Catapulting stroke monitoring system for catapulting mechanism in missile launching stage

Abstract

The invention provides an ejection stroke monitoring system for an ejection mechanism in a missile launching stage, and the system comprises an ejection stroke monitoring module which is composed of a sensor disposed on the ejection mechanism of a missile launching device, and carries out the real-time ejection collection of stroke data; the data storage module is used for receiving, storing and exporting data of the ejection stroke monitoring module; and the ground visualization platform is used for downloading the data from the data storage module and importing the data into the ground visualization platform for data collection and display. According to the invention, the system suitable for monitoring the ejection stroke of the ejection mechanism of the missile launching device is established to collect, process and display the ejection stroke of the ejection mechanism in the ejection stage, so that technicians are assisted in monitoring the motion stroke data of the ejection mechanism related to the missile launching device in the ejection stage; technicians are helped to know the working condition of the ejection mechanism.

Description

Technical Field

[0001] The present invention relates to an ejection travel monitoring system for an ejection mechanism in a missile launch phase, which monitors the ejection mechanism in real time by deploying a sensor on the ejection mechanism on a missile launch device, so as to obtain ejection travel data of the ejection mechanism in real time in the missile launch phase. Background Art

[0002] The missile launcher is mainly responsible for mounting missiles. In addition, during the missile launch phase, it mainly plays the role of giving the missile the initial ejection posture and speed. During use, the missile may fail to execute the mission due to abnormal attitude control after ejection, and the fault needs to be located and troubleshooted. However, there is no suitable hardware or software to provide data collection and data display for the ejection stroke of the ejection mechanism during the use of the launcher.

[0003] The present invention designs an ejection stroke monitoring system for an ejection mechanism in a missile launch phase, which performs real-time ejection stroke monitoring and visual display on the ejection mechanism on a missile launch device, thereby realizing real-time collection of motion stroke data of the ejection mechanism in the ejection phase and offline data visual display. The data recorded by the sensor can be used to preliminarily judge whether the ejection stroke of the ejection mechanism in the missile launch phase meets the design expectations, assist maintenance personnel in analyzing and diagnosing and making maintenance decisions, and further grasp the motion conditions of the ejection mechanism in the ejection phase, thereby realizing the update and iteration of the ejection mechanism design. Summary of the invention

[0004] The present invention aims to solve the problem that the movement of the ejection mechanism of the domestic missile launch device during the missile ejection stage is unclear. A data collection and visualization system based on an angle sensor is proposed to realize the real-time collection of the motion stroke data of the ejection mechanism during the ejection stage and the offline data visualization display. The data recorded by the sensor can preliminarily judge whether the ejection stroke of the ejection mechanism during the missile launch stage meets the design expectations, assist maintenance personnel in analyzing and diagnosing and making maintenance decisions, and then grasp the movement of the ejection mechanism during the ejection stage, and realize the update and iteration of the ejection mechanism design.

[0005] The present invention provides an ejection travel monitoring system for an ejection mechanism in a missile launch phase, which includes an ejection travel monitoring module, a data storage module and a ground visualization platform;

[0006] Ejection travel monitoring module: collects the travel motion data of the ejection mechanism in the launcher through the sensor fixed on the ejection mechanism, providing data support for technicians;

[0007] Data storage module: stores the data collected in the ejection stroke monitoring module;

[0008] Ground visualization platform: collects and displays data in the data storage module to assist technicians in monitoring the working conditions of the ejection mechanism of the missile launcher.

[0009] The ejection stroke monitoring module includes an angle sensor installed on the ejection mechanism; wherein the angle sensor is used to collect the rotation angle of the relevant rotating mechanism in the ejection mechanism, and its deployment is to determine the installation position of the sensor based on the motion analysis of the relevant motion mechanism.

[0010] The data storage module is a data storage device, including a power supply component, a collection component, a controller, a storage chip and a Gigabit network port;

[0011] Power supply component: converts the upper power supply into the power supply for the electronic components in the equipment;

[0012] Acquisition component: converts the angle sensor analog signal into a digital signal;

[0013] Controller: used to control the operation of data storage devices and provide computing power support;

[0014] Storage chip: used to store angle data generated in real time;

[0015] Gigabit network port: used for high-speed data exchange between data storage devices and ground visualization platform.

[0016] The ground visualization platform is a high-performance computer equipped with data visualization software, which provides a local visualization and storage platform for all previous data.

[0017] The data visualization software can obtain motion travel data from the data storage module through the gigabit network port; visualize the motion travel data through the data visualization algorithm, help technicians determine the working conditions of the missile launch device during the ejection phase, assist technicians in judging the device conditions, and provide data support for the design and maintenance of the missile launch device.

[0018] The present invention is applicable to an airborne ejection-type missile launcher. The present invention has the advantages and beneficial effects of: the present invention proposes an ejection stroke monitoring system for an ejection mechanism in a missile launching phase, solves the problem of online acquisition and storage of ejection mechanism stroke data of an ejection-type missile launcher, provides powerful data and technical support for the movement of the ejection mechanism of an ejection-type missile launcher in the missile launching phase, thereby improving the understanding of the missile launcher, clarifying the movement process of the launcher, providing a data basis for data analysis for missile and launcher manufacturers, and improving corresponding military benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1It is a schematic diagram of the ejection stroke monitoring system of the ejection mechanism in the missile launching phase of the present invention.

[0020] Figure 2 It is a schematic diagram of installing the angle displacement sensor of the present invention.

[0021] Figure 3 It is a structural schematic diagram of the data storage device of the present invention.

[0022] Figure 4 It is a schematic diagram of the data visualization software interface carried by the ground visualization platform of the present invention.

[0023] Figure 5 It is a logical schematic diagram of the data visualization software installed on the ground visualization platform of the present invention. DETAILED DESCRIPTION

[0024] The present invention is further described in detail below in conjunction with specific implementations and drawings. The present invention provides a system for monitoring the ejection travel of an ejection mechanism during a missile launch phase. Figure 1 As shown in FIG. 1 , the system includes three parts: ejection travel monitoring module, data storage module and ground visualization platform. The following describes the operation process of the ejection travel monitoring system for the ejection mechanism of the missile launch phase.

[0025] The motion stroke data includes the rotation angle data of the rotating components in the angle ejection mechanism, the installation position of the angle sensor, the angle relationship of each component and the size of the related components. Figure 2 shown.

[0026] The sensors of the sensor assembly are powered by data storage devices, and the XC8224RBB power chip and XC9883QNB power chip are used to reduce the aircraft power supply voltage for powering the storage device and the angle sensor. After the angle sensor is powered on, it will generate a data stream of angle changes over time.

[0027] The sensors in the sensor group are connected to the data storage device through signal lines (the internal design of the data storage device is as follows Figure 3 As shown in FIG. 1 , the data storage device uses a JFMQL20S control chip and a FAD7606 acquisition chip to convert the sensor data from analog signals to digital signals. After the above conversion, the JFMQL20S control chip stores the digital signal in the SMFC32GBMP storage chip.

[0028] After the sensor information collected by the master control JFMQL20S is stored in the storage module, the ground station reads back the stored information through the Gigabit Ethernet bus and imports the angle data into the data visualization software for data analysis and visualization.

[0029] In the data visualization software, according to (x-l1cosα) 2 +(l1sinα-q) 2 =l2 2 To calculate the motion stroke of the ejection mechanism, α is the angle measured by the angle sensor, l1 and l2 are the lengths of the two rotating rods in the ejection mechanism, q is the deviation of the connection from the center point of the ejection mechanism, and x is the motion stroke of the ejection mechanism to be calculated. The data streams x1 and x2 of the motion stroke of the front and rear ejection mechanisms that change with time are calculated, and the formula Calculate the pitch attitude angle of the missile at the moment it leaves the missile launcher to assist in determining the initial attitude of the missile, where Δs is the motion travel data difference between the front and rear ejection mechanisms, L is the distance between the front and rear ejection mechanisms, and θ is the pitch attitude angle of the missile.

[0030] Since there is noise in the original data, after x1, x2 and θ are calculated, IRLS (iterative reweighted least squares) is used to calculate a continuous nonlinear curve to fit the original data (where time is the independent variable, x1, x2 and θ are the dependent variables of each curve). After the continuous nonlinear curve is obtained, the curve can be differentiated to obtain the movement speed v1 of the front ejection mechanism, the movement speed v2 of the rear ejection mechanism, the missile attitude angular velocity θ′, the movement acceleration a1 of the front ejection mechanism, the movement acceleration a2 of the rear ejection mechanism and the missile attitude angular acceleration θ″; in addition, in order to ensure the reliability of the data, Locally Weighted Linear Regression (LWLR) is introduced to calculate the discontinuous nonlinear curve, through the formula: and Among them, l is displacement, v is velocity, and a is acceleration, so that the displacement with noise is calculated to obtain the velocity with noise and the acceleration with noise, and then the displacement, velocity and acceleration with noise removed are obtained by using the LWLR algorithm respectively. The results of the two algorithms correct the data mutually, which is convenient for users to have a certain understanding of the data.

[0031] The data visualization software interface is as follows Figure 4 As shown, the software logic is as follows Figure 5 As shown, the software provides a visualization window for a single or all ejection mechanism travel data obtained from a data storage device. By displaying the visualization of the front and rear angle sensor data, the movement of the front and rear ejection mechanisms during the ejection process can be understood. By analyzing the motion travel data, it can be understood whether the ejection mechanism is operating normally.

Claims

1. A system for monitoring the ejection travel of an ejection mechanism during the missile launch phase, characterized in that: The system includes an ejection travel monitoring module, a data storage module and a ground visualization platform; Ejection travel monitoring module: collects the travel motion data of the ejection mechanism in the launcher through the sensor fixed on the ejection mechanism, providing data support for technicians; Data storage module: stores the data collected in the ejection stroke monitoring module; Ground visualization platform: collects and displays data in the data storage module to assist technicians in monitoring the working conditions of the ejection mechanism of the missile launcher, identify faults and improve the design.

2. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 1, characterized in that: The ejection stroke monitoring module includes an angle sensor installed on the ejection mechanism.

3. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 2, characterized in that: The angle sensor is used to collect the rotation angle of the relevant rotating mechanism in the ejection mechanism. The deployment of the angle sensor is to determine the installation quantity and position of the sensor based on the motion analysis of the relevant motion mechanism.

4. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 1, characterized in that: The data storage module is a data storage device, including a power supply component, a collection component, a controller, a storage chip and a Gigabit network port; Power supply component: converts the upper power supply to the equipment power supply standard; Acquisition component: converts the angle sensor analog signal into a digital signal; Controller: used to control the operation of data storage devices and provide computing power support; Storage chip: used to store angle data generated in real time; Gigabit network port: used for high-speed data exchange between data storage devices and ground visualization platform.

5. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 1, characterized in that: The ground visualization platform is a high-performance computer equipped with data visualization software, which provides a local visualization and storage platform for all previous data.

6. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 5, characterized in that: The data visualization software can obtain motion travel data from the data storage module through the gigabit network port; visualize the motion travel data through the data visualization algorithm, help technicians determine the working conditions of the missile launch device during the ejection phase, assist technicians in judging the device conditions, and provide data support for the design and maintenance of the missile launch device.

7. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 5 or 6, characterized in that: In the data visualization software, according to (x-l1cosα) 2 +(l1sinα-q) 2 =l2 2 To calculate the motion stroke of the ejection mechanism, α is the angle measured by the angle sensor, l1 and l2 are the lengths of the two rotating rods in the ejection mechanism, q is the deviation of the connection from the center point of the ejection mechanism, and x is the motion stroke of the ejection mechanism that needs to be calculated.

8. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 7, characterized in that: The data streams x1 and x2 of the movement stroke of the front and rear ejection mechanisms over time are calculated and the formula Calculate the pitch attitude angle of the missile at the moment it leaves the missile launcher to assist in determining the initial attitude of the missile, where Δs is the motion travel data difference between the front and rear ejection mechanisms, L is the distance between the front and rear ejection mechanisms, and θ is the pitch attitude angle of the missile.

9. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 8, characterized in that: Since there is noise in the original data, after x1, x2 and θ are calculated, IRLS is used to calculate a continuous nonlinear curve to fit the original data, in which time is used as the independent variable, x1, x2 and θ are used as the dependent variables of each curve. After the continuous nonlinear curve is obtained, the curve is differentiated to obtain the movement speed v1 of the front ejection mechanism, the movement speed v2 of the rear ejection mechanism, the missile attitude angular velocity θ′, the movement acceleration a1 of the front ejection mechanism, the movement acceleration a2 of the rear ejection mechanism and the missile attitude angular acceleration θ″.

10. The ejection travel monitoring system for an ejection mechanism in a missile launch phase according to claim 9, characterized in that: In order to ensure the reliability of the data, the local weighted linear regression LWLR is introduced to calculate the discontinuous nonlinear curve, through the formula: and Among them, l is the displacement, v is the velocity, and a is the acceleration, so that the noisy displacement is calculated to obtain the noisy velocity and the noisy acceleration, and the LWLR algorithm is used to obtain the noise-removed displacement, velocity and acceleration.

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