A processing system for missile parameter binding and switching based on launch control equipment

Abstract

The present invention discloses a processing system for implementing 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. The launch control module is used to interact with the command and control system data, receive a first binding parameter, generate a second binding parameter, execute missile parameter adjustment timing, and update the first binding parameter to a historical first binding parameter. The launch control execution module obtains the second binding parameter from the launch control module, interacts with the missile's onboard control device, performs parameter binding consistency judgment, returns the parameter binding consistency judgment result, and stores the second binding parameter as a historical second binding parameter. According to the above technical solution, safety control can be ensured when a problem occurs on the missile launch control device where the onboard control device binding parameters are inconsistent with the onboard control device execution parameters. That is, when an abnormality occurs, the launch control device does not execute the launch program, causing the missile to enter a safe state.

Description

Technical Field

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

[0002] Surface-to-air missile weapon systems utilize new bus and communication technologies to meet the demands of large data volumes and high-speed transmission. However, during Ethernet data transmission, occasional packet loss often occurs, resulting in the omission of important status and data messages. Especially during wireless data transmission, to minimize exposure time, the communication system transmits electromagnetic signals erratically at the minimum available signal power. Communication between the launch control module and the launch control execution module utilizes non-periodic, real-time trigger messages, for example, sending three consecutive messages at 10ms intervals followed by a pause. However, if occasional message loss during transmission contains important status information, this can cause parameter binding errors in the launch control equipment uploading to the missile control equipment, potentially resulting in serious consequences.

[0003] In order to ensure the correct transmission of important control information and status information between the transmission and control module and the transmission and 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 program is relatively long. The parameters such as the operating frequency of the launch control equipment bound to the on-board control equipment may change with the parameter calculation of the upper-level system. Therefore, a technical solution is also needed to assist the launch control equipment 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 implementing 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, wait for a specified time and then judge the status information, and generate a sending decision according to the status information; the sending decision includes: updating the status information content and sending the second binding parameter to the launch control execution module; the status information content includes: missile binding parameter adjustment and missile binding parameter adjustment end.

[0007] The launch control execution module obtains the second binding parameter from the launch control module, exchanges data with the control device on the missile launcher, 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;

[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 DC 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 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 bound and the on-board control device 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 on-board 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 to stop executing the missile parameter adjustment timing.

[0013] The execution parameter binding consistency judgment of the dispatch 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 based on 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 parameters bound by the launch control execution module to the on-board control device are 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 This is a structural diagram of the missile binding parameter message format provided according to an embodiment of the present invention. DETAILED DESCRIPTION

[0021] The present invention provides a processing system for implementing missile parameter binding switching based on a launch control device. The launch control device receives missile binding parameters sent by an upper-level system (such as a command and control system), judges changes in the missile binding parameters in the system, protects the missile's readiness state, and prohibits the execution of a launch control program before confirming that the on-board control device has completed 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 proposed 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 and software. It 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, capable of determining the status of the missile launch vehicle and missiles, and deciding whether a missile can be launched.

[0025] In actual application, 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. Based on the change, the missile binding parameter change control logic is performed, and 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 launched accidentally due to the missile not completing parameter binding;

[0027] The second binding parameters are important content in 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 to 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. If the missile's binding parameter adjustment flag is valid and a 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 timer.

[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 and 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 timer of the launch control module reaches a 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 (e.g., 1.5s), a launch decision is generated.

[0032] When judging the status information: if the missile parameter binding status is binding completed and the missile control device working status is working well, the binding parameter adjustment flag is set to invalid, the status information content is updated to missile binding parameter adjustment 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 on-board 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 will stop the missile ground power supply, and the missile parameter adjustment will be completed.

[0034] During the control process of the processing system, the launch control module generates a second binding parameter based on 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 consecutive beats 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 The 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 instructions from the launch control module, the P110 launch control execution module converts the instructions, outputs the signals required by the missile, and executes the missile power connection and launch control. Specifically, the launch control execution module obtains the second binding parameters from the launch control module, exchanges data with the missile's onboard control device, performs parameter binding consistency judgment, and returns the parameter binding consistency judgment result; at this time, the second binding parameters are stored as historical second binding parameters; the parameter binding consistency judgment result includes: missile parameter binding status;

[0042] The execution parameter binding consistency judgment of the dispatch 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 based on this state; send the parameter binding consistency judgment result to the launch control module;

[0044] If the missile parameter binding status is unbound, the launch control execution module locks the second binding parameters, binds them to the P120 missile's onboard control device, and obtains the binding result returned by the onboard control device. During the interactive process, the launch control execution module locks the changed missile binding parameters and binds them to the onboard control device in real time. After the onboard control device completes the parameter binding, it transmits the execution value back to the launch control execution module. The launch control execution module then compares and confirms the parameter binding, 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 on-board 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 missile release command, it stops the missile ground power supply, and the missile parameter adjustment is completed and execution stops.

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

[0048] The present invention performs multiple rounds of consistency verification on the transmission of important control and status information between the launch control module, the launch control execution module, and the missile equipment. This identifies and detects the inevitable network packet loss during data transmission and mitigates the potential consequences of this phenomenon. Through the processing system, a feedback and retransmission mechanism is implemented for such messages, thereby protecting the missile's state consistency. Furthermore, the processing system also determines changes and anomalies in the status of various devices during the missile's power-on readiness phase until the missile is ready to execute the irreversible launch sequence, ensuring that the missile is not accidentally launched.

[0049] The above disclosures are only a few specific embodiments of the present invention. However, the present invention is not limited thereto. Any changes that can be conceived by those skilled in the art should fall within the scope of protection 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; 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; the execution of the missile parameter adjustment timing refers to waiting for a specified time period and then judging the status information, and generating a sending decision according to the status information; the sending decision includes: updating the status information content and sending the second binding parameter to the launch control execution module; the status information content includes: missile binding parameter adjustment and missile binding parameter adjustment completion; The launch control execution module obtains the second binding parameter from the launch control module, exchanges data with the missile's onboard control device, performs parameter binding consistency judgment, returns a 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, wherein: 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, wherein: The generating of the second binding parameter includes: setting the missile ready state to invalid, setting the missile parameter binding state to unbound, and setting the binding parameter adjustment flag to valid.

4. The processing system according to claim 1, wherein: The judgment status information includes: if the missile parameter binding state is binding, the missile 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, wherein: If the launch control module captures that the parameter binding status in the binding result is abnormal or the working status of the on-board 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 to stop executing the missile parameter adjustment timing.

6. The processing system according to claim 1, wherein: The execution parameter binding consistency judgment of the issuance control execution module includes: 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 based on 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 acquiring the second binding parameter, the on-board control device completes the parameter binding and returns the binding result to the transmission control execution module.

9. The processing system according to claim 2, wherein: 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.

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