Comprehensive measurement system for icebreaking experiment of navigation body under conditions of pressure reduction and low temperature

Abstract

The invention provides a navigation body icebreaking experiment comprehensive measurement system under reduced pressure and low temperature conditions. The navigation body icebreaking experiment comprehensive measurement system comprises an experiment water tank, an environment temperature monitoring system, a projectile body measurement system, a launch canister measurement system, an environment pressure monitoring system, an image measurement system and a data acquisition system. The environment temperature monitoring system is installed on the inner wall of the experimental water tank, the environment pressure monitoring system is installed on the inner side wall of the experimental water tank, and the projectile body measuring system comprises a projectile body model and is arranged in water in the experimental water tank; the launch canister measurement system comprises a launch canister, the launch canister is installed in the experimental water tank, and the bottom of the projectile body model is in butt joint with the top of the launch canister; and the image measuring system and the data acquisition system are arranged outside the experimental water tank. According to the invention, atmospheric pressure, atmospheric temperature and water environment temperature in an experimental environment can be effectively measured; the physical quantities of pressure and temperature are monitored, and the method has important significance for accurately controlling experiment influence factors and ensuring the accuracy and repeatability of the experiment.

Description

Technical Field

[0001] The present invention relates to the technical field of underwater launch experiment testing of a navigation body, and in particular to a comprehensive measurement system for icebreaking experiments of a navigation body under decompression and low temperature conditions. Background Art

[0003] Underwater model ejection experiment is an important method to study the process of a navigation body from the beginning of launch to the exit from the water. It has low cost, short experimental cycle, and can better simulate the physical process of the navigation body from the launch of the vehicle to the complete crossing of the water surface. Based on the above advantages, underwater model ejection experiments of navigation bodies have been widely carried out, but with the deepening of research, researchers want to obtain more experimental data to carry out relevant kinematic and dynamic analysis, and at the same time provide reference for numerical simulation and guide actual design work. Therefore, how to obtain more experimental data to make each experiment more valuable is a question that experimenters have been thinking about.

[0004] In the underwater ejection model experiments of navigation bodies currently carried out, decompression ejection experiments are rarely carried out, so little attention is paid to environmental pressure. In addition, the water exit experiment of navigation bodies in low-temperature environments is also a new topic, and the monitoring of water temperature and air temperature is very important. In the model ejection experiments currently carried out, little attention is paid to the ejection pressure parameters, and the initial experimental conditions are unclear, so it is difficult to guide the simulation. The hydrodynamic characteristics and kinematic characteristics of the navigation body during the water exit are the core of the experiment, but due to the limitations of testing technology, there are few valid data that can be obtained. Summary of the invention

[0005] In response to the technical problems raised above, a comprehensive measurement system for icebreaking experiments of navigation bodies under decompression and low temperature conditions is provided.

[0006] The technical means adopted by the present invention are as follows:

[0007] A comprehensive measurement system for icebreaking experiments of navigation bodies under decompression and low temperature conditions, including: an experimental water tank, an environmental temperature monitoring system, a missile body measurement system, a launch tube measurement system, an environmental pressure monitoring system, an image measurement system and a data acquisition system;

[0008] The environmental temperature monitoring system is installed on the inner wall of the experimental water tank to monitor the temperature of the gas and water inside the experimental water tank;

[0009] The environmental pressure monitoring system is installed on the inner side wall of the experimental water tank and is used to monitor the gas pressure inside the experimental water tank;

[0010] The projectile measurement system includes a projectile model placed in water inside an experimental water tank;

[0011] The launch tube measurement system comprises a launch tube, which is installed inside the experimental water tank, and the bottom of the projectile model is docked with the top of the launch tube;

[0012] The image measurement system is placed outside the experimental water tank and is used to observe the entire process of the projectile model from the beginning of ejection to the exit from the water, and to measure image information;

[0013] The data acquisition system is placed outside the experimental water tank, and the environmental temperature monitoring system, the projectile measurement system, the launch tube measurement system, the environmental pressure monitoring system and the image measurement system are all electrically connected to the data acquisition system.

[0014] Furthermore, the ambient temperature monitoring system includes an ambient temperature sensor, which includes at least one water temperature sensor and at least one air temperature sensor, wherein the water temperature sensor is placed below the water surface, and the air temperature sensor is placed above the water surface.

[0015] Furthermore, the environmental pressure monitoring system includes at least one environmental pressure sensor, which is a gas pressure sensor with a measurement range of -0.1 MPa to 1 MPa.

[0016] Further, the main body of the projectile model is a projectile shell, and a high-frequency water pressure sensor, a six-axis inertial combination sensor system, a data acquisition storage unit and a power supply are arranged inside the projectile shell, and at least one threaded hole is respectively opened on the head and shoulder of the projectile shell, and a high-frequency water pressure sensor is installed at each of the threaded holes; a metal support is arranged inside the projectile shell, and screw holes are arranged on the metal support, and the six-axis inertial combination sensor system, the data acquisition storage unit and the power supply are respectively installed on the metal support through the screw holes;

[0017] The six-axis inertial combination sensor system includes at least one six-axis inertial combination sensor, and the data acquisition storage unit includes an electrically connected first data acquisition card and a storage module. The first data acquisition card has multiple data acquisition interfaces, which are electrically connected to the high-frequency water pressure sensor and the six-axis inertial combination sensor, and is used to simultaneously acquire data from multiple sensors and transmit the acquired data to the storage module for storage; the power supply is used to power the high-frequency water pressure sensor and the first data acquisition card.

[0018] Furthermore, the projectile model satisfies a certain reduction ratio relationship, and its reduction ratio range is between 1:20 and 1:30. The projectile shell is composed of a projectile head and a projectile body. The projectile head satisfies a streamlined rotating shell, and the projectile body is a cylindrical shell.

[0019] Furthermore, the six-axis inertial combination sensor is composed of a three-axis acceleration sensor and a three-axis gyroscope. The three-axis acceleration sensor is used to measure acceleration in three directions of X, Y, and Z, with a range of ±16g; the three-axis gyroscope has a range of ±2000° / s and is used to output physical quantities, which include at least time, acceleration, gyroscope, and Euler angle.

[0020] Furthermore, the launch tube is a cylinder made of metal, an air chamber is provided at the bottom of the launch tube, a limit groove is provided at the top of the air chamber, and a plurality of sealing rings are equidistantly provided on the limit groove; a plurality of threaded holes are provided on the side wall on the back flow side of the launch tube, and an ejection pressure sensor electrically connected to the data acquisition system is installed at each threaded hole.

[0021] Furthermore, the ejection pressure sensor is a high-frequency dynamic high-temperature pressure sensor with a measurement range of 0-2Mpa; three ejection pressure sensors are provided, and the three ejection pressure sensors are arranged on the same busbar of the launch tube, and the head of each ejection pressure sensor is provided with an external thread, and the external thread is matched and connected with the internal thread of the launch tube;

[0022] Three sealing rings are equidistantly arranged on the limit groove from top to bottom, namely the first sealing ring, the second sealing ring and the third sealing ring; the three ejection pressure sensors are respectively the first ejection pressure sensor, the second ejection pressure sensor and the third ejection pressure sensor, the first ejection pressure sensor is arranged at a position 2 / 3 away from the bottom of the air chamber, the second ejection pressure sensor is arranged at a position 1 / 2 between the second sealing ring and the third sealing ring, and the third ejection pressure sensor is arranged at a distance of 1 / 10 from the muzzle of the launch tube.

[0023] Further, the data acquisition system includes a signal transmitter and receiver, a second data acquisition card, a computer and a display, the signal transmitter and receiver are connected to the second data acquisition card, the second data acquisition card is connected to the computer, the computer is connected to the display, and the ambient temperature monitoring system, the launch tube measurement system, the ambient pressure monitoring system and the image measurement system are all electrically connected to the signal transmitter and receiver;

[0024] The pressure data monitored by the ambient temperature sensor, the transmitting tube measurement system, and the ambient pressure sensor are transmitted to the second data acquisition card through the signal transmitter and receiver, and a signal curve is generated on the computer and displayed on the monitor; the image measurement system transmits the collected image to the computer in real time; the transmitting tube measurement system and the image measurement system are connected together through the signal transmitter and receiver, and the transmitting tube measurement system and the image measurement system are synchronously controlled to perform measurement.

[0025] Furthermore, the image measurement system includes a tripod and a high-speed camera installed on the tripod, and the high-speed camera is used to observe the entire process of the projectile model from the beginning of ejection to the emergence from the water, and measure image information; the sampling frame rate of the high-speed camera reaches 40,000 frames / s, and high frame rate shooting is used to collect the motion characteristics and fluid flow characteristics of the projectile model during the emergence from the water, and to capture the interaction characteristics of the projectile model with the water surface and ice layer.

[0026] Compared with the prior art, the present invention has the following advantages:

[0027] 1. The system of the present invention can effectively measure the atmospheric pressure, atmospheric temperature and water environment temperature in the experimental environment. Atmospheric pressure and water environment temperature have a great influence on the cavitation characteristics of the navigation body. Monitoring the physical quantities of pressure and temperature is of great significance for accurately controlling the influencing factors of the experiment and ensuring the accuracy and repeatability of the experiment.

[0028] 2. The system of the present invention can measure the ejection pressure in the launch, and can quantitatively understand the process of the flying body ejecting from the tube. At the same time, it can provide more accurate initial ejection parameters, thus providing a reference for numerical simulation.

[0029] 3. The system of the present invention can measure the hydrodynamic parameters and motion posture parameters of the projectile model during the process of exiting the water, which is an improvement in the underwater ejection test technology of the navigation body. Measuring more parameters can maximize the experimental benefits.

[0030] Based on the above reasons, the present invention can be widely promoted in the fields of underwater launch experiment and testing of navigation bodies. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0032] Figure 1 It is a schematic diagram of the overall structure of the measurement system of the present invention.

[0033] Figure 2 It is a schematic diagram of the structure of the projectile measurement system of the present invention.

[0034] Figure 3 It is a schematic diagram of the structure of the launch tube measurement system of the present invention.

[0035] Figure 4 It is a schematic diagram of the structure of the camera system and data acquisition system of the present invention.

[0036] In the figure: 1. Experimental water tank; 2. Ambient temperature sensor; 3. Projectile measurement system; 4. Launch tube measurement system; 5. Ambient pressure sensor; 6. Image measurement system; 7. Data acquisition system;

[0037] 3-1, projectile shell; 3-2, high-frequency water pressure sensor; 3-3, six-axis inertial combined sensor system; 3-4, first data acquisition card; 3-5, power supply;

[0038] 4-1, launch tube body; 4-2, ejection pressure sensor;

[0039] 7-1. Signal transmitter and receiver; 7-2. Second data acquisition card; 7-3. Computer; 7-4. Display. DETAILED DESCRIPTION

[0040] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0043] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps described in these embodiments do not limit the scope of the present invention. At the same time, it should be clear that, for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. The technology, methods and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0044] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention: the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0045] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below their position devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0046] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0047] In order to solve the problem of difficulty in measuring various physical fields during the water exit process of a freely ejected vehicle under low temperature and reduced pressure environment, the present invention provides a comprehensive measurement system for icebreaking experiments of a vehicle under reduced pressure and low temperature conditions.

[0048] The present invention discloses a comprehensive measurement system for icebreaking experiments of navigation bodies under decompression and low temperature conditions, comprising an experimental water tank 1, an ambient temperature sensor 2, a projectile measurement system 3, a launch tube measurement system 4, an ambient pressure sensor 5, an image measurement system 6 and a data acquisition system 7.

[0049] The experimental water tank 1 is an overall closed structure during the experiment, and the internal air temperature and water temperature are relatively low. Therefore, an ambient temperature sensor 2 is set to measure the temperature. There are two ambient temperature sensors 2, which are set on the box wall on the front of the experimental water tank 1, including a water temperature sensor and an air temperature sensor. The water temperature sensor is set 1m below the water surface, and the air temperature sensor is set 0.5m above the water surface. Both ambient temperature sensors 2 are connected to the computer 7-3 of the data acquisition system 7. Before starting the ejection experiment, the internal gas is extracted by a rotary vane vacuum pump, and an ambient pressure sensor 5 is set to monitor the gas pressure inside the experimental water tank 1. The ambient pressure sensor 5 is an air pressure sensor with a measurement range of -0.1MPa to 1MPa. The gas pressure sensor (ambient pressure sensor 5) is installed on the upper and side box walls of the experimental water tank 1 through threads, and the ambient pressure sensor 5 is connected to the computer 7-3.

[0050] The projectile measurement system 3 includes a projectile model, the main body of the projectile model is a projectile shell 3-1, the projectile model meets a certain reduction ratio relationship, and its reduction ratio range is between 1:20 and 1:30. The projectile shell 3-1 is composed of a projectile head and a projectile body. The projectile head meets the streamlined rotating shell, and the projectile body is a cylindrical shell. Threaded holes of specific sizes are opened on the projectile head and the projectile shoulder. A metal support is arranged inside the projectile, and a screw hole of specific size is arranged on the metal support. The threaded holes opened on the projectile head and the projectile shoulder are used to install a high-frequency water pressure sensor 3-2 (hydrodynamic pressure sensor). A six-axis inertial combination sensor system 3-3, a data acquisition storage unit, and a power supply 3-5 are arranged inside the projectile. The six-axis inertial combination sensor system 3-3 includes at least one six-axis inertial combination sensor. The data acquisition storage unit is composed of a first data acquisition card 3-4 and a storage module. The first data acquisition card 3-4 has multiple data acquisition interfaces. In this embodiment, the first data acquisition card 3-4 has 10 channels (data acquisition interfaces) and can collect data from 10 sensors at the same time. The storage module is connected to the first data acquisition card 3-4 and is used to store the measurement data of the hydrodynamic pressure sensor and the six-axis inertial combination sensor. The data acquisition storage unit is installed on the metal support inside the projectile by screws. The high-frequency water pressure sensor 3-2 is connected to the first data acquisition card 3-4, and the first data acquisition card 3-4 stores the collected data in the storage module, and the power supply 3-5 supplies power to the high-frequency water pressure sensor 3-2 and the first data acquisition card 3-4. The six-axis inertial combination sensor system 3-3, the first data acquisition card 3-4, and the power supply 3-5 are fixed to the metal support inside the projectile by screws. The six-axis inertial combination sensor consists of a three-axis accelerometer and a three-axis gyroscope. The three-axis accelerometer can measure acceleration in the three directions of X, Y, and Z, with a range of ±16g. The three-axis gyroscope has a range of ±2000° / s and can output physical quantities such as time, acceleration, gyroscope, and Euler angle. The six-axis inertial combination sensor is installed on the metal support inside the projectile by screws.

[0051] The launch tube measurement system 4 includes a launch tube, and the top of the launch tube is connected to the bottom of the projectile model. The launch tube is a cylinder made of metal (i.e., the launch tube body 4-1), and an air chamber is arranged at the bottom of the launch tube. There is a limit groove on the top of the air chamber, and three sealing rings are arranged equidistantly from top to bottom on the limit groove. Three threaded holes are provided on the side wall of the launch tube, and their sizes are consistent with those of the ejection pressure sensor 4-2, which are used to install the ejection pressure sensor 4-2. The ejection pressure sensor 4-2 is a high-frequency dynamic high-temperature pressure sensor, and its measurement range is 0-2MPa. There are three ejection pressure sensors 4-2, which are three high-frequency air pressure sensors, which are respectively installed on the back flow side of the launch tube (the ejection pressure sensor 4-2 head has a thread, and the thread is matched with the launch tube thread and installed on the launch tube). The three high-frequency air pressure sensors are arranged on the same busbar of the launch tube. The first high-frequency air pressure sensor is arranged at a position 2 / 3 of the distance from the bottom of the air chamber. The second high-frequency air pressure sensor is arranged at a position 1 / 2 between the second and third sealing rings. The third high-frequency air pressure sensor is arranged at 1 / 10 of the distance from the muzzle of the launch tube. All three high-frequency air pressure sensors are connected to the computer 7-3.

[0052] The image measurement system 6 includes a tripod and a high-speed camera mounted on the tripod. The main function of the high-speed camera is to observe the entire process of the projectile model from the beginning of ejection to the emergence from the water through the visualization window set on the experimental water tank 1, and measure the image information for subsequent analysis. The sampling frame rate of the high-speed camera can reach 4000 frames / s, and high frame rate shooting is used to collect the motion characteristics and fluid flow characteristics of the projectile model during the emergence from the water, and at the same time, it is convenient to capture the interaction characteristics between the projectile model and the water surface and ice layer.

[0053] The data acquisition system 7 is composed of a signal transmitter and receiver 7-1, a second data acquisition card 7-2, a computer 7-3, and a display 7-4. The ambient temperature sensor 2, the transmitting tube measurement system 4, the ambient pressure sensor 5, and the image measurement system 6 are all connected to the signal transmitter and receiver 7-1. The pressure data monitored by the ambient temperature sensor 2, the transmitting tube measurement system 4, and the ambient pressure sensor 5 are transmitted to the second data acquisition card 7-2 through the signal transmitter and receiver 7-1, and a signal curve is generated on the computer 7-3 and displayed on the display 7-4. The image measurement system 6 transmits the image back to the computer 7-3 in real time, connects the transmitting tube measurement system 4 and the image measurement system 6 together through the signal transmitter and receiver 7-1, and synchronously controls the two systems to start measurement.

[0054] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A comprehensive measurement system for icebreaking experiments on navigation bodies under decompression and low temperature conditions, characterized in that: include: Experimental water tank (1), environmental temperature monitoring system, projectile measurement system (3), launch tube measurement system (4), environmental pressure monitoring system, image measurement system (6) and data acquisition system (7); The environmental temperature monitoring system is installed on the inner wall of the experimental water tank (1) and is used to monitor the temperature of the gas and water inside the experimental water tank (1); The environmental pressure monitoring system is installed on the inner side wall of the experimental water tank (1) and is used to monitor the gas pressure inside the experimental water tank (1); The projectile measurement system (3) comprises a projectile model placed in water inside the experimental water tank (1); The launch tube measurement system (4) comprises a launch tube, which is installed inside the experimental water tank (1), and the bottom of the projectile model is docked with the top of the launch tube; The image measurement system (6) is placed outside the experimental water tank (1) and is used to observe the entire process of the projectile model from the beginning of ejection to the exit from the water, and to measure image information; The data acquisition system (7) is placed outside the experimental water tank (1), and the environmental temperature monitoring system, the projectile measurement system (3), the launch tube measurement system (4), the environmental pressure monitoring system and the image measurement system (6) are all electrically connected to the data acquisition system (7).

2. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 is characterized in that: The environmental temperature monitoring system comprises an environmental temperature sensor (2), wherein the environmental temperature sensor (2) comprises at least one water temperature sensor and at least one air temperature sensor, wherein the water temperature sensor is placed below the water surface, and the air temperature sensor is placed above the water surface.

3. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 is characterized in that: The environmental pressure monitoring system comprises at least one environmental pressure sensor (5), wherein the environmental pressure sensor (5) is a gas pressure sensor having a measurement range of -0.1 MPa to 1 MPa.

4. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 is characterized in that: The main body of the projectile model is a projectile shell (3-1), and a high-frequency water pressure sensor (3-2), a six-axis inertial combined sensor system (3-3), a data acquisition storage unit and a power supply (3-5) are arranged inside the projectile shell (3-1); at least one threaded hole is respectively opened at the head and shoulder of the projectile shell (3-1), and a high-frequency water pressure sensor (3-2) is installed at each of the threaded holes; a metal support is arranged inside the projectile shell (3-1), and screw holes are arranged on the metal support, and the six-axis inertial combined sensor system (3-3), the data acquisition storage unit and the power supply (3-5) are respectively installed on the metal support through the screw holes; The six-axis inertial combination sensor system (3-3) comprises at least one six-axis inertial combination sensor, the data acquisition storage unit comprises an electrically connected first data acquisition card (3-4) and a storage module, the first data acquisition card (3-4) having a plurality of data acquisition interfaces, being electrically connected to the high-frequency water pressure sensor (3-2) and the six-axis inertial combination sensor, and being used for simultaneously acquiring data from the plurality of sensors, and transmitting the acquired data to the storage module for storage; the power supply (3-5) is used for supplying power to the high-frequency water pressure sensor (3-2) and the first data acquisition card (3-4).

5. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 4 is characterized in that: The projectile model satisfies a certain reduction ratio relationship, and its reduction ratio range is between 1:20 and 1:

30. The projectile shell (3-1) consists of a projectile head and a projectile body. The projectile head satisfies a streamlined rotating shell, and the projectile body is a cylindrical shell.

6. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 4 is characterized in that: The six-axis inertial combination sensor is composed of a three-axis acceleration sensor and a three-axis gyroscope. The three-axis acceleration sensor is used to measure acceleration in the three directions of X, Y, and Z, and the range is ±16g; the three-axis gyroscope has a range of ±2000° / s and is used to output physical quantities, and the physical quantities include at least time, acceleration, gyroscope, and Euler angle.

7. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 is characterized in that: The launch tube is a cylinder made of metal, an air chamber is arranged at the bottom of the launch tube, a limit groove is arranged at the top of the air chamber, and a plurality of sealing rings are arranged at equal intervals on the limit groove; a plurality of threaded holes are opened on the side wall of the back flow side of the launch tube, and a ejection pressure sensor (4-2) electrically connected to a data acquisition system (7) is installed at each threaded hole.

8. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 7 is characterized in that: The ejection pressure sensor (4-2) is a high-frequency dynamic high-temperature pressure sensor with a measurement range of 0-2Mpa; three ejection pressure sensors (4-2) are provided, and the three ejection pressure sensors (4-2) are arranged on the same busbar of the launch tube, and the head of each ejection pressure sensor (4-2) is provided with an external thread, and the external thread is matched and connected with the internal thread of the launch tube; Three sealing rings are equidistantly arranged on the limit groove from top to bottom, namely the first sealing ring, the second sealing ring and the third sealing ring; the three ejection pressure sensors (4-2) are respectively the first ejection pressure sensor, the second ejection pressure sensor and the third ejection pressure sensor, the first ejection pressure sensor is arranged at a position 2 / 3 of the distance from the bottom of the air chamber, the second ejection pressure sensor is arranged at a position 1 / 2 between the second sealing ring and the third sealing ring, and the third ejection pressure sensor is arranged at a distance of 1 / 10 from the muzzle of the launch tube.

9. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 is characterized in that: The data acquisition system (7) comprises a signal transmitter and receiver (7-1), a second data acquisition card (7-2), a computer (7-3) and a display (7-4); the signal transmitter and receiver (7-1) is connected to the second data acquisition card (7-2), the second data acquisition card (7-2) is connected to the computer (7-3), the computer (7-3) is connected to the display (7-4), and the environmental temperature monitoring system, the launch tube measurement system (4), the environmental pressure monitoring system and the image measurement system (6) are all electrically connected to the signal transmitter and receiver (7-1); The pressure data monitored by the ambient temperature sensor (2), the launch tube measurement system (4), and the ambient pressure sensor (5) are transmitted to the second data acquisition card (7-2) via the signal transmitter and receiver (7-1), and a signal curve is generated on the computer (7-3) and displayed on the display (7-4); the image measurement system (6) transmits the collected image to the computer (7-3) in real time; the launch tube measurement system (4) and the image measurement system (6) are connected together via the signal transmitter and receiver (7-1), and the launch tube measurement system (4) and the image measurement system (6) are synchronously controlled to perform measurement.

10. The comprehensive measurement system for icebreaking experiment of navigation body under decompression and low temperature conditions according to claim 1 or 9, characterized in that: The image measurement system (6) comprises a tripod and a high-speed camera mounted on the tripod, wherein the high-speed camera is used to observe the entire process of the projectile model from the beginning of ejection to the emergence from the water, and to measure image information; the sampling frame rate of the high-speed camera reaches 40,000 frames / s, and high frame rate shooting is adopted to collect the motion characteristics and fluid flow characteristics of the projectile model during the emergence from the water, and to capture the interaction characteristics between the projectile model and the water surface and ice layer.

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