Test system for anti-overturning test of radar vehicle

Abstract

The invention discloses an anti-overturning test system for a radar vehicle, which comprises a radar vehicle, a simulation loading frame, a tension meter, a simulation wind load loading tower, a pull rope assembly and a stress test system, and is characterized in that the simulation loading frame is arranged on a rotary table of the radar vehicle and is used for simulating antenna working conditions of different self-weight loads through loading; one end of the pull rope assembly is connected with the simulation loading frame and is connected with the loading equipment after being turned by the simulation wind load loading tower so as to carry out vector loading on the simulation loading frame, and the tension meter is connected to the pull rope assembly in series so as to measure the magnitude of the loaded tension. The stress test system comprises a stress sheet and a static resistance strain gauge which are used for measuring stress of multiple measuring points of the radar vehicle, and a computer storage display processing system, so as to measure and process the stress of each measuring point of the loaded radar vehicle. According to the invention, the anti-overturning performance of the radar vehicle can be detected reliably, rapidly and safely.

Description

Technical Field

[0001] The invention relates to an anti-overturning test of a radar vehicle, and in particular to an anti-overturning test system for a radar vehicle. Background Art

[0002] With the rapid advancement of military technology, the number of highly maneuverable, large-area radar vehicles is increasing. The safe operation of these vehicles after deployment places increasingly stringent requirements on the vehicle's rollover resistance. Existing radar vehicle rollover resistance designs primarily rely on mechanical simulation verification, which cannot meet the requirements of actual rollover resistance testing.

[0003] Therefore, it is necessary to design an anti-rollover test device and test method for a radar vehicle. Summary of the Invention

[0004] The purpose of the present invention is to provide a test method for anti-rollover testing of a radar vehicle, so as to realize the construction of a physical test environment for the anti-rollover test.

[0005] To this end, the present invention provides an anti-overturning test system for a radar vehicle, comprising: a radar vehicle, a simulated loading frame, a dynamometer, a simulated wind load tower, a drawstring assembly, and a stress testing system. The simulated loading frame is arranged on a turntable of the radar vehicle and is used to simulate antenna working conditions with different deadweight loads by loading. One end of the drawstring assembly is connected to the simulated loading frame and is connected to a loading device after being changed in direction by the simulated wind load tower to perform vector loading on the simulated loading frame. The dynamometer is connected in series to the drawstring assembly to measure the magnitude of the loaded tension. The stress testing system comprises a stress sheet and a static resistance strain gauge for stress measurement at multiple measuring points of the radar vehicle, as well as a computer storage, display, and processing system to measure and process the stress at each measuring point of the loaded radar vehicle.

[0006] The present invention provides the first test system for the radar vehicle's anti-rollover test, which can reliably, quickly and safely test the radar vehicle's anti-rollover performance.

[0007] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0009] Figure 1 Schematic diagram of an anti-overturning test system for a radar vehicle of the present invention;

[0010] Figure 2is a structural block diagram of the stress testing system of the present invention;

[0011] Figure 3 This is a comparison chart of the radar vehicle’s actual antenna load and the simulated loading framework;

[0012] Figure 4 It is a schematic diagram of a simulated loading frame installed on the turntable of the radar vehicle of the present invention;

[0013] Figure 5 is a schematic diagram of the radar vehicle platform of the present invention;

[0014] Figure 6 Shows some measuring points arranged on the radar vehicle platform of the present invention;

[0015] Figure 7 Shows some measuring points arranged on the middle box section of the wind-resistant support leg of the radar vehicle of the present invention;

[0016] Figure 8 These are some measuring points arranged on the wind-resistant bracing ears of the radar vehicle of the present invention. DETAILED DESCRIPTION

[0017] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0018] When the radar vehicle is parked, the leveling legs and anti-rollover legs are opened and extended to touch the bottom, and the antenna is erected and unfolded. In a windy environment, it will be subjected to wind loads. The radar vehicle must meet the wind load resistance requirements of the technical indicators. The current simulation model has not been corrected through actual testing and cannot be prepared to express the wind load anti-rollover capability. Therefore, it is necessary to design a test system.

[0019] Combined with reference Figures 1 to 8 The anti-overturning test system of the radar vehicle of the present invention includes a radar vehicle 1, a simulated loading frame 2, a dynamometer 3, a simulated wind load loading tower 4, a rope assembly 5, and a stress testing system 6.

[0020] Radar vehicle 1 is the real radar vehicle chassis, and the simulated loading frame 2 replaces the real array antenna. Figure 3 and Figure 4 As shown in the figure, the advantage is that different antenna working conditions with deadweight loads can be simulated by loading. Here, it is traction loading, not wind loading.

[0021] Place the radar vehicle 1 on a flat, hard cement ground, with its side facing the simulated wind load tower 4. Open the leveling legs and anti-overturning swing legs of the radar vehicle 1 and extend them to touch the ground. Level the radar vehicle 1 as a whole and lift the tires of the entire vehicle off the ground. Use a theodolite to scan the antenna installation surface of the radar vehicle 1 and adjust the accuracy to meet the requirements.

[0022] The radar vehicle 1 platform is loaded with the required weight, and simulated loading is performed using the tension assembly 5 on the simulated loading frame 2. The simulated load magnitude and center of mass position applied by the simulated loading frame 2 are converted to the wind load magnitude. The simulated load is applied by the tension rope assembly 5, and the force magnitude is determined by the dynamometer 3. The simulated loading is then performed using the simulated wind load tower 4. The stress measurement system 6 records the stress changes and magnitude at each measurement point.

[0023] The stress testing system 6 includes a stress gauge, a static resistance strain gauge, and a computer storage, display, and processing system.

[0024] Static strain measurement uses a static resistance strain gauge. Finite element analysis and calculations determine the placement of n stress gauges. After metal surface treatment, stress gauges (preferably 45° rosettes) are attached to each of the n measurement locations. Additionally, temperature compensation stress gauges are attached to the material corresponding to the measurement point. The static resistance strain gauges are then connected to form a stress testing system 6. Data collected by the static resistance strain gauges is stored, displayed, and processed by computer analysis software.

[0025] Stress test experiments and data processing:

[0026] Check the balance of the stress acquisition system and return it to zero, and record the initial data. Connect an automatic dynamometer to the pull rope to apply force.

[0027] Starting from zero, record the strain data at each point each time the tension is increased, and continue to record the data until it reaches F. After loading to F, maintain it for a period of time, and then gradually reduce the simulated wind load tension. From F to 0, record the strain data each time the tension is reduced, and when there is no tension.

[0028] F=P×A

[0029] Where F is wind force, P is wind pressure, and A is windward area;

[0030]

[0031] Where ρ is the air density and v is the wind speed.

[0032] The test data are processed according to the calculation formulas of principal strain (Formula 1), principal stress (Formula 2) and equivalent stress (Formula 3).

[0033]

[0034] According to the fourth strength theory, the equivalent stress is

[0035]

[0036] Where, ε 1,2,3 is the principal strain, σ 1,2,3is the principal stress, σ von is the equivalent stress, E is the elastic modulus, μ is the Poisson's ratio, ε0, ε 45 , ε 90 are the stress values ​​at 0°, 45°, and 90° on the stress sheet, respectively, and α is the principal stress direction.

[0037] After the stress is measured, it is compared with the yield strength of the material used to make the radar vehicle to make a judgment.

[0038] Test Examples

[0039] The simulated loading frame 2, also known as the antenna fixture frame, consists of an arm 21 and a hydraulic cylinder simulated leg 22. The bottom end of the arm 21 is hinged to one side of the turntable, the bottom end of the hydraulic cylinder simulated leg 22 is detachably connected to the other side of the turntable, and the top end of the hydraulic cylinder simulated leg 22 is hinged to the top of the arm 21. A counterweight bearing frame 23 is provided above the arm 21 for hoisting the counterweight onto it.

[0040] Initial test state: An 8.8-ton simulated load (simulated loading frame + counterweight) is applied to the radar vehicle turntable. The center of gravity of the simulated load is consistent with the center of gravity of the antenna when it is in the 74° working state. The radar vehicle is then leveled, and it is confirmed that the 8 leveling legs and 2 wind-resistant legs are all in the load-bearing state. At this time, the radar vehicle platform tires have not yet completely left the ground. Finally, the turntable is rotated to 101° from the horizontal state, and the rope assembly passing through the simulated wind load loading tower is connected to the loading equipment, such as a trailer, to simulate wind loads and monitor the platform vehicle leg lifting and stress state.

[0041] For the convenience of description, the leveling legs and wind-resistant arms of the platform vehicle are numbered, such as Figure 5 shown.

[0042] The settings of the radar vehicle anti-rollover test conditions are shown in the following table.

[0043] Table 1 Radar vehicle anti-overturning test conditions

[0044] Working condition number Load Description Working condition 1 Under the test state, a horizontal load of 3000kg is applied by a crane Working condition 2 Based on working condition 1, the horizontal load is increased to 3875kg Working condition 3 Based on working condition 2, the horizontal load increases to 4640kg Working condition 4 Based on working condition 3, the horizontal load is reduced to 1290kg

[0045] The stress measurement points of the radar vehicle are arranged as follows:

[0046] During the test, 6 stress measuring points were arranged on the working platform and 6 stress measuring points were arranged on the wind-resistant legs, for a total of 12 measuring points. Figure 6 、 Figure 7 and Figure 8 shown.

[0047] Measuring points 1#, 2#, 7# and 8# are located on the walking platform in front of the turntable, measuring points 3# and 9# are located on the working platform behind the turntable, measuring points 5#, 6#, 11# and 12# are located on the middle box section of the wind-resistant support leg, and measuring points 4# and 10# are located on the support ears of the wind-resistant support leg.

[0048] The wind load resistance test steps are as follows:

[0049] (1) Hoist a 5.8-ton counterweight block at 0° in the antenna fixture frame. After hoisting, perform the first rough leveling. After leveling, the two leveling legs (4# and 8#) and two wind-resistant legs at the rear of the antenna vehicle are in a non-loaded state. In this state, clear each strain channel and record the zero point once.

[0050] (2) When the antenna fixture frame is hoisted from 0° to 74°, strain is collected with the state in step (1) as the zero point until the hoisting is completed;

[0051] (3) Finely level the antenna fixture at 74°. After leveling, manually confirm that all leveling legs and wind-resistant legs are in a load-bearing state. At this time, the tires of the vehicle platform have not yet completely left the ground. Then rotate the turntable to 101°, reset all channels, and collect the stress changes at each measuring point during the turntable rotation.

[0052] (4) Apply simulated wind load, reset each channel to zero, and then start data collection. Load working conditions 1, 2, 3, and 4 in sequence. Each working condition lasts for 5 minutes to keep the stress data stable. At the same time, record the leg lifting situation and stress changes under different working conditions.

[0053] (5) The experiment ends.

[0054] Stress data processing is as follows:

[0055] The strain data in this test was collected using a three-dimensional 45° strain gauge rosette, which provided the first and second in-plane principal stresses. Based on the plane stress state assumption, the principal stress in the thickness direction of the plate is assumed to be zero. In this case, the Mises equivalent stress at the measuring point can be calculated. The stress results at each measuring point after processing are shown in Tables 2 to 4.

[0056] Table 2 Stress changes at each measuring point during the antenna fixture lifting process (unit: MPa)

[0057] Measuring point 1 Measuring point 2 Measuring point 3 Measuring point 4 Measuring point 5 Measuring point 6 19.5 28 7.3 2.8 1.8 3.1 Measuring point 7 Measuring point 8 Measuring point 9 Point 10 Measuring point 11 Measuring point 12 20.2 23.8 3.8 3.1 7 2.5

[0058] Table 3 Stress changes at each measuring point during the turntable rotation (unit: MPa)

[0059] Measuring point 1 Measuring point 2 Measuring point 3 Measuring point 4 Measuring point 5 Measuring point 6 1.5 2.4 2.6 4.5 0.8 2.6 Measuring point 7 Measuring point 8 Measuring point 9 Measuring point 10 Measuring point 11 Measuring point 12 1.3 1 2.5 1.2 3.1 3.8

[0060] Table 4 Stress changes at each measuring point under wind load conditions (unit: MPa)

[0061] Working conditions / measuring points Measuring point 1 Measuring point 2 Measuring point 3 Measuring point 4 Measuring point 5 Measuring point 6 Working condition 1 6.5 54.5 6.9 / / 5.5 Working condition 2 16.2 71.7 10.6 / / 8.2 Working condition 3 37.7 99.3 19.6 / / 14 Working condition 4 2.1 20.8 3 / / 4.2 Working conditions / measuring points Measuring point 7 Measuring point 8 Measuring point 9 Measuring point 10 Measuring point 11 Measuring point 12 Working condition 1 24.4 24.8 22.8 16.8 72.4 9.8 Working condition 2 35.5 38.5 30 29.4 98.5 14.4 Working condition 3 63.4 53.5 40.3 39.4 125.4 21.6 Working condition 4 10.6 7.3 11.7 1.3 20.4 5.3

[0062] From Tables 2 to 5 above, we can see that:

[0063] (1) During the lifting process of the antenna fixture, the stress changes of 1#, 2#, 7# and 8# on the symmetrical side are relatively close, indicating that the test results are basically reliable;

[0064] (2) During the lifting and rotation of the antenna fixture, the data at most stress measurement points did not change significantly;

[0065] (3) Under wind load conditions, the 4# and 5# measuring points are located on the wind-resistant support arm where the legs are lifted, and their stress levels are not considered. The stresses of the other measuring points all show an increasing trend as the wind load increases;

[0066] (4) The maximum stress measured on the wind-resistant support leg is 125.4 MPa at the 1# measuring point (on the skin near the wind-resistant support leg ear), and the maximum stress on the working platform is 99.3 MPa at the 2# measuring point (at the edge of the triangular reinforcement rib on the working platform).

[0067] The anti-overturning leg lifting conditions are as follows:

[0068] Table 5 Statistics of leg lifting

[0069]

[0070] The foregoing description is merely an embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A radar vehicle anti-overturning test system, characterized in that: include: Radar vehicle, simulated loading frame, dynamometer, simulated wind load tower, guy wire assembly, and stress test system, The simulation loading frame is arranged on the turntable of the radar vehicle and is used to simulate antenna working conditions of different deadweight loads by loading; One end of the pull rope assembly is connected to the simulated loading frame, and after passing through the simulated wind load tower and changing direction, it is connected to the loading device to perform vector loading on the simulated loading frame. A dynamometer is connected in series to the pull rope assembly to measure the magnitude of the loading force. The stress testing system includes stress gauges and static resistance strain gauges for stress measurement at multiple measuring points of the radar vehicle, as well as a computer storage, display and processing system to measure and process the stress at each measuring point of the loaded radar vehicle.

2. The radar vehicle anti-overturning test system according to claim 1, characterized in that: The simulated loading frame includes an arm and a cylinder simulated leg. The bottom end of the arm is hinged to one side of the radar vehicle turntable, the bottom end of the cylinder simulated leg is detachably connected to the other side of the radar vehicle turntable, and the top end of the cylinder simulated leg is hinged to the upper part of the arm. A counterweight bearing frame is provided on the arm for hoisting the counterweight there.

3. The anti-overturning test system of the radar vehicle according to claim 1, characterized in that: The simulated wind load loading tower is used to constrain the loaded tension to a horizontal direction.

4. The radar vehicle anti-overturning test system according to claim 1, characterized in that: The simulated wind load loading tower is also used to adjust the loaded tension to an inclined upward state and an inclined downward state.

5. The radar vehicle anti-overturning test system according to claim 1, characterized in that: The stress gauge is a three-way 45° strain rosette.

6. The radar vehicle anti-overturning test system according to claim 1, characterized in that: The strain test data of the measured measuring points are processed according to the calculation formulas of principal strain, principal stress and equivalent stress.

7. The radar vehicle anti-overturning test system according to claim 1, characterized in that: The loading device is a trailer.

8. The radar vehicle anti-overturning test system according to claim 1, characterized in that: Apply a simulated load, i.e. the sum of the weight of the simulated loading frame and the counterweight, to the turntable of the radar vehicle, and ensure that the center of gravity of the simulated load is consistent with the center of gravity of the antenna when it is in the 74° working state.

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