A missile launch phase ejection mechanism ejection stroke monitoring system

Abstract

The application provides a missile launching stage ejection mechanism ejection stroke monitoring system, the system comprises: an ejection stroke monitoring module: composed of sensors deployed on the missile launcher ejection mechanism, real-time ejection collects stroke data; a data storage module: for receiving, storing and exporting the data of the ejection stroke monitoring module; a ground visualization platform: downloading data from the data storage module and importing into the ground visualization platform for data collection and display. The application establishes a monitoring system suitable for the ejection stroke of the ejection mechanism of the missile launcher to collect, process and display the ejection stroke of the ejection mechanism in the ejection stage, assists the technical personnel in monitoring the movement stroke data of the related ejection mechanism of the missile launcher in the ejection stage, and helps the technical personnel to understand the working condition of the ejection mechanism.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of ejector travel monitoring systems for missile launch phase ejector mechanism, by sensor on the ejector mechanism of missile launcher upper deployment, real-time monitoring ejector mechanism, to obtain the ejector travel data of missile launch phase ejector mechanism in real time. BACKGROUND

[0002] Missile launcher is mainly responsible for mounting missile, in addition, in missile launch phase, it mainly plays the role of giving missile initial pop posture and speed.In use, the posture control abnormality of missile after pop may lead to the failure of missile task execution, and the fault needs to be positioned and troubleshooting.But there is no applicable hardware or software to provide data collection and data display for the ejector travel of launcher in use.

[0003] The present application designs a kind of ejector travel monitoring systems for missile launch phase ejector mechanism, and the real-time ejector travel monitoring and visual display of ejector mechanism on missile launcher are carried out, to realize the real-time collection and offline data visual display of the movement travel data of ejector mechanism in ejector phase, the data recorded by sensor can preliminarily judge whether the ejector travel of ejector mechanism in missile launch phase meets design expectation, assist maintenance personnel to analyze diagnosis and make maintenance and repair decision, and then master the movement of ejector mechanism in ejector phase, realize the update iteration of ejector mechanism design. SUMMARY

[0004] The present application is to solve the problem that the movement of missile launcher in missile launch phase is unknown, and proposes a data collection and visualization system based on angle sensor, to realize the real-time collection and offline data visual display of the movement travel data of ejector mechanism in ejector phase, the data recorded by sensor can preliminarily judge whether the ejector travel of ejector mechanism in missile launch phase meets design expectation, assist maintenance personnel to analyze diagnosis and make maintenance and repair decision, and then master the movement of ejector mechanism in ejector phase, realize the update iteration of ejector mechanism design.

[0005] The present application provides a kind of ejector travel monitoring systems for missile launch phase ejector mechanism, including ejector travel monitoring module, data storage module and ground visualization platform;

[0006] Ejector travel monitoring module: the travel movement data of ejector mechanism in launcher is collected by sensor fixed on ejector mechanism, to provide data support for technical personnel;

[0007] Data storage module: the data collected in ejector travel monitoring module is stored;

[0008] The ground visualization platform collects and displays the data in the data storage module, and assists the technical personnel in monitoring the working condition of the missile launching device ejection mechanism.

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

[0010] The data storage module is a data storage device, which comprises a power supply component, an acquisition component, a controller, a storage chip and a gigabit network port.

[0011] The power supply component converts the power supply from the upper level into the power supply for the electronic components in the device.

[0012] The acquisition component converts the analog signal of the angle sensor into a digital signal.

[0013] The controller is used to control the operation of the data storage device and provide computing power support.

[0014] The storage chip is used to store the real-time generated angle data.

[0015] The gigabit network port is used for high-speed data exchange between the data storage device and the ground visualization platform.

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

[0017] The data visualization software can obtain the motion stroke data from the data storage module through the gigabit network port, and visualize the motion stroke data through the data visualization algorithm, so as to help the technical personnel determine the working condition of the missile launching device in the ejection stage, assist the technical personnel in judging the device condition, and provide data support for the design and maintenance of the missile launching device.

[0018] The present application is suitable for airborne ejection type missile launching device, and the advantages and beneficial effects of the present application are that the ejection stroke monitoring system for the ejection mechanism in the missile launching stage is provided, the online acquisition and storage of the ejection mechanism stroke data of the ejection type missile launching device are solved, powerful data and technical support are provided for the motion of the ejection mechanism in the missile ejection stage of the ejection type missile launching device, thereby improving the understanding of the missile launching device, clarifying the motion process of the launching device, providing data analysis data basis for the missile and launching device manufacturers, and improving the corresponding military benefit. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1This is a schematic diagram of the ejection stroke monitoring system for the ejection mechanism during the missile launch phase according to the present invention.

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

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

[0022] Figure 4 This is a schematic diagram of the data visualization software interface mounted on the ground visualization platform of the present invention.

[0023] Figure 5 This is a logical diagram of the data visualization software mounted on the ground visualization platform of the present invention. Detailed Implementation

[0024] The present invention will be further described in detail below with reference to specific embodiments and accompanying drawings. The present invention provides a catapult stroke monitoring system for a missile launch mechanism during the launch phase, such as... Figure 1 As shown, the system comprises three parts: a launch stroke monitoring module, a data storage module, and a ground visualization platform. The following describes the operation of the launch stroke monitoring system for the missile launch mechanism during the missile launch phase.

[0025] The motion travel data includes the rotation angle data of the rotating components in the angle ejection mechanism, the installation position of the angle sensor, the angular relationship between each component, and the dimensions of relevant components, such as... Figure 2 As shown.

[0026] The sensors in the sensor assembly are powered by the data storage device. XC8224RBB and XC9883QNB power chips are used to step down the aircraft's power supply voltage to power the storage device and the angle sensor, respectively. The angle sensor generates a data stream showing the angle changing over time after being powered on.

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

[0028] The sensor information collected by the main controller JFMQL20S is stored in the storage module. The ground station then reads back the stored information via 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, the motion stroke of the ejection mechanism is calculated according to (x-l1cosα) 2 +(l1sinα-q) 2 =l2 2 wherein α is the angle measured by the angle sensor, l1 and l2 are the lengths of two rotating rods in the ejection mechanism, q is the deviation of the connecting point from the center point position 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 strokes of the front and rear ejection mechanisms changing with time are calculated through the formula The pitch attitude angle of the missile at the moment of leaving the missile launcher is calculated to assist in judging the initial attitude of the missile, wherein Δs is the data difference of the motion strokes of 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 (wherein time is the independent variable and x1, x2 and θ are the dependent variables of the respective curves), and after the continuous nonlinear curve is obtained, the curve can be differentiated to obtain the motion velocities v1 and v2 of the front and rear ejection mechanisms, the attitude angular velocity θ' of the missile, the motion accelerations a1 and a2 of the front and rear ejection mechanisms, and the attitude angular acceleration θ" of the missile. In addition, in order to ensure the reliability of the data, locally weighted linear regression (LWLR) is introduced to calculate a discontinuous nonlinear curve, through the formula: and wherein l is the displacement amount, v is the velocity amount, and a is the acceleration amount, so that the displacement amount containing noise is calculated to obtain the velocity amount containing noise and the acceleration amount containing noise, and the noise-removed displacement amount, velocity amount and acceleration amount are obtained by using the LWLR algorithm respectively. The results of the two algorithms correct each other, which is convenient for the user to have a certain understanding of the data.

[0031] The data visualization software interface is shown in Figure 4 The software logic is shown in Figure 5 The software provides a visualization window for the single or historical ejection mechanism stroke data obtained from the data storage device, and the motion of the front and rear ejection mechanisms in the ejection process is understood through the visualization of the data of the front and rear two angle sensors, and whether the ejection mechanism is normally operated can be understood through the analysis of the motion stroke data.

Claims

1. A launch stroke monitoring system for a missile launch phase ejection mechanism, characterized by: The system comprises an ejection stroke monitoring module, a data storage module and a ground visualization platform; The ejection stroke monitoring module collects the stroke movement data of the ejection mechanism in the launching device through the sensor fixed on the ejection mechanism to provide data support for the technicians; The data storage module stores the data collected in the ejection stroke monitoring module; The ground visualization platform collects and displays the data in the data storage module to assist the technicians in monitoring the working condition of the ejection mechanism of the missile launching device and determining the fault and improving the design; In the ejection stroke monitoring module, an angle sensor is installed on the ejection mechanism. wherein the movement stroke of the ejection mechanism is calculated in the data visualization software according to (x - l1cosα) 2 + (l1sinα - q) 2 = l2 2 wherein α is the angle measured by the angle sensor, l1, l2 are the lengths of two rotating rods in the ejection mechanism, q is the deviation of the connection point from the center point position of the ejection mechanism, and x is the movement stroke of the ejection mechanism to be calculated.

2. A launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 1, wherein: The angle sensor is used to collect the rotation angle of the relevant rotating mechanism in the ejection mechanism, and the deployment of the angle sensor determines the number and position of the sensors installed on the motion analysis of the relevant motion mechanism.

3. The launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 1, wherein: The data storage module is a data storage device, which comprises a power supply component, an acquisition component, a controller, a storage chip and a gigabit network port. The power supply component converts the power supply from the upper level into the standard of the device power supply. The acquisition component converts the analog signal of the angle sensor into a digital signal. The controller is used to control the operation of the data storage device and provides computing power support. The storage chip is used to store the real-time generated angle data. The gigabit network port is used for high-speed data exchange between the data storage device and the ground visualization platform.

4. The launch stroke monitoring system for a missile launch phase ejection mechanism according to claim 1, characterized in that: The ground visualization platform is a high-performance computer loaded with data visualization software, which provides a local visualization and storage platform for historical data.

5. A launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 4, wherein: The data visualization software can obtain the motion stroke data from the data storage module through the gigabit network port, and visualize the motion stroke data through the data visualization algorithm to help the technicians determine the working condition of the missile launching device in the ejection stage and assist the technicians in judging the device condition, thereby providing data support for the design and maintenance of the missile launching device.

6. A launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 1, wherein: The data flow x1, x2 of the movement stroke of the front and rear ejection mechanism changing with time is calculated by formula The pitch attitude angle of the missile at the moment of leaving the missile launcher is calculated to assist in judging the initial attitude of the missile, wherein Δs is the data difference of the movement stroke of the front and rear ejection mechanism, L is the distance of the front and rear ejection mechanism, and θ is the pitch attitude angle of the missile.

7. A launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 6, wherein: Since there is noise in the original data, a continuous nonlinear curve is calculated using IRLS to fit the original data after calculating x1, x2 and θ, where time is the independent variable and x1, x2 and θ are the dependent variables of the respective curves. After obtaining the continuous nonlinear curve, the curve is differentiated to obtain the motion speed v1 of the front ejection mechanism, the motion speed v2 of the rear ejection mechanism, the attitude angular velocity θ' of the missile, the motion acceleration a1 of the front ejection mechanism, the motion acceleration a2 of the rear ejection mechanism and the attitude angular acceleration θ'' of the missile.

8. A launch stroke monitoring system for a missile launch phase ejection mechanism as claimed in claim 7, wherein: To ensure the reliability of data, local weighted linear regression (LWLR) is introduced to calculate the non-continuous nonlinear curve through the formula: and wherein, l is displacement, v is velocity, and a is acceleration, so that the displacement containing noise is calculated to obtain the velocity containing noise and the acceleration containing noise, and the displacement, velocity and acceleration without noise are obtained by using the LWLR algorithm respectively.

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