Catapult take-off and arrested impact test apparatus

Abstract

The present invention belongs to the technical field of impact tests, and particularly relates to a catapult take-off and arrested impact test apparatus, comprising a supporting frame, an auxiliary supporting and guiding apparatus above the supporting frame, a mounting base below the supporting frame, a servo actuator, an oil circuit system, and a control and measurement system. The oil circuit system comprises an oil source, a low-pressure accumulator group, a high-pressure accumulator group, an oil inlet valve block, an oil return valve block, a servo valve block, an oil source low-pressure oil return pipe, an oil source high-pressure oil outlet pipe, and necessary tubes among components. The control and measurement system comprises a vibration and impact loading upper computer, a vibration impact controller, a static loading upper computer, a hydraulic servo controller, a servo valve, and an accelerometer. The servo actuator is internally provided with a displacement sensor. The present invention can be widely applied to conventional vibration and impact tests of various suspension launch apparatuses in a suspension-mounted state, as well as arrested impact tests under composite waveforms.

Description

A catapult takeoff and arresting impact test device Technical Field

[0001] The present invention belongs to the technical field of impact testing, and in particular relates to a catapult takeoff and arresting impact testing device. Background Art

[0002] An aircraft carrier is a large surface ship equipped with carrier-based fighter jets as its primary combat weapon. It provides takeoff and landing facilities for these fighter jets. As the core warship for ocean-going strikes, its carrier-based fighter jets possess formidable attack capabilities. With my country prioritizing the development of a strong maritime nation as a major national strategic task, aircraft carriers and carrier-based fighter jets have experienced unprecedented development. A launcher is a device used by aircraft to mount missiles, allowing them to be secured and carried along with the aircraft during missions. When the aircraft is ready to launch a missile, the launcher must promptly release the missile, freeing it for attack.

[0003] Arrested shock testing verifies the adaptability of carrier-based aircraft and their associated components to the shock environment encountered during landing on an aircraft carrier and catapult takeoff. It assesses the functional reliability and structural integrity of test components in these environments and is crucial for the flight safety of carrier-based aircraft throughout their service life. Although the pulse amplitude associated with this environment is relatively low, its duration and frequency of occurrence are long, potentially causing significant dynamic / low-cycle fatigue damage to improperly designed equipment. An aircraft typically conducts 200 sorties per year, over 67% of which involve catapult takeoffs and arrested landings. Laboratory testing, by simulating multiple catapult takeoffs and landings in multiple axes, ensures that most significant defects can be identified and corrected. With the development of my country's aircraft carriers and carrier-based aircraft, the demand for arrested shock testing of airborne components is increasing. Arrested shock testing is essential for suspended launch systems, air-to-air missiles, air-to-ground missiles, wing sensors, and other components. At present, there are three main assessment modes for the assessment requirements of single-unit carrier-based aircraft: one is to conduct assessment by reproducing complex time domain waveforms through measured data; one is a half-sine wave classic shock test (amplitude is generally ≤12g, pulse width is generally 140ms or 200ms); and one is a damped sine wave shock test. Since the real environment of arresting shock has the characteristics of complex transient positive and negative attenuation, in the absence of corresponding actual test data, it is more accurate and effective to conduct test assessment through damped sine wave shock. For the damped sine wave shock test, for different product installation locations, the overall different test conditions are given as shown in Formula 2-1 and Table 1. y=A m e -ξωt sin(ωt) (0≤t≤T) (2-1)

[0004] Where: y——transient wave acceleration, unit is g;

[0005] A m ——transient wave amplitude, unit: g;

[0006] ξ——damping ratio, take 0.025;

[0007] ω——modal circular frequency, unit rad / s;

[0008] t——time, unit s.

[0009] Table 1 Typical arresting impact test conditions

[0010] As shown in Table 1, typical arresting shock conditions all use a single damped sine wave. The shock conditions experienced by products installed in various aircraft locations are primarily determined by the external shock environment parameters and the modal response parameters of that aircraft location. However, analysis of extensive field data indicates that the modal response parameters of other aircraft components also impact the product. Therefore, the overall unit has proposed a test method that superimposes multiple damped sine waves. A typical superposition test condition involves superimposing three damped sine waves with different circular frequencies and acceleration peaks, meeting specific acceleration peak and phase requirements. The resulting composite waveform is no longer a standard damped sine wave, but rather a complex transient waveform with peak accelerations as high as 20g, as shown in Figure 17. Testing of suspended launch systems requires the installation of simulated missiles. If implemented using existing shock test systems, the impact displacement exceeds 1000mm and the impact velocity exceeds 5m / s, both exceeding the capabilities of existing equipment.

[0011] Summary of the Invention

[0012] In order to solve the deficiencies in the prior art, the present invention provides a catapult takeoff and arresting impact test device.

[0013] The present invention provides the following technical solutions:

[0014] A catapult takeoff and arresting impact test device includes a support frame, an auxiliary support guide device above the support frame, a mounting seat below the support frame, a servo actuator, an oil system, and a control and measurement system, wherein:

[0015] The support frame includes a column and a rectangular load-bearing platform at the top of the column, the servo actuator is installed on the load-bearing platform, and a central circular hole for the piston rod of the servo actuator to pass through is provided at the center of the load-bearing platform; the auxiliary support guide device includes a pair of parallel load-bearing beams, and a pair of first guide rods are vertically provided under each load-bearing beam; the mounting seat includes a mounting platform and second guide rods provided on the front, rear, left and right sides of the mounting platform, and the center of the mounting platform is connected to the front end of the piston rod of the servo actuator; an air spring is provided between the load-bearing beam and the load-bearing platform, and the second guide rods on the front and rear sides of the mounting platform pass through the load-bearing platform and are connected to the load-bearing beam;

[0016] The oil circuit system includes an oil source, a low-pressure accumulator group, a high-pressure accumulator group, an oil inlet valve block, an oil return valve block, a servo valve block, an oil source low-pressure return pipe, an oil source high-pressure outlet pipe, and necessary pipelines between the various components. The oil inlet valve block is connected to the oil outlet pipe of the high-pressure accumulator group and the oil inlet pipe of the servo valve block through pipelines, and the oil return valve block is connected to the oil inlet pipe of the low-pressure accumulator group and the oil outlet pipe of the servo valve block through pipelines.

[0017] The control and measurement system includes a vibration and shock loading host computer, a vibration and shock controller, a static loading host computer, a hydraulic servo controller, a servo valve and an acceleration sensor. The servo actuator has a built-in displacement sensor. The vibration and shock loading host computer is connected to the vibration and shock controller for transmitting instructions to the vibration and shock controller. The static loading host computer is connected to the hydraulic servo controller for transmitting instructions to the hydraulic servo controller. The hydraulic servo controller is connected to the servo valve for driving the servo valve to supply oil to the servo actuator. The vibration and shock controller is connected to the hydraulic servo controller for decomposing the vibration and shock conditions into action signals of the servo actuator, and then forming a closed-loop control by referring to the acceleration signal fed back by the acceleration sensor.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. This test device can be widely used for conventional vibration tests, classic shock tests, classic arresting shock tests and composite waveform arresting shock tests of various types of suspended launch devices, carrier-based aircraft and missiles.

[0020] 2. The test device can realize the inverted installation of the test piece, simulating the actual installation status of the suspended launch device and the missile; the bottom of the test installation platform can be connected to different types of suspended launch devices, which is highly practical; the test installation platform has large thrust, large maximum displacement, and high maximum speed, which is suitable for large test pieces and larger test volumes; there is a large space available under the installation platform, and it can be used as a simulated missile release test bench in conjunction with a buffer pad. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] FIG1 is a schematic diagram of the present invention;

[0022] FIG2 is a top view of the support stand of the present invention;

[0023] FIG3 is a schematic structural diagram of the auxiliary support guide device of the present invention;

[0024] FIG4 is a schematic structural diagram of the mounting base of the present invention;

[0025] FIG5 is a structural diagram of the mounting platform in the mounting base of the invention;

[0026] FIG6 is a second structural diagram of the mounting platform in the mounting base of the invention;

[0027] 7 is a structural diagram of the guide rod support in the mounting base of the present invention;

[0028] FIG8 is a second structural diagram of the guide rod support in the mounting base of the present invention;

[0029] 9 is a schematic diagram of the combined structure of the support stand and the auxiliary support guide device of the present invention;

[0030] 10 is a schematic diagram of the combined structure of the auxiliary support guide device and the mounting seat of the present invention;

[0031] Figure 11 is a schematic structural diagram of the adapter mounting block;

[0032] 12 is a schematic diagram of the combined structure of the support stand, mounting base, servo actuator and servo valve block of the present invention;

[0033] 13 is a side view of the combined structure of the support stand, auxiliary support guide device, mounting seat, air spring, simulated bomb, suspension launch device and adapter mounting block of the present invention;

[0034] 14 is a rear view of the combined structure of the support stand, auxiliary support guide device, mounting seat, air spring, simulated bomb, suspension launch device and adapter mounting block of the present invention;

[0035] FIG15 is a control principle diagram of the present invention;

[0036] FIG16 is a schematic diagram of the present invention in use;

[0037] Figure 17 is the composite shock waveform after the superposition of three sinusoidal damped waves.

[0038] Figure 18 is a comparison diagram before and after the compensation algorithm.

[0039] Among them, 1-support frame, 111-column, 112-load-bearing platform, 1121-center circular hole, 1122-spring mounting seat, 1123-first circular hole, 1124-second circular hole, 1125-platform square hole, 2-auxiliary support guide device, 211-load-bearing beam, 212-first guide rod, 3-mounting seat, 311-mounting platform, 3111-shell, 3112-mounting flange surface, 3113-reinforcement plate, 3114-mounting threaded hole, 312-second guide rod, 313-guide rod support, 4 -Servo actuator, 5-air spring, 6-oil source, 7-low-pressure accumulator group, 8-high-pressure accumulator group, 9-oil inlet valve block, 10-oil return valve block, 11-servo valve block, 12-oil source low-pressure return pipe, 13-oil source high-pressure outlet pipe, 14-vibration and shock loading host computer, 15-vibration and shock controller, 16-static loading host computer, 17-hydraulic servo controller, 18-servo valve, 19-acceleration sensor, 20-simulated bomb, 21-suspension launching device, 22-adapter mounting block, 23-delivery controller. DETAILED DESCRIPTION

[0040] The technical solution of the present invention is further described below with reference to the accompanying drawings and embodiments.

[0041] As shown in Figures 1 to 18, a catapult takeoff and arresting impact test device includes a support rig 1, an auxiliary support guide device 2 above the support rig 1, a mounting base 3 below the support rig 1, a servo actuator 4, an oil system, and a control and measurement system, wherein:

[0042] The support stand 1 includes a column 111 and a rectangular load-bearing platform 112 at the top of the column 111, the servo actuator 4 is installed on the load-bearing platform 112, and a central circular hole 1121 is provided at the center of the load-bearing platform 112 for the piston rod of the servo actuator 4 to pass through; the auxiliary support guide device 2 includes a pair of parallel load-bearing beams 211, and a pair of first guide rods 212 are vertically provided below each load-bearing beam 211; the mounting seat 3 includes a mounting platform 311 and second guide rods 312 provided on the front, rear, left and right sides of the mounting platform 311, and the center of the mounting platform 311 is connected to the front end of the piston rod of the servo actuator 4; an air spring 5 is provided between the load-bearing beam 211 and the load-bearing platform 112, and the second guide rods 312 on the front and rear sides of the mounting platform 311 pass through the load-bearing platform 112 and are connected to the load-bearing beam 211;

[0043] The oil circuit system includes an oil source 6, a low-pressure accumulator group 7, a high-pressure accumulator group 8, an oil inlet valve block 9, an oil return valve block 10, a servo valve block 11, an oil source low-pressure oil return pipe 12, an oil source high-pressure oil outlet pipe 13, and necessary pipelines between the various components. The oil inlet valve block 9 is connected to the oil outlet pipe of the high-pressure accumulator group 8 and the oil inlet pipe of the servo valve block 11 through pipelines, and the oil return valve block 10 is connected to the oil inlet pipe of the low-pressure accumulator group 7 and the oil outlet pipe of the servo valve block 11 through pipelines.

[0044] The control and measurement system includes a vibration and impact loading host computer 14, a vibration and impact controller 15, a static loading host computer 16, a hydraulic servo controller 17, a servo valve 18 and an acceleration sensor 19. The servo actuator 4 has a built-in displacement sensor. The vibration and impact loading host computer 14 is connected to the vibration and impact controller 15 for transmitting instructions to the vibration and impact controller 15. The static loading host computer 16 is connected to the hydraulic servo controller 17 for transmitting instructions to the hydraulic servo controller 17. The hydraulic servo controller 17 is connected to the servo valve 18 for driving the servo valve 18 to supply oil to the servo actuator 4. The vibration and impact controller 15 is connected to the hydraulic servo controller 17 for decomposing the vibration and impact conditions into action signals of the servo actuator 4, and then forming a closed-loop control by referring to the acceleration signal fed back by the acceleration sensor 19.

[0045] The ejection takeoff and arresting impact test device has a spring mounting seat 1122 on its load-bearing platform 112, and the load-bearing platform 112 is also provided with a first circular hole 1123 for the first guide rod 212 to pass through and a second circular hole 1124 for the second guide rod 312 to pass through.

[0046] The ejection takeoff and arresting impact test device has a mounting platform 311 with guide rod supports 313 provided around it for the second guide rod 312 to pass through.

[0047] The installation platform 311 of the catapult takeoff and arresting impact test device is a rectangular shell 3111 with a base plate. A hollow column is provided at the center of the shell 3111, and a mounting flange surface 3112 is formed at the upper end of the hollow column. The mounting flange surface 3112 is connected to the front end of the piston rod of the servo actuator 4. Reinforcement plates 3113 are evenly distributed radially on the periphery of the hollow column, and mounting threaded holes 3114 are provided on the base plate of the shell 3111.

[0048] The ejection takeoff and arresting impact test device comprises a pair of low-pressure accumulator group 7 and high-pressure accumulator group 8, and an oil inlet valve block 9 and an oil return valve block 10, which are symmetrically arranged on both sides of the support frame 1.

[0049] In the ejection takeoff and arresting impact test device, servo valve blocks 11 are symmetrically provided on both sides of the servo actuator 4 , and the servo valve 18 is installed on the servo valve block 11 .

[0050] The acceleration sensor 19 of the ejection takeoff and arresting impact test device is installed on the lower surface of the installation platform 311.

[0051] The first guide rod 212 is a cylindrical structure, and the second guide rod 312 is a cylindrical structure with a stopper at one end. The upper ends of the first guide rod 212 and the second guide rods 312 on the front and rear sides of the mounting platform 311 are screwed to the lower end of the load-bearing beam 211, and the lower ends of the first guide rod 212 are free. The first guide rod 212 and the second guide rods 312 around the mounting platform 311 respectively pass through the first circular hole 1123 and the second circular hole 1124 of the support frame 1 and can slide up and down.

[0052] A spring mounting seat is also provided at the lower end of the load-bearing beam 211 in the auxiliary support guide device 2 , which is used to install the air spring 5 between the support stand 1 and the auxiliary support guide device 2 .

[0053] The auxiliary support guide device 2 serves to improve the stability and load-bearing capacity of the installation platform 311, that is, to enhance the support stiffness of the installation platform 311 in the non-movement direction and the static load-bearing capacity in the movement direction.

[0054] The first guide rod 212 in the auxiliary support guide device 2 plays a guiding role, and the air spring 5 plays an auxiliary supporting role. The air pressure in the air spring 5 is adjustable and can be adjusted according to the weight of the test piece during use to ensure that the mounting platform 311 is at an appropriate height.

[0055] When the air spring 5 is inflated, it pushes the auxiliary load-bearing beam 211 upward, which in turn drives the mounting platform 311 upward via the second guide rod 312. When the air spring 5 is deflated, the mounting platform 311 moves downward under the action of gravity. Therefore, the position of the mounting platform 311 can be adjusted by adjusting the inflation level of the air spring 5, thereby balancing the weight of the mounting platform 311 and the test specimen mounted on it.

[0056] The support frame 1 is the main support structure, on which the servo actuator 4, servo valve 18, auxiliary support guide device 2, oil circuit and valve block are mounted, and the mounting platform 311 is mounted below. The support frame 1 provides mounting locations for multiple major components and also provides sufficient support rigidity and strength for the entire test system.

[0057] The support frame 1 is a steel plate welded structure, and the main structure is four variable-section columns 111 supporting a cross-section bearing platform 112. The variable-section columns 111 are small at the top and large at the bottom. The top is connected to the four corners of the cross-section bearing platform 112 by bolts, and the bottom is connected to the static foundation by bolts, which plays a stabilizing role. A central circular hole 1121 is designed in the center of the cross-section bearing platform 112, for the piston rod of the servo actuator 4 to pass through and connect to the mounting platform 311 below the cross-section bearing platform 112. The four platform square holes 1125 of the cross-section bearing platform 112 can be used for the slings to pass through when lifting heavy objects from below. When the center of the cross-section bearing platform 112 bears a vertical force of 500kN, the deformation is no more than 2mm. The field-shaped load-bearing platform 112 is designed with mounting surfaces with threaded holes around it, which can be used to install the oil inlet valve block, oil return valve block, pipe clamps, etc. The effective usable space below the field-shaped load-bearing platform 112 is 1600mm×1600mm×2400mm.

[0058] The mounting platform 311 is a monolithic, cast rectangular parallelepiped structure. A circular mounting flange 3112 at its center is designed to connect to the front end of the piston rod of the servo actuator 4. The lower surface of the mounting platform 311 is designed with an array of threaded mounting holes 3114 to facilitate installation of suspension launchers with various interface types. The mounting platform 311 also has threaded mounting holes on its front, back, left, and right sides, each of which is bolted to a guide rod support 313. The guide rod support 313 is not fixed to the second guide rod 312; the second guide rod 312 can slide up and down within the guide rod support 313, ensuring stable vertical movement of the mounting platform 311 and providing a certain load-bearing capacity. After the second guide rod 312 is installed on the mounting platform 311, it cooperates with the first guide rod 212 and air spring 5 mounted on the auxiliary support guide device 2. The first guide rods 212 on the left and right sides of the mounting platform 311 provide vertical guidance, while the first guide rods 212 on the front and back sides of the mounting platform 311 and the air spring 5 connected via the load-bearing beam 211 also provide load-bearing and platform position adjustment.

[0059] The mounting platform 311 is a universal mounting platform for test pieces, designed for inverted installation, with a mounting surface measuring 600mm x 1600mm. The base of the mounting platform 311 is the mounting surface, designed with an array of threaded holes 3114. Suspended launchers 21 of varying sizes can be mounted on the mounting platform 311 using adapter mounting blocks 22 and bolts. There is ample space beneath the test piece for a cushion, allowing for immediate verification of the test piece's launch functionality after the impact test.

[0060] The servo actuator 4 plays a role in generating impact action.

[0061] The servo actuator 4 is a front-end mounting structure with a static pressure support seal. During installation, it is inverted at the center of the upper surface of the support frame 1 and connected to the support frame 1 using a flange surface. There is a threaded hole at the front end of the piston rod of the servo actuator 4, which can be connected to the mounting platform 311 by bolts. In addition, the T-shaped load-bearing platform 112 of the support frame 1 is a vertically symmetrical structure. When the test piece does not need to be suspended for installation, the servo actuator 4 can also be installed on the lower surface of the T-shaped load-bearing platform 112 (the T-shaped load-bearing platform 112 is symmetrical up and down, and the lower surface also has a mounting interface), so that the mounting surface of the mounting platform 311 is upward.

[0062] The oil circuit system, in which the function of the oil inlet valve block 9 is to connect the oil outlet pipeline of the high-pressure accumulator group 8 and the oil inlet pipeline (P port) of the servo valve block 11; the function of the oil return valve block 10 is to connect the oil inlet pipeline of the low-pressure accumulator group 7 and the oil outlet pipeline (T port) of the servo valve block 11; the servo valve block 11 is an adapter block for installing multiple servo valves 18 in parallel on the servo actuator 4.

[0063] The system's hydraulic oil path is: high-pressure oil pump from oil source 6 - high-pressure oil outlet pipe 13 from oil source - high-pressure accumulator assembly 8 - oil inlet valve block 9 - port P of servo valve block 11 - servo valve 18 - servo actuator 4 - port T of servo valve block 11 - return valve block 10 - low-pressure accumulator assembly 7 - low-pressure oil return pipe 12 from oil source 6 - oil tank from oil source 6. The oil circuit connects the oil source 6, high-pressure accumulator assembly 8, low-pressure accumulator assembly 7, servo valve 18, and servo actuator 4 into a hydraulic oil circuit, supplying energy to the servo actuator 4. This energy is then transferred to the suspended object through mounting base 3, enabling vibration or impact testing of the suspended object.

[0064] The single-side servo valve block 11 and its upstream and downstream oil inlet and return valve blocks 9 and 10 are all rated for a flow rate of 2000 L / min. Four 2-inch high-pressure oil pipes connect the servo valve block 11 to the oil inlet valve block 9, while four 2.5-inch high-pressure oil pipes connect the servo valve block 11 to the oil return valve block 10. The oil inlet valve block 9 is connected to the high-pressure accumulator group 8 via 100 mm diameter rigid pipes, while the oil return valve block 10 is connected to the low-pressure accumulator group 7 via 100 mm diameter rigid pipes. A bypass oil line is provided between the oil inlet and return valve blocks 9 and 10 to facilitate cleaning of the oil lines and valve block systems.

[0065] The oil source 6 is a high-pressure oil source with a rated working pressure of 28 MPa, a maximum working pressure of 31.5 MPa, and a flow rate of 400 L / min. The oil source includes a high-pressure pump unit, an oil tank, etc.

[0066] The high-pressure accumulator groups 8 are arranged symmetrically in two groups, which serve to provide a large flow of high-pressure hydraulic oil to the servo actuator 4. The capacity is 900L, the rated operating pressure is 31.5MPa, and it can output an instantaneous flow of 2000L / min and last for not less than 2s.

[0067] The low-pressure accumulator group 7 is symmetrically arranged in two groups, which plays the role of recovering the hydraulic oil flowing out of the servo actuator 4. It has a capacity of 500L and a rated operating pressure of 10MPa. It can absorb an instantaneous flow of 2000L / min and last for not less than 2s.

[0068] The control and measurement system includes a vibration and shock loading host computer 14 with a vibration and shock control application. Users enter vibration or shock test conditions on this host computer, which then converts them into command signals and transmits them to the vibration and shock controller 15. The static loading host computer 16 includes a hydraulic servo system control application. Users enter basic control parameters and safety strategies for the hydraulic servo system on this host computer, which then converts them into command signals and transmits them to the hydraulic servo controller 17.

[0069] The vibration and shock controller 15 in the control and measurement system can composite multiple damped sine waves (duration 2s) of different frequencies and acceleration peaks as target curve input, and then output corresponding control signals to the hydraulic servo controller 17. The hydraulic servo controller 17 controls the servo valve 18 to change the flow and direction of the hydraulic oil flowing through the servo actuator 4. The piston rod of the servo actuator 4 drives the mounting platform 311 to produce corresponding movements. The acceleration sensor 19 installed on the mounting platform 311 measures the acceleration signal and transmits it to the vibration and shock controller 15. The vibration and shock controller 15 then compares the signal from the acceleration sensor 19 with the target value and corrects the output control signal, thereby performing closed-loop control. The control and measurement system can control the servo actuator 4 to achieve the target vibration or shock spectrum on the mounting platform 311 through this closed-loop control method.

[0070] The control and measurement system's control logic follows the following sequence: vibration and shock controller 15 - hydraulic servo controller 17 - servo valve 18 - servo actuator 4 - mounting platform 311. Mounting platform 311 is equipped with an acceleration sensor 19, which collects acceleration signals and feeds them back to the vibration and shock controller 15 for closed-loop control. The vibration and shock controller 15 provides input and control functions for general vibration and shock conditions. It also incorporates a composite arresting shock function, enabling the superposition of multiple different sinusoidal damped wave conditions and the reproduction of transient shocks from measured shock data. Utilizing this control system, the arresting shock test apparatus of the present invention can perform conventional vibration tests, classical shock tests, classical arresting shock tests, and arresting shock tests using composite waveforms.

[0071] The servo actuator 4 has a built-in LVDT displacement sensor. The servo actuator 4 has a maximum static thrust of 500kN, a maximum dynamic thrust of 400kN, an effective stroke of 450mm, a maximum speed of 4m / s, a working pressure of 28MPa, and a design flow rate of 4300L / min.

[0072] The vibration and shock controller 15 in the control and measurement system has a built-in bias waveform optimization compensation algorithm. As shown in Formula 1-1, with the zero point of the acceleration waveform under the formal test conditions as the origin, within the effective test pulse width [0, Te], the acceleration waveform is a damped sine wave; a compensation signal with a duration of [-Δt, 0] is added before the effective pulse width. The direction of this signal is negative, opposite to the direction of the initial damped sine wave waveform. After adding this compensation, the displacement signal obtained by integrating the acceleration waveform changes from the original single-sided waveform to a double-sided waveform, and the peak value is significantly reduced, as shown in Figure 18. Without changing the target acceleration signal, this algorithm can achieve zero-point balance for the velocity and displacement terms of various types of transient waveforms, significantly reducing the displacement and velocity peak of the servo actuator, alleviating the load on the servo actuator, and has the advantages of small shock spectrum distortion and small displacement after compensation.

[0073] During the test, the simulated missile 20 can be installed on the suspended launching device 21. The suspended launching device 21 is fixed on the lower surface of the mounting platform 311 through the cooperation of the adapter mounting block 22 and the mounting threaded holes 3114 on the mounting platform 311. The mounting platform 311 has multiple sets of table mounting threaded holes 3114, which can be connected to suspended launching devices of different sizes. It is highly practical and its installation method is hanging installation, which can realize simulated delivery assessment immediately after the vibration or impact test is completed.

[0074] The suspended launcher 21 in this embodiment has a three-stage structure and is equipped with a release controller 23, which can be remotely operated to release the simulated projectile 20. The simulated projectile 20 is suspended from the suspended launcher 21 via a hook. The suspended launcher 21 is connected to the lower end surface of the mounting platform 311 via an adapter mounting block 22 and connecting bolts. At the moment of release, the suspended launcher 21 applies a downward thrust to the simulated projectile 20 while simultaneously experiencing an upward reaction force.

[0075] Multiple adapter mounting blocks 22 can be designed. The upper end of each adapter mounting block 22 has threaded holes that mate with the threaded mounting holes 3114 of the mounting platform 311. The lower end of the adapter mounting block 22 can be quickly and easily connected to different types of suspension launchers 21 via bolts. The connection between the suspension launcher 21 and the dummy projectile 20 is consistent with the actual installation on the aircraft. Changing the position of the adapter mounting block 22 on the mounting platform 311 adjusts the center of gravity of the suspension system. Once properly positioned, the adapter mounting block 22 can be locked to the mounting platform 311 via the bolt holes on its upper portion. It is important to note that during installation, the center of gravity of the combined suspension system, comprising the dummy projectile 20, suspension launcher 21, and adapter mounting block 22, must be positioned within the downward projection of the mounting platform 311 and as close to the center of the mounting platform 311 as possible. This ensures greater stability during impacts, as the mounting platform and suspension components form a single unit.

[0076] The specific steps of the test are as follows:

[0077] 1. Open the oil source 6 and the oil system valve, adjust the oil pressure to the pressure value required for the test, supply pressure to the high-pressure accumulator group 8 and the servo valve 18, and wait until the high-pressure accumulator group 8 is charged and stabilized.

[0078] 2. Turn on the inflation switch of the air spring 5 and adjust the pressure in the airbag so that the mounting platform 311 is in a balanced position, that is, halfway through the stroke of the piston rod of the servo actuator 4.

[0079] 3. According to the number of installation points of the suspended launch device, select a corresponding number of adapter mounting blocks 22 and pre-install them at appropriate positions on the installation platform 311.

[0080] 4. Select appropriate dummy parts or counterweights and install them on the mounting platform 311 for pre-test and debugging. Adjust the pressure in the air spring 5 again to make the mounting platform 311 in a balanced position.

[0081] 5. Start the vibration and shock controller 15 and the hydraulic servo controller 17, install the acceleration sensor 19 on the mounting platform 311 and connect it to the vibration and shock controller 15, test the sensor signal to ensure that the connection and signal are normal.

[0082] 6. Set a small-scale sinusoidal frequency sweep test condition in the vibration shock controller 15, start the test system, test whether the servo control system works normally, observe whether the installation platform operates normally, and observe whether the test curve is normal.

[0083] 7. Input the target test conditions into the vibration and shock controller 15, such as three different sinusoidal damped waves, and perform waveform superposition and preprocessing in the controller. Perform pre-test debugging. During debugging, the test level can be increased step by step, such as from -6dB, -3dB, to the full level.

[0084] 8. Remove the dummy parts and counterweights, install the test dummy projectile 20 on the suspension launching device 21, and fix the suspension launching device 21 to the adapter mounting block 22 on the mounting platform 311 with bolts. Adjust the position of the adapter mounting block 22 on the mounting platform 311 according to the overall center of gravity of the suspension composed of the dummy projectile 20 and the suspension launching device 21, so that the overall center of gravity of the suspension is near the center point of the mounting platform 311, and then lock the adapter mounting block 22.

[0085] 9. Adjust the pressure in the air spring 5 again to keep the mounting platform 311 in a balanced position.

[0086] 10. Enter the target test conditions for formal testing. The test level can be increased step by step, such as from -6dB, -3dB to the full level.

[0087] 11. Complete the formal test and save the required test data.

[0088] 12. After the test is completed, you can choose whether to conduct a simulation operation as needed.

[0089] 13. Disassemble the test piece and shut down the test system.

[0090] In this way, the arresting impact test assessment of the simulated missile and the suspended launch device under the composite waveform is realized, and the delivery function assessment can be carried out immediately after the test.

[0091] The present invention discloses a catapult takeoff and arresting shock test device. The device designs a new arresting shock test system construction form, uses a customized large-tonnage, large-stroke, and high-speed servo actuator as an impact generating device; uses a 28MPa high-pressure oil source and an accumulator that can provide a large flow of 2000L / min as a power device; and uses a vibration shock controller, a hydraulic servo controller, and an acceleration sensor to form a control system, thereby realizing arresting shock test assessment under a composite waveform of a missile and a suspended launch device.

[0092] The present invention can be widely used in conventional vibration and impact tests of various types of suspended launch devices in the suspended and installed state, arresting impact tests under composite waveforms, and delivery function assessments. It can also be expanded to other test pieces that require suspended installation, as well as other conventional vibration and impact tests. It has large thrust, large displacement, and high speed capabilities that conventional vibration tables and impact tables do not have.

[0093] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. The above is only a preferred implementation method of the present invention. It should be pointed out that due to the limitations of textual expression, there are objectively infinite specific structures. For ordinary technicians in this technical field, without departing from the principles of the present invention, they can make several improvements, modifications or changes, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the scope of protection of the present invention.

Claims

1. A catapult takeoff and arresting impact test device, characterized in that: The invention comprises a support frame (1), an auxiliary support guide device (2) above the support frame (1), a mounting seat (3) below the support frame (1), a servo actuator (4), an oil circuit system and a control and measurement system, wherein: The support frame (1) comprises a column (111) and a rectangular load-bearing platform (112) at the top of the column (111); the servo actuator (4) is mounted on the load-bearing platform (112); a central circular hole (1121) is provided at the center of the load-bearing platform (112) for the piston rod of the servo actuator (4) to pass through; the auxiliary support guide device (2) comprises a pair of parallel load-bearing beams (211), and a pair of first guide rods (212) are vertically provided below each load-bearing beam (211); the auxiliary support guide device (2) comprises a pair of parallel load-bearing beams (211), and a pair of first guide rods (212) are vertically provided below each load-bearing beam (211); The mounting seat (3) comprises a mounting platform (311) and second guide rods (312) arranged on the front side, rear side, left side and right side of the mounting platform (311); the central part of the mounting platform (311) is connected to the front end of the piston rod of the servo actuator (4); an air spring (5) is arranged between the load-bearing beam (211) and the load-bearing platform (112); the second guide rods (312) on the front side and rear side of the mounting platform (311) pass through the load-bearing platform (112) and are connected to the load-bearing beam (211); The oil circuit system comprises an oil source (6), a low-pressure accumulator group (7), a high-pressure accumulator group (8), an oil inlet valve block (9), an oil return valve block (10), a servo valve block (11), an oil source low-pressure oil return pipe (12), an oil source high-pressure oil outlet pipe (13) and necessary pipelines between the components; the oil inlet valve block (9) is connected to the oil outlet pipeline of the high-pressure accumulator group (8) and the oil inlet pipeline of the servo valve block (11) through pipelines, and the oil return valve block (10) is connected to the oil inlet pipeline of the low-pressure accumulator group (7) and the oil outlet pipeline of the servo valve block (11) through pipelines; The control and measurement system comprises a vibration and impact loading host computer (14), a vibration and impact controller (15), a static loading host computer (16), a hydraulic servo controller (17), a servo valve (18) and an acceleration sensor (19). The servo actuator (4) has a built-in displacement sensor. The vibration and impact loading host computer (14) is connected to the vibration and impact controller (15) for transmitting instructions to the vibration and impact controller (15). The static loading host computer (16) is connected to the hydraulic servo controller (17) for transmitting instructions to the hydraulic servo controller (17). The hydraulic servo controller (17) is connected to the servo valve (18) for driving the servo valve (18) to supply oil to the servo actuator (4). The vibration and impact controller (15) is connected to the hydraulic servo controller (17) for decomposing and converting vibration and impact conditions into action signals of the servo actuator (4), and then forming a closed-loop control by referring to the acceleration signal fed back by the acceleration sensor (19).

2. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: The load-bearing platform (112) is provided with a spring mounting seat (1122), and the load-bearing platform (112) is also provided with a first circular hole (1123) for the first guide rod (212) to pass through and a second circular hole (1124) for the second guide rod (312) to pass through.

3. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: The installation platform (311) is surrounded by guide rod supports (313) through which the second guide rod (312) passes.

4. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: The mounting platform (311) is a rectangular shell (3111) with a bottom plate. A hollow column is provided at the center of the shell (3111). A mounting flange surface (3112) is formed at the upper end of the hollow column. The mounting flange surface (3112) is connected to the front end of the piston rod of the servo actuator (4). Reinforcement plates (3113) are evenly distributed radially around the periphery of the hollow column. A mounting threaded hole (3114) is provided on the bottom plate of the shell (3111).

5. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: The low-pressure accumulator group (7) and the high-pressure accumulator group (8), the oil inlet valve block (9) and the oil return valve block (10) are all a pair and are symmetrically arranged on both sides of the support frame (1).

6. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: Servo valve blocks (11) are symmetrically provided on both sides of the servo actuator (4), and the servo valve (18) is installed on the servo valve block (11).

7. The ejection takeoff and arresting impact test device according to claim 1, characterized in that: The acceleration sensor (19) is mounted on the lower surface of the mounting platform (311).

Images