Projectile body flight state detection device

Abstract

The utility model provides a projectile body flight state detection device which comprises a single chip microcomputer, an inertia measurement unit, at least one digital-to-analog converter, at least one differential amplifier, at least one magnetic sensor and a battery pack, and detection signals output by the magnetic sensor pass through the differential amplifier and the digital-to-analog converter to generate position signals; the single-chip microcomputer comprises a first data acquisition module, and acceleration data and angular velocity data detected by the inertial measurement unit in real time are obtained through the first data acquisition module; the second data acquisition module is used for acquiring the position signal to obtain position data; and the data fusion module is respectively connected with the first data acquisition module and the second data acquisition module, and integrates the acceleration data, the angular velocity data and the position data through the data fusion module to obtain flight state data. The beneficial effects of the utility model are that real-time acquisition of the flight state of the projectile body can be realized, and the flight precision of the projectile body is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of flight detection device, more particularly to a kind of projectile flight state detection device. BACKGROUND

[0002] According to whether engine and control system work in flight of projectile, its trajectory can be divided into powered flight segment (referred to as active segment) and unpowered flight segment (referred to as passive segment) two parts, according to the size of air force that warhead of passive segment is subjected to, it is divided into free flight segment (referred to as free segment) and re-entry flight segment (referred to as re-entry segment) two parts.

[0003] Active segment refers to a segment of trajectory from projectile off launching platform to head body separation, on this segment of trajectory, due to engine and control system work all the time, thus it is called active segment.

[0004] Passive segment refers to a segment of trajectory from head body separation to warhead landing, in the case of no control, warhead relies on the energy obtained at the end point of active segment to fly inertially, although control is not carried out on warhead in this segment, but force acting on it can be calculated, so that the movement of warhead can be accurately grasped, to ensure that it hits target under certain shooting accuracy requirement, if attitude control system is installed on warhead, namely provided with terminal guidance, then shooting accuracy of missile can be greatly improved.

[0005] But whether in active segment or in passive segment, due to lack of guidance system, flight state of projectile cannot be acquired in real time by control system in flight process, resulting in that flight accuracy is affected and reduced. UTILITY MODEL CONTENT

[0006] The technical problem to be solved by the utility model is to realize real-time acquisition of projectile flight state, improve projectile flight accuracy, in order to overcome the defects of above prior art (or related technology), the utility model provides a projectile flight state detection device.

[0007] The utility model provides a projectile flight state detection device, the projectile flight state detection device is loaded on projectile, and it includes:

[0008] A single-chip microcomputer, at least three input ends and at least one output end are arranged on the single-chip microcomputer;

[0009] An inertial measurement unit is connected to the first input end of the single-chip microcomputer;

[0010] At least one digital-to-analog converter is connected to the second input end of the single-chip microcomputer;

[0011] At least one differential amplifier is connected to the third input end of the single-chip microcomputer;

[0012] At least one magnetic sensor is connected to the output end of the differential amplifier and the single-chip microcomputer, respectively, and the detection signal output by the magnetic sensor is transmitted to the single-chip microcomputer through the differential amplifier and the digital-to-analog converter to generate a position signal.

[0013] A battery pack is connected to the single-chip microcomputer, the inertial measurement unit, the digital-to-analog converter, the differential amplifier, and the magnetic sensor, respectively.

[0014] The single-chip microcomputer comprises:

[0015] A first data acquisition module is configured to acquire acceleration data and angular velocity data detected by the inertial measurement unit in real time.

[0016] A second data acquisition module is configured to acquire position data from the position signal.

[0017] A data fusion module is connected to the first data acquisition module and the second data acquisition module, respectively, and is configured to integrate the acceleration data, the angular velocity data, and the position data to obtain flight state data.

[0018] Compared with the prior art, the projectile flight state detection device has the following advantages:

[0019] In the present application, the projectile flight state detection device is loaded onto the projectile, the acceleration data and the angular velocity data of the projectile are detected in real time by the inertial measurement unit, the position data of the projectile are detected in real time by the magnetic sensor, and the data signal is transmitted to the single-chip microcomputer through the differential amplifier and the digital-to-analog converter. The data fusion module integrates the acceleration data, the angular velocity data, and the position data to obtain flight state data for use by the control system of the projectile to assist in adjusting the flight attitude, realizes real-time acquisition of the flight state of the projectile, and effectively improves the flight accuracy of the projectile.

[0020] In a possible implementation, the single-chip microcomputer further comprises a reset control module configured to send a reset signal to the magnetic sensor to reset the magnetic sensor.

[0021] Compared with the prior art, the above technical solution can facilitate the reset control of the magnetic sensor.

[0022] In a possible implementation, the battery pack is a 5V lithium ion battery.

[0023] In a possible implementation, the single-chip microcomputer is an STM32H743 type single-chip microcomputer.

[0024] In a possible implementation, each of the input terminals and the output terminal is a CAN bus interface.

[0025] In a possible implementation, the differential amplifier is an AD620 type instrument amplifier.

[0026] In a possible implementation, the magnetic sensor is an HMC5883L three-axis magnetoresistance sensor. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a structure principle diagram of the utility model;

[0028] Figure 2 is a structure principle diagram of the single-chip microcomputer of the utility model;

[0029] Reference signs: 1, single-chip microcomputer; 11, first data acquisition module; 12, second data acquisition module; 13, data fusion module; 14, reset control module; 2, inertial measurement unit; 3, digital-analog converter; 4, differential amplifier; 5, magnetic sensor; 6, battery pack. DETAILED DESCRIPTION

[0030] First, those skilled in the art should understand that these implementations are only used to explain the technical principles of the embodiments of the present application, and are not intended to limit the protection scope of the embodiments of the present application. Those skilled in the art can adjust them as needed in order to adapt to specific application occasions.

[0031] The present application will be further described in detail below in combination with the drawings and specific embodiments.

[0032] Reference signs: 1, single-chip microcomputer; 11, first data acquisition module; 12, second data acquisition module; 13, data fusion module; 14, reset control module; 2, inertial measurement unit; 3, digital-analog converter; 4, differential amplifier; 5, magnetic sensor; 6, battery pack. Figure 1 and Figure 2 The embodiments of the present application disclose a projectile flight state detection device, which comprises a single-chip microcomputer 1, an inertial measurement unit 2, at least one digital-analog converter 3, at least one differential amplifier 4, at least one magnetic sensor 5, and a battery pack 6. The single-chip microcomputer 1 is provided with at least three input terminals and at least one output terminal. The inertial measurement unit 2 is connected to the first input terminal of the single-chip microcomputer 1. The digital-analog converter 3 is connected to the second input terminal of the single-chip microcomputer 1. The differential amplifier 4 is connected to the third input terminal of the single-chip microcomputer 1. The magnetic sensor 5 is respectively connected to the output terminal of the differential amplifier 4 and the single-chip microcomputer 1. The battery pack 6 is respectively connected to the single-chip microcomputer 1, the inertial measurement unit 2, the digital-analog converter 3, the differential amplifier 4, and the magnetic sensor 5. The detection signal output by the magnetic sensor 5 generates a position signal through the differential amplifier 4 and the digital-analog converter 3.

[0033] In the embodiment of the present application, the single-chip microcomputer 1 comprises a first data acquisition module 11, a second data acquisition module 12, a data fusion module 13 and a reset control module 14, the first data acquisition module 11 is configured to acquire acceleration data and angular velocity data detected by the inertial measurement unit 2 in real time, the second data acquisition module 12 is configured to acquire position data from a position signal, the data fusion module 13 is configured to integrate the acceleration data, the angular velocity data and the position data to obtain flight state data, and the reset control module 14 is configured to send a reset signal to the magnetic sensor 5 to reset the magnetic sensor 5.

[0034] In the embodiment of the present application, the battery pack 6 is a 5V lithium ion battery, the single-chip microcomputer 1 is an STM32H743 type single-chip microcomputer 1, each input and output of the single-chip microcomputer 1 is a CAN bus interface, the differential amplifier 4 is an AD620 type instrument amplifier, and the magnetic sensor 5 is an HMC5883L three-axis magnetoresistance sensor.

[0035] In the embodiment of the present application, the battery pack 6 is responsible for providing voltage to each component, the differential amplifier 4 is responsible for amplifying the output voltage of the magnetic sensor 5, the digital-to-analog converter 3 is responsible for converting an analog signal into a digital signal, and the single-chip microcomputer 1 sends a clock pulse to an external set / reset circuit to reset the magnetic sensor 5 to eliminate external interference.

[0036] In the embodiment of the present application, the number of the digital-to-analog converters 3 is set to three, the number of the differential amplifiers 4 is set to three, the number of the magnetic sensors 5 is set to three, and the number of the output ends is set to three, the magnetic sensor 5 collects the change of the surrounding magnetic field to output three pairs of differential signals, the differential signals are amplified by the corresponding differential amplifiers 4, the amplified signals are converted into digital signals by the digital-to-analog converters 3, and the digital signals are sent to the single-chip microcomputer 1 for data processing, the position data of the projectile in flight is read out, at this time, the single-chip microcomputer 1 communicates with the inertial measurement unit 2 in real time, and the acceleration and the angular velocity of the projectile in flight are read as flight attitude data.

[0037] In the description of the present application, the description of the terms “one embodiment”, “some embodiments”, “in this embodiment”, “specific examples” or “some examples” means that the specific features, mechanisms, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, mechanisms, materials or characteristics described can be combined in any suitable manner in any one or more embodiments or examples. In addition, the different embodiments or examples described in the present specification and the features of the different embodiments or examples can be combined and combined by those skilled in the art without contradiction.

[0038] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any changes or replacements within the technical scope disclosed by the present application can be easily conceived by the person skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A projectile flight state detection device, characterized by comprising: The missile flight state detection device is loaded on a missile body and comprises: a single-chip microcomputer, which is provided with at least three input ends and at least one output end; an inertial measurement unit, which is connected to a first input end of the single-chip microcomputer; at least one digital-to-analog converter, which is connected to a second input end of the single-chip microcomputer; at least one differential amplifier, which is connected to a third input end of the single-chip microcomputer; at least one magnetic sensor, which is respectively connected to the differential amplifier and the output end of the single-chip microcomputer, and outputs a detection signal through the differential amplifier and the digital-to-analog converter to generate a position signal; a battery pack, which is respectively connected to the single-chip microcomputer, the inertial measurement unit, the digital-to-analog converter, the differential amplifier and the magnetic sensor. The single-chip microcomputer comprises: a first data acquisition module, which is used to acquire acceleration data and angular velocity data detected by the inertial measurement unit in real time; a second data acquisition module, which is used to acquire position data from the position signal; a data fusion module, which is respectively connected to the first data acquisition module and the second data acquisition module, and is used to integrate the acceleration data, the angular velocity data and the position data to obtain flight state data.

2. The elastic body flight state detection device according to claim 1, characterized by The single-chip microcomputer further comprises a reset control module, which is used to send a reset signal to the magnetic sensor to reset the magnetic sensor.

3. The elastic body flight state detection device according to claim 1, characterized by The battery pack is a 5V lithium ion battery.

4. The elastic body flight state detection device according to claim 1, characterized by The single-chip microcomputer is an STM32H743 type single-chip microcomputer.

5. The elastic body flight state detection device according to claim 1, characterized by Each of the input ends and the output end is a CAN bus interface.

6. The elastic body flight state detection device according to claim 1, characterized by The differential amplifier is an AD620 type instrument amplifier.

7. The elastic body flight state detection device according to claim 1, characterized by The magnetic sensor is an HMC5883L three-axis magnetoresistance sensor.

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