Test device for multi-posture, multi-angle, high-energy impact of carrier-based aircraft on ship deck

Abstract

The present invention discloses a test device for a multi-posture, multi-angle, high-energy impact of a carrier-based aircraft on a ship deck, comprising an impact assembly and a measurement assembly. The impact assembly comprises a supporting steel frame, the bottom end of which is provided with a plurality of bottom pulleys, the top end of which is arc-shaped, the top end of which is fixedly connected to a guide portion, the guide portion being matched with the top end of the supporting steel frame, the top end of which is provided with an energy-boosting portion, an impact portion being slidably provided on the guide portion, the impact portion being magnetically connected to the bottom end of the energy-boosting portion, the bottom end of the guide portion being located above the measurement assembly; the measurement assembly being located on the sliding-out side of the impact portion; the measurement assembly comprising a fixing portion, the top end of which is inclined toward the guide portion, the top end of which is fixedly connected to a measuring portion, and a recording device being located above the end of the measuring portion away from the guide portion. The test device of the present invention has a clear design principle, simple equipment layout, flexible load control, and diverse application scenarios, and is convenient for simulating the test of a multi-posture, multi-angle, high-energy impact of a carrier-based aircraft on a ship deck.

Description

Technical Field

[0001] The present invention belongs to the technical field of engineering experimental equipment, and in particular relates to a multi-posture, multi-angle, high-energy impact test device for carrier-based aircraft on a ship deck. Background Art

[0002] The decks of large surface ships support the takeoff and landing of carrier-based aircraft at sea, becoming crucial for developing maritime defense capabilities. While my country's large surface ships in service possess the basic capabilities for aircraft takeoff and landing, ship deck design faces challenges in accurately inputting aircraft impact loads, leading to highly conservative ship deck design specifications. The true safety level of deck structures under aircraft landing impacts is unclear, leading to strict restrictions on the applicable environmental requirements for aircraft takeoff and landing at sea, reducing aircraft takeoff and landing flexibility. Model testing methods enable direct measurement of impact loads on ship deck structures, which is of great significance to ship structural design and aircraft landing safety.

[0003] The principle of the impact test is to simulate the landing impact posture, structural form and load conditions of the carrier-based aircraft, design an equivalent simplified test model of the carrier-based aircraft and the ship, lift the landing gear and counterweight combination to a predetermined height, release it, and let it fall freely, reach a certain impact speed and impact angle at the moment of contact with the deck test model, convert gravitational potential energy into kinetic energy, and exert an impact on the deck test model.

[0004] However, the existing impact test of carrier-based aircraft has the following problems: (1) The impact of carrier-based aircraft landing on the ship deck involves different disciplines such as ship engineering, aviation engineering, and physical experiments. Currently, there is a lack of impact test equipment that considers the comprehensive impact of various disciplines; (2) For the drop shock test equipment, only the single-angle impact in the vertical direction is considered, ignoring the impact posture and angle changes caused by the movement of the carrier-based aircraft and the ship at sea; (3) For the ship structure impact test equipment, dynamic load exciters such as hammers are usually used, ignoring the nonlinear mechanics and complex contact effects of aviation structures; (4) The impact working conditions of carrier-based aircraft landing are relatively special, involving coupling effects such as rigid body motion, dynamic deformation of elastic bodies, superelastic body contact, and instantaneous impact. The existing test equipment cannot reflect the joint effects of these factors. Therefore, it is necessary to design a carrier-based aircraft multi-posture, multi-angle, and high-energy impact test equipment for ship decks to solve the above problems. Summary of the Invention

[0005] The purpose of the present invention is to provide a multi-posture, multi-angle, high-energy impact ship deck test device for carrier-based aircraft to solve the above-mentioned problems and achieve the purpose of supporting ship structure design and carrier-based aircraft landing safety data.

[0006] To achieve the above-mentioned object, the present invention provides the following solutions: a carrier-based aircraft multi-posture, multi-angle, high-energy impact ship deck test device, comprising an impact component and a measurement component;

[0007] The impact assembly includes a supporting steel frame, a plurality of bottom pulleys are provided at the bottom end of the supporting steel frame, the top end of the supporting steel frame is arc-shaped, a guide portion is fixedly connected to the top end of the supporting steel frame, the guide portion matches the top end of the supporting steel frame, an energy-enhancing portion is provided at the top end of the guide portion, an impact portion is slidably provided on the guide portion, the impact portion is magnetically connected to the bottom end of the energy-enhancing portion, the bottom end of the guide portion is located above the measuring assembly; the measuring assembly is located on the sliding-out side of the impact portion;

[0008] The measuring component includes a fixing portion, the top of which is tilted toward the guide portion, the top of which is fixedly connected to the measuring portion, and a recording device is provided above one end of the measuring portion away from the guide portion.

[0009] Preferably, the impact part includes a landing gear, the landing gear is slidably connected to the guide part, the top end of the landing gear is detachably connected to a counterweight, and the counterweight is magnetically connected to the bottom end of the energizing part.

[0010] Preferably, the energy-boosting part includes a hook, the bottom end of the hook is fixedly connected to an electromagnet, the electromagnet is magnetically connected to the counterweight, the top end of the supporting steel frame is fixedly connected to an energy storage spring, and the bottom end of the energy storage spring abuts against the top end of the landing gear.

[0011] Preferably, the guide part includes two fixed rails arranged in parallel, the fixed rails are fixedly connected to the top of the supporting steel frame through a strut, the landing gear is slidably arranged between the two fixed rails, the top of the energy storage spring is fixedly connected to the top of the fixed rails, the bottom end of the fixed rail is detachably connected to a detachable slide rail, and the lower end of the detachable slide rail is located above the measuring part.

[0012] Preferably, the fixing portion includes a pad, the top of the pad is fixedly connected to a wedge, the top of the wedge is an inclined surface, the lower end of the wedge is arranged close to the fixed rail, and the measuring portion is fixedly connected to the top of the wedge.

[0013] Preferably, the measuring part includes a deck model, the bottom end of the deck model is fixedly connected to the top end of the wedge-shaped body, an acceleration sensor and several strain gauges are arranged inside the deck model, and a thin film pressure sensor is fixedly connected to the middle part of the top end of the deck model.

[0014] Preferably, a load sensor is provided on the landing gear, a rolling bearing is sleeved on the outer side wall of the fixed track, and the outer ring of the rolling bearing is fixedly connected to the landing gear.

[0015] Preferably, the recording device comprises a camera.

[0016] The present invention has the following technical effects:

[0017] The impact assembly of the present invention can reduce the difficulty of simulating complex models of carrier-based aircraft; by setting the top of the supporting steel frame to an arc shape and setting the shape of the guide part to match the top of the supporting steel frame, impacts of different speeds can be achieved; the provided energy-boosting part can achieve greater impact energy; the impact point position can be adjusted through the bottom pulley at the bottom of the supporting steel frame, making it convenient to impact different positions of the measurement assembly.

[0018] This test device has clear design principles, simple equipment layout, flexible load control, and diverse application scenarios, making it convenient for carrier-based aircraft to simulate high-energy impacts on ship decks in multiple postures and angles. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. 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 any creative work.

[0020] Figure 1 It is a front view of the present invention;

[0021] Figure 2 It is a side view of the present invention;

[0022] Figure 3 This is a cross-sectional view of the connection between the fixed rail and the rolling bearing of the present invention;

[0023] Figure 4 This is a schematic diagram of the main landing gear of the present invention;

[0024] Figure 5 This is a schematic diagram of the front landing gear of the present invention;

[0025] Figure 6 This is a schematic diagram of the main landing gear and nose landing gear combination of the present invention;

[0026] Figure 7 It is a three-dimensional stereogram of the present invention.

[0027] Among them, 1. Counterweight; 2. Landing gear; 3. Fixed track; 4. Strut; 5. Thin film pressure sensor; 6. Deck model; 7. Wedge; 8. Pad; 9. Bottom pulley; 10. Support steel frame; 11. Strain gauge; 12. Acceleration sensor; 13. Load sensor; 14. Rolling bearing; 15. Removable slide rail; 16. Electromagnet; 17. Hook; 18. Energy storage spring; 19. Camera. DETAILED DESCRIPTION

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts are within the scope of protection of the present invention.

[0029] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0030] Reference Figure 1-7 The present invention discloses a test device for a carrier-based aircraft to impact a ship deck with multiple postures, multiple angles, and large energy, including an impact component and a measurement component;

[0031] The impact assembly includes a supporting steel frame 10, a plurality of bottom pulleys 9 are provided at the bottom end of the supporting steel frame 10, the top end of the supporting steel frame 10 is arc-shaped, a guide portion is fixedly connected to the top end of the supporting steel frame 10, the guide portion matches the top end of the supporting steel frame 10, an energy-enhancing portion is provided at the top end of the guide portion, an impact portion is slidably provided on the guide portion, the impact portion is magnetically connected to the bottom end of the energy-enhancing portion, and the bottom end of the guide portion is located above the measuring assembly; the measuring assembly is located on the sliding-out side of the impact portion;

[0032] The measuring component includes a fixing part, the top of which is tilted toward the guide part, the top of which is fixedly connected to the measuring part, and a recording device is arranged above one end of the measuring part away from the guide part.

[0033] According to a further optimized solution, the impact part includes a landing gear 2, which is slidingly connected to the guide part. A counterweight 1 is detachably connected to the top of the landing gear 2, and the counterweight 1 is magnetically connected to the bottom end of the energizer part.

[0034] Furthermore, the landing gear 2 includes a main landing gear and a front landing gear.

[0035] The Landing Gear 2 test model focused on simulating tire nonlinear elasticity, landing gear stiffness, and damping. Based on the landing method of Landing Gear 2, models for the main landing gear, nose landing gear, and main and nose landing gear were designed. Compression testing was conducted to verify the consistency of the load-displacement curve of Landing Gear 2 between the model and the actual situation. Counterweight 1 was used to adjust the weight and center of gravity of the Landing Gear 2 test model to approximate the weight distribution of the carrier-based aircraft.

[0036] The landing gear 2 (including counterweight 1)-tire-deck model 6 satisfies the conversion relationships of force similarity, mass similarity, displacement similarity, etc. with the actual physical model. The nonlinear finite element method is used to verify the similarity between the test model and the actual situation, ensuring the consistency of the impact load characteristics and structural response.

[0037] Counterweight 1 simulates the aircraft itself and its attached weight, facilitating weight and center of gravity position adjustment. Landing gear 2 simulates the aircraft's landing gear stiffness and tires. The tires are made of rubber to simulate large elastic deformation during impact. Bottom pulley 9 facilitates changing the position of support steel frame 10 and has the function of locking it in a predetermined position. Support steel frame 10 is welded and processed from steel structure, providing high stiffness to prevent localized excessive deformation during normal testing. The combined model of counterweight 1 and landing gear 2 focuses on the similarity of impact loads, achieving a simplified simulation of the mechanical similarity of a complex aircraft from the perspective of weight, center of gravity, and tire contact control.

[0038] To further optimize the solution, the energy-enhancing part includes a hook 17, the bottom end of the hook 17 is fixedly connected to an electromagnet 16, the electromagnet 16 is magnetically connected to the counterweight 1, and the top end of the supporting steel frame 10 is fixedly connected to an energy storage spring 18, and the bottom end of the energy storage spring 18 abuts against the top end of the landing gear 2.

[0039] The energy storage spring 18 can store a large amount of elastic potential energy when it is compressed by the counterweight 1 . When the electromagnet 16 is disconnected, the elastic potential energy of the energy storage spring 18 is converted into downward sliding energy of the landing gear 2 .

[0040] The impact energy of a carrier-based aircraft landing is simulated by combining the counterweight 1, the supporting steel frame 10, and the energy storage spring 18. The maximum mass of the counterweight 1 can be configured according to the lifting capacity of the hook 17, and the maximum drop height can be designed according to the effective clearance height of the laboratory.

[0041] The hook 17 is connected to the lifting equipment of the laboratory (not shown in the figure), one end of the energy storage spring 18 is connected to the supporting steel frame 10, and the other end acts on the landing gear 2. The energy storage spring 18 is stretched by the hook 17 to increase the initial energy of the landing gear 2 sliding down along the fixed track 3.

[0042] To further optimize the solution, the guide part includes two fixed rails 3 arranged in parallel, the fixed rails 3 are fixedly connected to the top of the supporting steel frame 10 through the strut 4, the landing gear 2 is slidably set between the two fixed rails 3, the top of the energy storage spring 18 is fixedly connected to the top of the fixed rail 3, and the bottom end of the fixed rail 3 is detachably connected to a detachable slide rail 15, and the lower end of the detachable slide rail 15 is located above the measuring part.

[0043] The shape of the fixed rail 3 matches the arc shape of the top of the supporting steel frame 10, and has a curved angle to facilitate the free sliding of the landing gear 2. The fixed rail 3 has a certain load-bearing capacity and does not undergo large deformation when supporting the counterweight 1. The number of detachable slide rails 15 is at least one section. By adding different numbers of detachable slide rails 15, the angle of the landing gear 2 at the moment of falling can be changed.

[0044] A further optimized solution is that the fixed part includes a pad 8, the top of the pad 8 is fixedly connected to a wedge 7, the top of the wedge 7 is an inclined surface, the lower end of the wedge 7 is arranged close to the fixed rail 3, and the measuring part is fixedly connected to the top of the wedge 7.

[0045] The fixed track 3, the wedge-shaped body 7, and the detachable slide rail 15 are combined with each other to realize a variety of postures and angles for carrier-based aircraft landing, covering the possible posture range (such as one-wheel landing, two-wheel landing, etc.) and angle range (such as a glide angle of 3-5°).

[0046] To further optimize the solution, the measuring part includes a deck model 6, the bottom end of the deck model 6 is fixedly connected to the top end of the wedge-shaped body 7, an acceleration sensor 12 and several strain gauges 11 are arranged inside the deck model 6, and a thin film pressure sensor 5 is fixedly connected to the middle part of the top end of the deck model 6.

[0047] Deck Model 6 uses the same steel as the actual ship structure. The length and width of Deck Model 6 were selected based on the ship's deck structural support framework. Comparisons were made in stiffness, frequency, and modal characteristics. Similarity design criteria for dynamic strength were established using dimensional analysis to ensure similar dynamic response between Deck Model 6 and the actual ship. Deck Model 6 was designed based on the actual ship's structural form, taking into account transverse and longitudinal bulkheads and openings below the deck.

[0048] The thin film pressure sensor 5 is convenient for capturing the impact pressure position and distribution as well as the surface pressure distribution field diagram of the deck model 6, and supports transient load measurement. The strain gauge 11 is used to measure the structural response of the deck model 6 and evaluate the structural elastic / plastic stress state; the deck model 6 is used to simulate the ship deck structure and the strong frame structure below. The scaled model is used to reduce the size of the actual ship. The wedge 7 is made of steel structure, and the top inclination angle is adjusted according to the test conditions. The deck model 6 is fixed to the top of the wedge 7 by bolts. The deck model 6, the wedge 7, and the pad 8 are aligned up and down to avoid the deck model 6 boundary being suspended.

[0049] According to a further optimized solution, a load sensor 13 is provided on the landing gear 2 , a rolling bearing 14 is sleeved on the outer wall of the fixed track 3 , and the outer ring of the rolling bearing 14 is fixedly connected to the landing gear 2 .

[0050] The lower end of the rolling bearing 14 is open, and the rolling bearing 14 can reduce the movement friction between the landing gear 2 and the fixed rail 3 and the detachable slide rail 15. The load sensor 13 is used to measure the impact load.

[0051] The counterweight 1 and landing gear 2 are fastened together with bolts. The weight and center of gravity of the counterweight 1-landing gear 2 combination model are measured before the test. Rolling bearing 14 is used to connect the landing gear 2 and the fixed track 3. Balls are arranged inside the rolling bearing 14 to reduce friction. The fixed track 3 is welded to the supporting steel frame 10 via struts 4 to meet certain flatness requirements to prevent the counterweight 1 from getting stuck or lagging during the free fall. If necessary, the surface of the fixed track 3 is lubricated. A series of detachable slide rails 15 of different lengths are designed to adjust the impact angle when the landing gear 2 leaves the fixed track 3.

[0052] The load sensor 13 and thin-film pressure sensor 5 measure the time history of the impact load, while the strain gauge 11 and accelerometer 12 measure the structural dynamic response of the deck model 6. The measurement points are arranged according to research needs, primarily considering the locations of maximum stress and acceleration, as well as representative locations for plotting distribution curves. This addresses the difficulty of accurately presetting impact load measurement points.

[0053] The acceleration sensor 12 is used to measure the dynamic response of the deck model 6. It can output acceleration time history data and convert velocity change information through integration. The load sensor 13 is used to measure the load time history information of the landing gear 2 along the three spatial coordinate directions and convert it into the impact load amplitude and action angle.

[0054] In a further optimized solution, the recording device includes a camera 19 .

[0055] The camera 19 captures images during the test process, which can be used to analyze the landing gear 2's falling posture, impact angle, and impact position.

[0056] To simulate different ways a carrier aircraft might impact the deck, test conditions included aircraft attitude, impact energy, and impact location. Aircraft attitude conditions were achieved by selecting different landing gear configurations. A tilted main landing gear configuration simulated a single tail drop, a horizontal main landing gear configuration simulated a two-point tail drop, and a main and nose landing gear configuration simulated a three-point horizontal drop. Impact energy conditions were achieved by adjusting the impact mass and impact velocity. Impact positioning conditions were achieved by adjusting the deck model's tilt angle and longitudinal impact location.

[0057] The impact load was directly measured using load sensors 13 and thin film pressure sensors 5 to compare the effectiveness of the load inversion calculation results. The load sensors 13 were connected to the landing gear 2 test model; the thin film pressure sensors 5 were placed on the surface of the deck model 6.

[0058] The sampling period is determined according to the impact load data waveform and the natural vibration period of the structure, the test process data is measured, and the impact of different sampling periods on load collection is evaluated.

[0059] The deck model 6 is fixed on the wedge 7, and an impulse hammer is used to apply an impact load to the deck model 6. Single impact, two consecutive impacts, and three consecutive impacts are carried out. The impact load, deck strain, and deck acceleration response are measured. The natural vibration period and mode of the deck model 6 are calibrated through the hammer test.

[0060] The deck model 6 was fixed beneath the impact platform, and the landing gear 2 model was attached to the fixed track 3 and connected to the test and measurement system equipment. First, the landing gear 2 (including counterweight 1)-tire system was raised to a lower height and then released to verify the effectiveness of the test system. Then, tests were conducted according to the predetermined test conditions, measuring the impact load, deck strain, and deck acceleration response. This was to conduct experimental research on the impact of the carrier-based aircraft model on the deck.

[0061] Based on the measured load, strain, and acceleration information, a time history curve of the impact load and structural response was plotted. Based on the test load conditions such as aircraft attitude, impact energy, and impact location, the impact load and deck model 6 response under different loading modes were analyzed.

[0062] Adjust the mass of the counterweight 1 to analyze the impact of the mass of the carrier-based aircraft on the impact response of the deck model 6. Adjust the impact position to analyze the impact of different impact points on the impact response of the deck model 6. Adjust the angle of the deck model 6 or the angle of the detachable slide rail 15 to analyze the impact of different impact angles on the impact response of the deck model 6.

[0063] The impact test process of the landing gear 2 is recorded by the camera 19, and the trajectory curves during the impact process and the post-impact period are drawn to provide data for the impact trajectory curve prediction.

[0064] The present invention simulates the stiffness, damping and center of gravity of a carrier-based aircraft by using the counterweight 1 and the landing gear 2, thereby reducing the difficulty of simulating complex models of the carrier-based aircraft. The rolling bearing 14 enables the landing gear 2 to slide freely along the fixed track 3, thereby avoiding jamming or hysteresis during the sliding process. The curved track converts gravitational potential energy into a combination of different horizontal and vertical speeds, thereby achieving impacts at different speeds. The energy storage spring 18 achieves greater impact energy. The impact point position is adjusted by the bottom pulley 9 at the bottom of the support steel frame 10, thereby facilitating impacts at different positions of the deck model 6. The impact angle is adjusted by the detachable slide rail 15, thereby facilitating simulation of the landing angle of the carrier-based aircraft at the moment of impact. The inclination angle of the deck model 6 is adjusted by the wedge 7 to simulate the deck posture of the ship, thereby facilitating simulation of the ship's roll, pitch and other postures. The landing posture of the carrier-based aircraft is simulated by adjusting the number of landing gears 2, thereby facilitating simulation of one-wheel landing, two-wheel landing and other operating conditions of the carrier-based aircraft. The landing impact load is measured by the thin film pressure sensor 5, thereby facilitating measurement of the non-uniform distribution of the impact pressure.

[0065] This test device has a clear design principle, simple equipment layout, flexible load control, and diverse application scenarios. It facilitates the simulation of carrier-based aircraft impacting ship decks in multiple postures, multiple angles, and high energy, solving the problem that conventional methods are difficult to simulate carrier-based aircraft impacting ship decks.

[0066] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0067] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A test device for carrier-based aircraft impacting ship decks in multiple postures, multiple angles, and high energy, characterized by: Includes impact assembly and measurement assembly; The impact assembly includes a supporting steel frame (10), a plurality of bottom pulleys (9) are provided at the bottom end of the supporting steel frame (10), the top end of the supporting steel frame (10) is arc-shaped, a guide portion is fixedly connected to the top end of the supporting steel frame (10), the guide portion is matched with the top end of the supporting steel frame (10), an energy-enhancing portion is provided at the top end of the guide portion, an impact portion is slidably provided on the guide portion, the impact portion is magnetically connected to the bottom end of the energy-enhancing portion, and the bottom end of the guide portion is located above the measuring assembly; the measuring assembly is located on the sliding-out side of the impact portion; The measuring assembly includes a fixing portion, the top of which is inclined toward the guide portion, the top of which is fixedly connected to the measuring portion, and a recording device is provided above an end of the measuring portion away from the guide portion; The impact part includes a landing gear (2), the landing gear (2) is slidably connected to the guide part, the top end of the landing gear (2) is detachably connected to a counterweight (1), and the counterweight (1) is magnetically connected to the bottom end of the energy boosting part; The energy-increasing part includes a hook (17), the bottom end of the hook (17) is fixedly connected to an electromagnet (16), the electromagnet (16) is magnetically connected to the counterweight (1), the top end of the support steel frame (10) is fixedly connected to an energy storage spring (18), and the bottom end of the energy storage spring (18) abuts against the top end of the landing gear (2); The guide portion comprises two fixed rails (3) arranged in parallel, the fixed rails (3) being fixedly connected to the top of the support steel frame (10) via a strut (4), the landing gear (2) being slidably arranged between the two fixed rails (3), the top of the energy storage spring (18) being fixedly connected to the top of the fixed rail (3), the bottom end of the fixed rail (3) being detachably connected to a detachable slide rail (15), the lower end of the detachable slide rail (15) being located above the measuring portion; The number of the detachable slide rails (15) is at least one segment, and the angle of the landing gear (2) at the moment of falling is changed by adding different numbers of the detachable slide rails (15).

2. The multi-posture, multi-angle, high-energy impact test device for carrier-based aircraft on ship decks according to claim 1 is characterized in that: The fixing portion comprises a pad (8), the top end of the pad (8) is fixedly connected to a wedge-shaped body (7), the top end of the wedge-shaped body (7) is an inclined surface, the lower end of the wedge-shaped body (7) is arranged close to the fixed track (3), and the measuring portion is fixedly connected to the top end of the wedge-shaped body (7).

3. The multi-posture, multi-angle, high-energy impact test device for carrier-based aircraft on ship decks according to claim 2 is characterized in that: The measuring part comprises a deck model (6), the bottom end of the deck model (6) is fixedly connected to the top end of the wedge-shaped body (7), an acceleration sensor (12) and a plurality of strain gauges (11) are arranged inside the deck model (6), and a thin film pressure sensor (5) is fixedly connected to the middle part of the top end of the deck model (6).

4. The multi-posture, multi-angle, high-energy impact test device for carrier-based aircraft on ship decks according to claim 1 is characterized in that: A load sensor (13) is provided on the landing gear (2), a rolling bearing (14) is sleeved on the outer side wall of the fixed track (3), and the outer ring of the rolling bearing (14) is fixedly connected to the landing gear (2).

5. The multi-posture, multi-angle, high-energy impact test device for carrier-based aircraft on ship decks according to claim 1 is characterized in that: The recording device comprises a camera (19).

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