is adopted for such messages, thereby realizing the protection of the missile state consistency. On the other hand, the processing system also judges the changes and abnormalities of the states of various devices during the launch waiting process from the missile being powered on and ready to the missile being able to execute the launch irreversible program, so as to ensure that the missile is not launched by mistake.

[0049] The above disclosures are only several specific embodiments of the present invention; however, the present invention is not limited thereto, and any changes that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. A processing system for realizing missile parameter binding switching based on a launch control device, characterized in that: The processing system runs on a missile launch control device and includes a launch control module and a launch control execution module; Wherein, the launch control module is used to interact with the command and control system data, receive the first binding parameter, generate the second binding parameter, execute the missile parameter adjustment timing, and update the first binding parameter to the historical first binding parameter; wherein, before generating the second binding parameter, the launch control module compares the first binding parameter with the historical first binding parameter, and generates the second binding parameter if the first binding parameter changes compared with the historical first binding parameter; if the second binding parameter is generated, execute the missile parameter adjustment timing according to the binding parameter adjustment flag; the execution of the missile parameter adjustment timing refers to judging the status information after waiting for a specified time, and generating a sending decision according to the status information; the sending decision includes: updating the status information content, sending the second binding parameter to the launch control execution module; the status information content includes: missile binding parameter adjustment, missile binding parameter adjustment end. The launch control execution module obtains the second binding parameter from the launch control module, performs data interaction with the control device on the missile, performs parameter binding consistency judgment, returns the parameter binding consistency judgment result, and stores the second binding parameter as a historical second binding parameter; wherein the parameter binding consistency judgment result includes: missile parameter binding status; The second binding parameters include the missile's ready state, a binding parameter adjustment flag, and the missile parameter binding state returned by the launch control execution module.

2. The processing system according to claim 1, characterized in that The processing system also includes a launch control power supply for providing direct current to the launch control execution module and the missile.

3. The processing system according to claim 1, characterized in that The generating of the second binding parameter includes: setting the missile ready state to be invalid, setting the missile parameter binding state to be unbound, and setting the binding parameter adjustment flag to be valid.

4. The processing system according to claim 1, characterized in that The judgment status information includes: if the missile parameter binding state is binding, the on-board control device working state is working well, the binding parameter adjustment flag is set to invalid, and the update status information content is missile binding parameter adjustment completed.

5. The processing system according to claim 1, characterized in that If the launch control module captures that the parameter binding status in the binding result is abnormal or the working status of the onboard control device is abnormal, the status information content is updated to indicate that the missile binding parameter adjustment is completed and the binding parameter adjustment flag is invalid, and a missile release command is sent to the launch control execution module to stop executing the missile parameter adjustment timing.

6. The processing system according to claim 1, characterized in that The execution control execution module performs parameter binding consistency judgment including: Determine whether the second binding parameter has changed compared with the historical second binding parameter. If so, set the missile parameter binding state to unbound; otherwise, set the missile parameter binding state to bound. Generate a parameter binding consistency judgment result according to the missile parameter binding state.

7. The processing system according to claim 6, characterized in that After the launch control execution module performs parameter binding consistency judgment, if the missile parameter binding status is not bound, the launch control execution module locks the second binding parameter, binds the second binding parameter to the missile's onboard control device, and obtains the binding result returned by the onboard control device.

8. The processing system according to claim 7, characterized in that After the on-board control device obtains the second binding parameter, it completes the parameter binding and returns the binding result to the transmission control execution module.

9. The processing system according to claim 2, characterized in that The launch and control module is installed in the command and control vehicle, and the launch and control power supply module and the launch and control execution module are installed in the missile launch vehicle.

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