A high-intensity missile flight measurement and recording system
By integrating a high-intensity missile flight measurement and recording system into the missile body, the problems of insufficient parameter monitoring and insufficient protection capabilities of the test system during missile flight are solved, and the stability in continuous monitoring and high-impact environments are achieved.
Patent Information
- Application Number
- CN202421639092.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-11
- Publication Date
- 2025-04-08
- Estimated Expiration
- 2034-07-11
AI Technical Summary
The existing missile flight measurement and recording system is insufficient to monitor the parameters during flight, and the testing system's protection capabilities are insufficient to ensure its stability during the crash.
Design a high-intensity missile flight measurement and recording system to achieve continuous monitoring by integrating the measurement system into the missile body and powering it in a built-in battery. The system uses buffer pads, shock absorbing springs and buffer materials for protection, and integrates static three-axial acceleration sensors, dynamic acceleration sensors, temperature and humidity sensors and gyroscopes to obtain a variety of flight parameters.
It realizes comprehensive monitoring and recording of parameters during missile flight, ensuring that the system is not damaged in a high-impact environment, can continuously supply power and obtain a variety of flight parameters.
Smart Images
Figure CN222733633U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of artillery shells, and in particular relates to a high-intensity missile flight measurement and recording system. Background Art
[0002] During missile testing, it is necessary to monitor various flight parameters during flight. Existing technical tests are mainly based on telemetry, which tests few parameters and cannot cover the entire process from launching to falling. In addition, during flight, many parameters cannot be tested due to lack of power supply; at the same time, the protection capability of the test system is not enough to ensure its ability to withstand crashes. Utility Model Content
[0003] The utility model aims to provide a high-intensity missile flight measurement and recording system to solve the technical problems in the prior art that the monitoring parameters are few, continuous monitoring cannot be performed, and the protection capability of the test system is poor.
[0004] The technical solution adopted by the utility model to solve its technical problems is:
[0005] A high-intensity missile flight measurement and recording system is used to be installed in a shell to measure the flight data of a shell, comprising: a shell, the shell is a cylindrical structure with one end open, the top open end of the shell is connected to a mounting seat by bolts, the top surface of the mounting seat is connected to a boss on the inner side of the shell by mounting bolts, the mounting seat is close to the shell connection end, and a plurality of impact sensors are embedded and installed on the side of the mounting seat away from the shell connection end, a collection box is arranged in the space of the shell, a controller is arranged in the collection box, the impact sensor is electrically connected to the controller, and a data reading socket is arranged at the bottom of the shell, and the data reading socket is electrically connected to the controller.
[0006] The utility model discloses a high-strength missile flight measurement and recording system. A buffer pad is provided between the shell and the mounting seat, and the mounting bolt passes through the buffer pad.
[0007] The utility model discloses a high-strength missile flight measurement and recording system. A plurality of shock-absorbing springs are sleeved on the buffer pad where the mounting bolts pass through.
[0008] The utility model discloses a high-strength missile flight measurement and recording system, wherein a buffer material is provided between the collection box and the shell.
[0009] The utility model discloses a high-intensity missile flight measurement and recording system. An acceleration sensor and a gyroscope are integrated in the collection box. The acceleration sensor and the gyroscope are electrically connected to a controller.
[0010] The utility model discloses a high-intensity missile flight measurement and recording system. A storage battery is arranged in the collection box to supply power to the system.
[0011] The utility model discloses a high-strength missile flight measurement and recording system. The number of the impact sensors is four, which respectively measure the lateral load, the vertical load, the longitudinal load and the loading load. The impact sensors are installed in the non-shock absorption area.
[0012] The utility model provides a high-strength missile flight measurement and recording system, wherein the shell is made of high-strength aluminum alloy.
[0013] The beneficial effects of the utility model are as follows: a high-intensity missile flight measurement and recording system is proposed, which integrates the measurement system in the missile body and is powered by a built-in battery, so that the system does not rely on the missile system, thereby realizing uninterrupted power testing during flight; by arranging a buffer pad, a spring and a buffer material, the collection box is prevented from being impacted to ensure that the circuit board is not damaged; by integrating a static three-axial acceleration sensor, four large-impact dynamic acceleration sensors, a temperature and humidity sensor, and a gyroscope in the system, the system can obtain a variety of parameters. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which:
[0015] Figure 1 It is a schematic diagram of an embodiment of the utility model;
[0016] Figure 2 is a partial cross-sectional view of a cushion according to an embodiment of the utility model;
[0017] Figure 3 It is an external axonometric diagram of an embodiment of the utility model;
[0018] Figure 4 is a cross-sectional view of the impact sensor installation structure of an embodiment of the utility model;
[0019] Figure 5 It is a schematic diagram of the structure of the buffer material of an embodiment of the utility model;
[0020] Figure 6 This is a schematic diagram of the piezoelectric effect principle of the sensor of the embodiment of the utility model;
[0021] Figure 7 It is a vertical cross-sectional view of the impact sensor distribution of an embodiment of the utility model;
[0022] Figure 8 It is a longitudinal cross-sectional view of the impact sensor distribution of an embodiment of the utility model. DETAILED DESCRIPTION
[0023] In order to make the purpose, technical scheme and advantages of the embodiment of the utility model clearer, the technical scheme in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. It should be understood that the specific embodiments described herein are only used to explain the utility model and are not used to limit the utility model. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.
[0024] like Figure 1-6 As shown, a high-intensity missile flight measurement and recording system is used to be installed in a shell 1 to measure the flight data of a shell, comprising: a shell 2, the shell 2 is a cylindrical structure with one end open, the top open end of the shell 2 is connected to a mounting seat 4 by bolts, the top surface of the mounting seat 4 is connected to the boss inside the shell 1 by mounting bolts, the mounting seat 4 is close to the shell connection end 5, and a plurality of impact sensors 6 are embedded and installed on the side of the mounting seat 4 away from the shell connection end 5, a collection box 7 is arranged in the space of the shell 2, a controller is arranged in the collection box 7, the impact sensor 6 is electrically connected to the controller, and a data reading socket 8 is arranged at the bottom of the shell 2, and the data reading socket 8 is electrically connected to the controller.
[0025] It should be noted that the technical solution of this application is the development of an in-bore overload test system for artillery shells to monitor the various postures and parameters of missiles during flight. It mainly stores impact parameters and rotation parameters for download and revisit. The core of this system is that it does not require additional power supply, has its own battery, has extremely strong impact protection performance, and integrates multiple sensor parameters, as well as data acquisition, edge computing and other functions. The impact sensor is installed on an aluminum alloy mounting seat 4, which can directly withstand external impact force without buffering, such as Figure 7-8 As shown, the four sensors are an X-direction impact sensor 61, a Y-direction impact sensor 62, a Z-direction impact sensor 63 and an X-direction load sensor 64. The above sensors are directly rigidly connected for impact testing without a buffer structure.
[0026] The system can be installed in the missile bay to monitor the loading load, axial load and lateral load in the barrel during the loading and unloading process, as well as the static attitude load based on gravity acceleration and the speed signal of the gyroscope to calculate the speed. Through the data collection and recording of the device and the data processing of the host computer software, the impact load data, speed and time-varying patterns of the shell loading and unloading process are visualized. The device is equipped with a trigger switch, which passes through the cabin to the outside of the missile body through the trigger cable. After the system is opened, it can connect to the network port for communication and download data.
[0027] The PCB in the collection box 7 is particularly important. Although there is a large buffer on the outside, the structural strength of the PCB still needs to be strengthened. The PCB adopts the method of potting process, which can prevent the circuit from being corroded by chemical substances such as water, acid, alkali, etc., improve its stability and durability, increase the circuit's adaptability to temperature, ensure that the normal operation of the circuit is not affected by temperature, improve the insulation performance of the circuit, and reduce the influence of factors such as leakage and inductance. The potted epoxy resin glue is hard after curing, is not easy to disassemble after potting, has high hardness, and has high impact resistance. And after potting, it has the ability of flame retardancy and heat conduction, which will also optimize the performance of the circuit board.
[0028] In a preferred embodiment of the utility model, a buffer pad 3 is provided between the housing 2 and the mounting seat 4, and the mounting bolt passes through the buffer pad 3. In a preferred embodiment of the utility model, a plurality of shock absorbing springs are provided at the position where the mounting bolt passes through the buffer pad 3. In a preferred embodiment of the utility model, a buffer material 9 is provided between the collection box 7 and the housing 2, and the buffer material 9 is foamed aluminum.
[0029] The collection box and the acceleration sensor require sufficient buffering to ensure that they are not damaged. Therefore, a rubber buffer pad 3 is added between the mounting seat 4 and the shell 2 as the first layer of buffering. That is, when an impact comes, the mounting seat 4 directly bears the impact, and then transfers it to the buffer pad 3 for the first buffering, and then transfers it to the shock-absorbing spring inside the buffer pad 3 for the second buffering. Finally, it is transferred to the buffer material 9 made of foam aluminum for the third buffering. After three bufferings, the acceleration borne by the collection box 7 and the acceleration sensor is theoretically close to 0, that is, it has basically been completely attenuated.
[0030] In terms of high-performance buffering, the protection buffering of the collection box and the acceleration sensor must be considered. The structure adopts a two-level buffering structure design. Therefore, foamed aluminum is proposed to be used as the second-level buffering, which is used for filling between the shell 2 and the collection box 7 to protect the collection box. Since foamed aluminum is an isotropic metal material that can adjust the elastic modulus by changing the density, it has high bending stiffness and shock wave absorption capacity. Among more buffering materials, such as rubber, nylon, epoxy resin, etc., foamed aluminum has the best and most effective ability to absorb shock waves.
[0031] The rubber pad is designed to be nitrile rubber or other shock-absorbing rubber pads, which have good cushioning performance. For example, the surface area of the rubber pad is 32.11cm 2 According to the estimated compression of 30%, 15.2kgf can be generated per square centimeter, so an impact of 15.2*32.11=488kgf can be generated on the rubber pad.
[0032] The shock-absorbing spring is made of structural steel and is designed according to a rectangular surface area. The force generated by the spring can be predicted based on the compression amount and the inner and outer diameters. According to the simulation design and material parameters, a 20% compression of the spring can generate a spring force greater than 45kgf. This system is designed for 4-12 springs. This application uses 8 springs as an example, and the total spring force is 8*45=360kgf. In summary, external buffering can achieve a total buffering of 360+488=848kgf, achieving 100% buffering of large impacts.
[0033] The internal buffer structure is mainly realized by aluminum foam. The expected compression amount is within the elastic range. The aluminum foam has a 50% change at a porosity of 84%, which can absorb more than 2.5 MJ / m 3 Aluminum foam with a porosity of 84% undergoes a 50% change and can absorb more than 2.5 MJ / m 3 The total volume of the buffer foam aluminum is 227271.181*2+ 79533.736 cubic millimeters, about (0.53*10-3) m 3 , the expected compression is 20%, that is (0.1*10-3)m 3 , it can absorb 100J of energy. The system is expected to receive an impact force of about 100kgf inside. When the foam aluminum is compressed by 20%, a compression greater than 30mm is achieved, and the impact energy generated is 29.2J, which is much smaller than the 100J energy that the foam aluminum can absorb. Therefore, it can effectively protect the collection device inside.
[0034] In a preferred embodiment of the utility model, an acceleration sensor and a gyroscope are integrated in the acquisition box 7, and the acceleration sensor and the gyroscope are electrically connected to the controller.
[0035] In a preferred embodiment of the present utility model, a storage battery is arranged in the collection box 7 to supply power to the system.
[0036] In a preferred embodiment of the present invention, there are four impact sensors 6 for measuring the lateral load, vertical load, longitudinal load and loading load respectively.
[0037] In a preferred embodiment of the utility model, the material of the shell 2 is a high-strength aluminum alloy material. The most important requirement of the system is the impact protection design, and its core considerations are high-strength impact resistance and high-performance buffering. In terms of impact resistance, in the shell structure design, the shell is made of high-strength aluminum alloy, and its impact sensor is directly mounted on the shell, which can withstand its 20000g acceleration to ensure the testing of the impact sensor. The shell uses high-strength aluminum alloy as the first-level buffer, so that it will not deform or the deformation is as small as possible under high-strength, high-pressure, and high-impact acceleration conditions, and will not cause extrusion damage to the internal circuit board. Therefore, the shell is made of various aluminum alloys or titanium alloys, etc. This application takes 7090 aluminum alloy as an example for explanation, and the tensile strength of 7090 aluminum alloy is ≥730MPa. Its mechanical properties are close to those of stainless steel, and it can theoretically withstand acceleration shocks exceeding 40000g.
[0038] In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.
[0039] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances. In addition, in the description of the present utility model, unless otherwise specified, "plurality" means two or more.
[0040] It should be understood that those skilled in the art can make improvements or changes based on the above description, and all these improvements and changes should fall within the scope of protection of the claims attached to the utility model.
Claims
1. A high-intensity missile flight measurement and recording system, used for being installed in a shell (1) to measure the flight data of a projectile, characterized in that: include: A shell (2) is provided, wherein the shell (2) is in a cylindrical structure with one end open, the top open end of the shell (2) is connected to a mounting seat (4) by means of bolts, the top surface of the mounting seat (4) is connected to a boss on the inner side of the shell (1) by means of mounting bolts, the mounting seat (4) is close to the shell connection end (5), and a plurality of impact sensors (6) are embedded and installed on the side of the mounting seat (4) away from the shell connection end (5), a collection box (7) is provided in the space of the shell (2), a controller is provided in the collection box (7), the impact sensor (6) is electrically connected to the controller, and a data reading socket (8) is provided at the bottom of the shell (2), and the data reading socket (8) is electrically connected to the controller.
2. A high-intensity missile flight measurement and recording system according to claim 1, characterized in that: A buffer pad (3) is provided between the housing (2) and the mounting seat (4), and the mounting bolt passes through the buffer pad (3).
3. A high-intensity missile flight measurement and recording system according to claim 2, characterized in that: The buffer pad (3) is provided with a plurality of shock absorbing springs at a position where the mounting bolts pass through.
4. A high-intensity missile flight measurement and recording system according to claim 3, characterized in that: A buffer material (9) is provided between the collection box (7) and the housing (2).
5. A high-intensity missile flight measurement and recording system according to claim 4, characterized in that: An acceleration sensor and a gyroscope are integrated in the acquisition box (7), and the acceleration sensor and the gyroscope are electrically connected to the controller.
6. A high-intensity missile flight measurement and recording system according to claim 5, characterized in that: A storage battery is arranged in the collection box (7) to supply power to the system.
7. A high-intensity missile flight measurement and recording system according to claim 1, characterized in that: The impact sensors (6) are four in number and respectively measure the lateral load, the vertical load, the longitudinal load and the loading load.
8. A high-intensity missile flight measurement and recording system according to claim 1, characterized in that: The shell (2) is made of high-strength aluminum alloy.