Underwater test device for aircraft and use method of underwater test device

Abstract

According to the underwater test device and the using method thereof, under the condition that the underwater angle of the aircraft is known, a sensor is fixed to the point position, making contact with the water surface first, of the head of the aircraft, multiple physical parameters such as pressure and impact acceleration at the underwater moment of the aircraft can be obtained, different head modules are replaced, and the underwater test of the aircraft can be achieved. The underwater vehicle head deformation measurement device can adapt to different water entry angles, basically adopts the same mechanism, obtains the measurement effect of multiple physical quantities, and can effectively improve the test precision and the test efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft water entry testing, and in particular to an aircraft water entry testing device and a use method thereof. Background Art

[0002] The whole process of a spacecraft entering water generally refers to the time course from the head touching the water to the spacecraft being completely wetted. The water entry process is a transient, dynamic, and complex mechanical process. The spacecraft is in a three-phase coupled state. At the same time, there is a strong interaction between the air, water, and spacecraft, accompanied by a series of complex physical phenomena, which brings difficulties to the theoretical analysis of some water entry phenomena. Therefore, the water entry test is an indispensable part of the water entry process research. At the same time, the water entry test also provides a complete example for numerical simulation analysis, which can be used to determine the effectiveness and correctness of numerical simulation analysis.

[0003] The water entry test mainly includes water entry pressure measurement, overload acceleration measurement, and aircraft head deformation and damage measurement. At present, the water entry pressure measurement and overload acceleration measurement are more studied, while the experimental research on aircraft head deformation and damage measurement is relatively small.

[0004] Currently, the main method of measuring water entry pressure is to install a pressure sensor at the exact center of the vehicle's head for measurement. This method is relatively accurate in measuring the water entry pressure of a vertically water-entering vehicle. However, when the vehicle enters the water at an angle, the first point of contact with the water is not at the center of the vehicle's head, but at the edge of the vehicle's head. Therefore, the measured water entry pressure will have a large error.

[0005] Therefore, it is necessary to develop a set of aircraft water entry test equipment, which can conveniently realize the measurement of water entry pressure at different water entry angles, and also realize the deformation and damage measurement of the aircraft head. These measurement data can provide an indispensable basis for subsequent numerical simulation analysis and optimization. Summary of the invention

[0006] Based on this, it is necessary to propose a set of aircraft water entry test equipment to address the above problems. It adopts a replaceable modular test head section to achieve water entry pressure measurement, aircraft head deformation and damage measurement in one set of equipment, and can realize the position of the pressure sensor as the first water contact point when entering the water at different angles through the pressure sensor adapter. To achieve the above purpose, the technical solution of the present invention is as follows:

[0007] A water entry test device for an aircraft, comprising an aircraft subsystem, a test subsystem and a simulation subsystem;

[0008] The aircraft subsystem includes a test head section, a test cylinder, and a plurality of sensors installed in or on the test head section and the test cylinder; the test subsystem includes a launch tube stand, a launch tube installed on the launch tube stand, a water pool, and a high-speed camera;

[0009] The test head section and the test cylinder are both in the shape of a body of revolution, and the test cylinder is coaxially installed with the test head section; the test head section includes three types: a pressure test head section, a crushing effect test head section and a strain test head section;

[0010] The pressure test head section is used to test the pressure of the aircraft at the moment of entering the water, and the pressure test head section is equipped with a pressure sensor;

[0011] The crushing effect test head section is used to test the damage to the head of the aircraft when the aircraft enters the water;

[0012] The strain test head section is used to test the head strain of the vehicle when entering water;

[0013] An overload sensor is installed in the test cylinder or / and the test head section;

[0014] The launch tube stand can adjust the launch angle of the launch tube and the distance between the launch tube and the water pool according to the test purpose;

[0015] The water pool is used to receive the aircraft subsystem after being launched from the launch tube;

[0016] The simulation subsystem is used for simulating the dynamic response of the aircraft subsystem entering the water at a given angle, including but not limited to the pressure, velocity, acceleration, strain, stress and deformation of the test head section during the water entry process.

[0017] The present invention also discloses a method for using a water-entry test device for a spacecraft. The test device is as described above. The method for using the test device comprises the following steps:

[0018] S1: Establish a water entry simulation model for the vehicle and conduct simulation, including:

[0019] S11: establishing a simulation model of the aircraft and the water body according to the test purpose and the water entry angle, wherein the simulation model of the aircraft does not include the head of the aircraft;

[0020] S12: according to the test purpose, establishing a simulation model of the test head section, including a pressure test head section simulation model, a crushing effect test head section simulation model and a strain test head section simulation model;

[0021] S13: according to the test requirements, combining the aircraft simulation model, the water body simulation model and the simulation model of the test header to obtain the aircraft water entry simulation model;

[0022] S14: using appropriate means to perform simulation calculation on the water-entry simulation model of the aircraft to obtain the water-entry dynamic response of the aircraft; in the simulation calculation process used in this step, the calculation method and calculation parameters used for the first time are selected and set based on existing knowledge;

[0023] S15: According to the test results, the calculation method and calculation parameters used in S14 are adjusted to obtain a new dynamic response of the vehicle entering the water, and the new dynamic response is compared with the test results. If the comparison result meets the test requirements, the test is completed, otherwise, the test is returned to S14;

[0024] S2: Conduct water entry test of the aircraft and obtain test results, including:

[0025] S21: According to the test purpose, the test head section is selected and installed with the test cylinder, including electrical installation and structural installation;

[0026] When pressure testing is selected, it is also necessary to select an adapter according to the water entry angle to ensure that the pressure sensor point is the first point where the aircraft subsystem contacts the water surface under the given water entry angle;

[0027] S22: adjusting the angle of the launch tube stand and the distance between the launch tube stand and the water pool according to the test purpose and the water entry angle;

[0028] S23: loading the installed aircraft subsystem into the launch tube;

[0029] S24: turning on the high-speed camera according to the test purpose, and photographing the water entry point position of the aircraft subsystem;

[0030] S25: launching the aircraft subsystem into water, reading the sensor data and the high-speed camera video results, and obtaining the test results;

[0031] S26: Enter step S15.

[0032] Implementing the embodiments of the present invention will have the following beneficial effects:

[0033] Through the replaceable modular test head, multiple physical quantities can be measured on the same test device with good repeatability, avoiding the inconsistency caused by the large-scale replacement of test equipment; at the same time, it can realize the pressure measurement of water entry at various angles, with good test economy, providing an indispensable foundation for subsequent numerical simulation analysis and optimization. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] 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 only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0035] in:

[0036] Figure 1 It is a schematic diagram of the aircraft head section of the present invention being a pressure test head section and entering water at an angle.

[0037] Figure 2 It is a schematic diagram of the pressure test header section of the present invention.

[0038] Figure 3 It is a cross-sectional schematic diagram of the pressure test head section of the present invention.

[0039] Figure 4 It is a schematic diagram of the strain test head section of the present invention.

[0040] Figure 5 It is a cross-sectional schematic diagram of the strain test head section of the present invention.

[0041] Figure 6 It is a schematic diagram of the crushing effect test head section of the present invention.

[0042] Figure 7 It is a cross-sectional schematic diagram of the crushing effect test head section of the present invention. DETAILED DESCRIPTION

[0043] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions 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. 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.

[0044] A water entry test device for an aircraft comprises an aircraft subsystem, a test subsystem and a simulation subsystem.

[0045] Generally speaking, the test device refers to the actual physical / chemical test, but considering the test cost and the rapid improvement of numerical simulation methods, simulation tests have also become an indispensable part of the test.

[0046] The aircraft water entry test device disclosed in the present invention includes an aircraft subsystem and a test subsystem for actual testing, and also includes a simulation subsystem. The test results obtained from the actual test can provide sufficiently reliable examples for the simulation test, and provide a basis for adjusting the simulation method and simulation parameters.

[0047] The aircraft subsystem includes a test head section 1, a test cylinder 2, and a plurality of sensors installed in or on the test head section 1 and the test cylinder 2. The test cylinder 2 is consistent with the actual shape of the aircraft.

[0048] The appearance of the test head section 1 is basically consistent with the actual head section of the aircraft, but its internal structure can be adjusted according to the test purpose. The test head section and the test cylinder are both in the shape of a rotating body, and the test cylinder is installed coaxially with the test head section.

[0049] Please refer to Figure 2-7 The test head section 1 includes three types: a pressure test head section, a crushing effect test head section, and a strain test head section. The crushing effect test head section has the thinnest wall thickness to ensure that the head section can be crushed during the water entry process; the strain test head section has the thickest wall thickness to ensure that the strain test head section will not be damaged during the water entry process. The thickness of the pressure test head section is in the middle, and in a specific embodiment, it should be consistent with the actual head section of the aircraft.

[0050] The pressure test head section is used to test the pressure of the aircraft at the moment of entering the water. The pressure test head section is equipped with a pressure sensor. The outside of the pressure test head section is provided with a pressure sensor installation slot 101 from the center along the busbar direction. The pressure sensor is installed in the pressure sensor installation slot through an adapter plug-in; the adapter plug-in can adjust the distance between the pressure sensor and the axis of the aircraft, and at the same time ensure that the pressure sensor is located on the outer surface of the pressure test head section to ensure that the pressure sensor point is the first point of contact between the aircraft subsystem and the water surface when the water entry angle is given.

[0051] In a specific embodiment, Figure 2-3 As shown, the pressure sensor mounting groove is shown as 101 in the figure.

[0052] The crushing effect test head section is used to test the damage to the head of the vehicle when the vehicle enters the water.

[0053] The strain test head section 1 is used to test the head strain of the vehicle when entering the water.

[0054] One or more overload sensors are installed in the test cylinder or / and the test head section. In a specific embodiment, the overload sensor is an inertial group sensor.

[0055] The test subsystem includes a launch tube stand, a launch tube mounted on the launch tube stand, a water pool and a high-speed camera. The launch tube stand can adjust the launch angle of the launch tube and the distance between the launch tube and the water pool according to the test purpose. The water pool 3 is used to receive the aircraft subsystem after being launched from the launch tube.

[0056] The simulation subsystem is used for simulation calculation of the dynamic response of the aircraft subsystem entering the water at a given angle, including but not limited to the pressure, velocity, acceleration, strain, stress and deformation of the test head section during the water entry process.

[0057] The method for using the water entry test device disclosed in the present invention includes the following steps:

[0058] S1: Establish a water entry simulation model for the vehicle and conduct simulation, including the following steps:

[0059] S11: Establish a simulation model of the aircraft and the water body according to the test purpose and the water entry angle. The simulation model of the aircraft does not include the head of the aircraft.

[0060] S12: According to the test purpose, a simulation model of the test head section is established, including a pressure test head section simulation model, a crushing effect test head section simulation model and a strain test head section simulation model.

[0061] S13: According to the test requirements, the aircraft simulation model, the water body simulation model and the simulation model of the test header are combined to obtain the aircraft water entry simulation model.

[0062] S14: Use appropriate means to perform simulation calculations on the vehicle entry into water simulation model to obtain the dynamic response of the vehicle entering water; in the simulation calculation process used in this step, the calculation method and calculation parameters used for the first time are selected and set based on existing knowledge.

[0063] S15: According to the test results, the calculation method and calculation parameters used in S14 are adjusted to obtain a new dynamic response of the vehicle entering the water, and compared with the test results. If the comparison results meet the test requirements, the test is completed, otherwise return to S14.

[0064] S2: Conduct water entry test of the aircraft and obtain test results, including:

[0065] S21: According to the test purpose, select the test head section and complete the installation with the test cylinder, including electrical installation and structural installation.

[0066] When pressure testing is selected, the adapter plug-in must be selected according to the water entry angle to ensure that the pressure sensor point is the first point where the vehicle subsystem contacts the water surface at the given water entry angle;

[0067] S22: Adjust the angle of the launch tube stand and the distance between the launch tube stand and the pool according to the test purpose and the water entry angle.

[0068] S23: Load the installed aircraft subsystem into the launch tube.

[0069] S24: Turn on the high-speed camera according to the test purpose and take pictures of the water entry point of the vehicle subsystem;

[0070] S25: Launch the vehicle subsystem into the water, read the sensor data and high-speed camera video results, and obtain the test results.

[0071] S26: Go to step S15, compare with the simulation result, and provide examples for simulation method and parameter adjustment.

[0072] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0073] The above embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A water entry test device for an aircraft, characterized in that: It includes the aircraft subsystem, experimental test subsystem and simulation subsystem; The aircraft subsystem includes a test head section, a test cylinder, and a plurality of sensors installed in or on the test head section and the test cylinder; the test subsystem includes a launch tube stand, a launch tube installed on the launch tube stand, a water pool, and a high-speed camera; The test head section and the test cylinder are both in the shape of a body of revolution, and the test cylinder is coaxially installed with the test head section; the test head section includes three types: a pressure test head section, a crushing effect test head section and a strain test head section; The pressure test head section is used to test the pressure of the aircraft at the moment of entering the water, and the pressure test head section is equipped with a pressure sensor; The crushing effect test head section is used to test the damage to the head of the aircraft when the aircraft enters the water; The strain test head section is used to test the head strain of the vehicle when entering water; An overload sensor is installed in the test cylinder or / and the test head section; The launch tube stand can adjust the launch angle of the launch tube and the distance between the launch tube and the water pool according to the test purpose; The water pool is used to receive the aircraft subsystem after being launched from the launch tube; The simulation subsystem is used for simulating the dynamic response of the aircraft subsystem entering the water at a given angle, including but not limited to the pressure, velocity, acceleration, strain, stress and deformation of the test head section during the water entry process.

2. The aircraft water entry test device according to claim 1, characterized in that: A pressure sensor mounting groove is provided on the outside of the pressure test head section from the center along the busbar direction, and the pressure sensor is installed in the pressure sensor mounting groove through an adapter plug-in; the adapter plug-in can adjust the distance between the pressure sensor and the axis of the aircraft, while ensuring that the pressure sensor is located on the outer surface of the pressure test head section to ensure that under the given water entry angle, the pressure sensor point is the first point where the aircraft subsystem contacts the water surface.

3. The aircraft water entry test device according to claim 1, characterized in that: The overload sensor is an inertial group sensor.

4. A method for using a water-entry test device for an aircraft, the test device being as described in any one of claims 1 to 3, characterized in that: The method of use includes the following process S1: Establish a water entry simulation model for the vehicle and conduct simulation, including: S11: establishing a simulation model of the aircraft and the water body according to the test purpose and the water entry angle, wherein the simulation model of the aircraft does not include the head of the aircraft; S12: according to the test purpose, establishing a simulation model of the test head section, including a pressure test head section simulation model, a crushing effect test head section simulation model and a strain test head section simulation model; S13: according to the test requirements, combining the aircraft simulation model, the water body simulation model and the simulation model of the test header to obtain the aircraft water entry simulation model; S14: using appropriate means to perform simulation calculation on the water-entry simulation model of the aircraft to obtain the water-entry dynamic response of the aircraft; in the simulation calculation process used in this step, the calculation method and calculation parameters used for the first time are selected and set based on existing knowledge; S15: According to the test results, the calculation method and calculation parameters used in S14 are adjusted to obtain a new dynamic response of the vehicle entering the water, and the new dynamic response is compared with the test results. If the comparison result meets the test requirements, the test is completed, otherwise, the test is returned to S14; S2: Conduct water entry test of the aircraft and obtain test results, including: S21: According to the test purpose, the test head section is selected and installed with the test cylinder, including electrical installation and structural installation; When pressure testing is selected, it is also necessary to select an adapter according to the water entry angle to ensure that the pressure sensor point is the first point where the aircraft subsystem contacts the water surface under the given water entry angle; S22: adjusting the angle of the launch tube stand and the distance between the launch tube stand and the water pool according to the test purpose and the water entry angle; S23: loading the installed aircraft subsystem into the launch tube; S24: turning on the high-speed camera according to the test purpose, and photographing the water entry point position of the aircraft subsystem; S25: launching the aircraft subsystem into water, reading the sensor data and the high-speed camera video results, and obtaining the test results; S26: Enter step S15.

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