A variable angle of attack sea-air cross-medium vehicle thin-wall shell test system

Abstract

The present application relates to the technical field of ship and ocean engineering experiment, and particularly relates to a thin-wall shell test system for a sea-air cross-medium vehicle with a gradually changing attack angle. The system comprises a sea surface navigation boat, a swing arm mechanism, a towing mechanism and a vehicle test body. The swing arm mechanism is arranged on the sea surface navigation boat and has a rotational degree of freedom in the vertical plane. The towing mechanism is arranged on the swing arm mechanism and is connected with the vehicle test body. The towing mechanism is used for winding and unwinding the vehicle test body. When the sea surface navigation boat drags the vehicle test body in the seawater, the swing arm mechanism can be rotated to realize the water test of the vehicle test body with a gradually changing attack angle. The present application can realize the water test of a full-scale sea-air cross-medium vehicle model with a gradually changing attack angle, and can accurately and gradually control the initial speed, acceleration and attitude angle of the full-scale sea-air cross-medium vehicle model, thereby providing key data and theoretical support for the design and control algorithm of the sea-air cross-medium vehicle.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of ship and ocean engineering experiments, in particular to a thin-wall shell test system for a sea-air cross-medium vehicle with a gradually changing attack angle. BACKGROUND

[0002] In recent years, cross-medium vehicles have been paid great attention in the fields of aerospace and ship and ocean engineering as new unmanned platforms in new domains; since the cross-medium vehicles have various water exit modes, but the water exit speed is much lower than the underwater launch speed, and the water exit process has almost no bubble or cavity parameters, which is a new problem to be studied.

[0003] Due to the huge differences in density, viscosity and compressibility between water and air, the force of the water fluid has a great influence on the water exit of the cross-medium vehicle; generally, the water-air cross-medium vehicle can be divided into a rotary wing type and a fixed wing type according to the principle of lift; the lift of the rotary wing type cross-medium vehicle in the air is generated by the rotary wing, which can quickly change its water exit posture to reduce the influence of water exit; while the lift of the fixed wing type cross-medium vehicle mainly depends on its flight speed, which cannot quickly change its water exit posture, and the water exit resistance is different under different water exit bow angles, water exit attack angles, water exit speeds and water exit accelerations; therefore, accurate measurement of the water exit resistance is the key to the study of the fixed wing type water-air cross-medium vehicle; and since the propeller of the fixed wing type cross-medium vehicle is generally located at the bow during the water entry and exit process, it is similar to a cantilever beam with variable cross-section in its constraint test research, and the test device needs higher rigidity, so the force measurement of the fixed wing type water-air cross-medium vehicle under different water exit parameters is a key point in the field of research on the fixed wing type water-air cross-medium vehicle.

[0004] Although the existing patent has disclosed a cross-medium vehicle water entry and exit test device, for example, the Chinese patent with the publication number "CN106932171B", which can realize the water entry and exit test of the cross-medium vehicle model under different angles and initial speeds, can accurately control the initial speed and angle of the water entry and exit of the cross-medium vehicle model, meet the water entry and exit test of the initial speed from 0m / s to 20m / s and the angle from close to 0° to 90°, and can realize the simulation test of different water entry and exit modes such as free water entry, free water exit, forced water entry and forced water exit. However, since the number of measurement parameters of this patent is limited in range, it cannot measure the gradually changing attack angle water exit, and therefore it is not suitable for the measurement of the full autonomous adjustment water exit working condition of the fixed wing type cross-medium vehicle. SUMMARY

[0005] In order to solve the problems that the measurement parameter range of the existing cross-medium vehicle water entry and exit test device is limited, the gradually changing attack angle water entry cannot be measured, and the device is not suitable for measuring the full autonomous adjustment water entry working condition of the fixed-wing cross-medium vehicle, the present application aims to provide a gradually changing attack angle sea-air cross-medium vehicle thin-wall shell test system.

[0006] In order to achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0007] The present application provides a gradually changing attack angle sea-air cross-medium vehicle thin-wall shell test system, which comprises a sea surface navigation boat, a swing arm mechanism, a towing mechanism and a vehicle test body, wherein the swing arm mechanism is arranged on the sea surface navigation boat and has the freedom of rotation in the vertical plane; the towing mechanism is arranged on the swing arm mechanism and is connected with the vehicle test body, and the towing mechanism is used for winding and unwinding the vehicle test body; when the sea surface navigation boat drags the vehicle test body to navigate in the seawater through the towing mechanism, the rotation of the swing arm mechanism can realize the gradually changing attack angle water entry test of the vehicle test body.

[0008] In a possible implementation manner, the vehicle test body comprises a vehicle thin-wall shell and a test head and a test tail connected to the front and rear ends of the vehicle thin-wall shell, wherein the test head is connected with the towing mechanism, a head six-dimensional force sensor is arranged in the test head, a tail six-dimensional force sensor is arranged in the test tail, and the head six-dimensional force sensor and the tail six-dimensional force sensor can respectively sense the gradually changing load at the front and rear ends of the vehicle thin-wall shell when the vehicle thin-wall shell is in the gradually changing attack angle water entry.

[0009] In a possible implementation manner, the vehicle thin-wall shell is provided with a counterweight module and a stress and strain test sensor, and the stress and strain test sensor is used for detecting the stress and strain inside the vehicle thin-wall shell.

[0010] In a possible implementation manner, the test head comprises a head body, a head connecting plate and a head profiling rubber, wherein the head body is connected with the head connecting plate through the head profiling rubber with a hollow cavity, the head six-dimensional force sensor is arranged in the hollow cavity of the head profiling rubber, and the two ends of the head six-dimensional force sensor are respectively connected with the head body and the head connecting plate; the inside of the head profiling rubber is filled with pressure-adjustable gas; the head connecting plate is positioned and matched with the front end of the vehicle thin-wall shell through the head profiling stopper arranged on the outer side face of the head connecting plate, and the head connecting plate is connected with the vehicle thin-wall shell through bolts.

[0011] In a possible implementation manner, left and right side duck wings are symmetrically arranged on the two sides of the head body, and the left and right side duck wings are respectively provided with left and right side duck wing elevators,

[0012] In a possible implementation manner, the test tail includes a tail body, a tail connecting plate and a tail profiling rubber, the tail body is connected with the tail connecting plate through the tail profiling rubber with a hollow cavity, the tail six-dimensional force sensor is arranged in the hollow cavity of the tail profiling rubber and connected with the tail body and the tail connecting plate at two ends respectively, the inside of the tail profiling rubber is filled with pressure-adjustable gas, the tail connecting plate is positioned and matched with the rear end of the thin-walled shell of the aircraft through the tail profiling stopper arranged on the outer side, and the tail connecting plate is connected with the thin-walled shell of the aircraft through bolts.

[0013] In a possible implementation manner, the tail body is symmetrically provided with a left tail wing and a right tail wing on two sides, and a left tail wing elevator and a right tail wing elevator are respectively arranged on the left tail wing and the right tail wing; a vertical tail wing is arranged on the top of the tail body, and a rudder is arranged on the vertical tail wing.

[0014] In a possible implementation manner, the sea surface navigation boat includes two speedboats and a cross beam connected with the two speedboats, and the swing arm mechanism is arranged on the cross beam.

[0015] In a possible implementation manner, the swing arm mechanism includes an outer ring gear rotary bearing, a swing arm, an output gear, a swing reducer and a swing motor, the root of the swing arm is installed on the cross beam through the outer ring gear rotary bearing, the swing reducer is installed on the cross beam and connected with the swing motor at an input end, an output end of the swing reducer is connected with the output gear, and the output gear is engaged with an outer ring of the outer ring gear rotary bearing; the swing motor drives the swing arm to rotate 360 degrees around the cross beam through the swing reducer.

[0016] In a possible implementation manner, the towing mechanism includes a traction motor, a traction reducer, a winding drum, a traction steel wire rope and a guide wheel set, the guide wheel set is arranged on the free end of the swing arm, the traction reducer is arranged at the root of the swing arm and connected with the traction motor at an input end, an output end of the traction reducer is connected with the winding drum, one end of the traction steel wire rope is wound on the winding drum, and the other end is connected with the aircraft test body after passing through the guide wheel set.

[0017] The gradual change attack angle sea-air cross medium aircraft thin-walled shell test system provided by the application can accurately and gradually control the initial speed, acceleration and attitude angle of a full-scale sea-air cross medium aircraft model, meets the water-out test of the initial speed of 36 km / h-112 km / h, the acceleration of 0.07 m / s^2-1 m / s^2 and the attitude angle of 0°-26°, and the water-in test and the water-out test of the full-scale sea-air cross medium aircraft model can be realized.

[0018] The vehicle test body of the application contains a head six-dimensional force sensor and a tail six-dimensional force sensor, which can sense the gradually changing load at the front and rear ends of the thin-walled shell 7 of the vehicle when the vehicle thin-walled shell 7 is out of water at a gradually changing attack angle, so it can be widely used in various working conditions of sea-air cross-medium vehicle model test, and can quickly and effectively obtain various test data such as variable hydrodynamic force and hydrodynamic moment of the sea-air cross-medium vehicle full-scale model when it is out of water, and the free surface change process in the process of entering and out of water, etc., providing key data and theoretical support for the design and control algorithm of the sea-air cross-medium vehicle.

[0019] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent to those skilled in the art from the description, or can be learned by practice of the application. The objects and other advantages of the application will be realized and attained by the structure particularly pointed out in the written description and claims.

[0020] The technical solutions of the application will be further described in detail below with the help of the drawings and examples. BRIEF DESCRIPTION OF DRAWINGS

[0021] The accompanying drawings, which are included to provide a further understanding of the application and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:

[0022] Figure 1 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application;

[0023] Figure 2 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application; Figure 1 is a partial view at A in the middle;

[0024] Figure 3 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application; Figure 2 is a partial view at B in the middle;

[0025] Figure 4 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application; Figure 2 is a partial view at C in the middle;

[0026] Figure 5 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application;

[0027] Figure 6 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application; Figure 5 is a partial view at D in the middle;

[0028] Figure 7 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application;

[0029] Figure 8 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application;

[0030] Figure 9 is a perspective view of a gradually changing attack angle sea-air cross-medium vehicle thin-walled shell test system of the application;Figure 8 Local view at E;

[0031] Figure 10 Schematic diagram of the connection between the test tail and the thin-walled shell of the vehicle in the application;

[0032] Figure 11 Schematic diagram of a navigation state of a thin-walled shell test system of a sea-air cross-medium vehicle with a gradually changing attack angle in the application;

[0033] Figure 12 Schematic diagram of another navigation state of a thin-walled shell test system of a sea-air cross-medium vehicle with a gradually changing attack angle in the application.

[0034] In the figure: 1-sea level, 2-speedboat, 3-crossbeam, 4-swinging arm mechanism, 401-outer ring rotating bearing, 402-swinging arm, 403-output gear, 404-swinging reducer, 405-swinging motor, 5-dragging mechanism, 501-towing motor, 502-towing reducer, 503-winding drum, 504-towing steel wire rope, 505-guide wheel I, 506-guide wheel II, 6-test head, 601-head body, 602-head connecting plate, 603-head profiling stopper, 604-head connecting hole, 605-head profiling rubber, 606-head six-dimensional force sensor, 607-left aileron, 608-right aileron, 609-left aileron elevator, 610-right aileron elevator, 611-front screw, 7-vehicle thin-walled shell, 701-front end face, 702-front curved hole, 703-rear end face, 704-rear curved hole, 8-test tail, 801-tail body, 802-tail connecting plate, 803-tail profiling stopper, 804-tail connecting hole, 805-tail profiling rubber, 806-tail six-dimensional force sensor, 807-left tail wing, 808-right tail wing, 809-left tail wing elevator, 810-right tail wing elevator, 811-tail screw, 812-vertical tail, 813-rudder, 9-strain gauge. DETAILED DESCRIPTION

[0035] In the application, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above-mentioned terms in the application can be understood according to the specific circumstances.

[0036] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0037] The present invention provides a thin-wall shell testing system for a sea-air cross-medium vehicle with a gradient angle of attack, which can realize the water exit test of a full-scale sea-air cross-medium vehicle model at a gradient angle of attack, and can perform relatively precise gradient control of the initial velocity, acceleration, and attitude angle of the full-scale sea-air cross-medium vehicle model. Figures 1 to 12 As shown, the sea-air cross-medium vehicle thin-wall shell test system with a gradual attack angle includes a surface sailing boat, a swing arm mechanism 4, a towing mechanism 5 and a vehicle test body, wherein the swing arm mechanism 4 is arranged on the surface sailing boat and has the freedom of rotation in the vertical plane; the towing mechanism 5 is arranged on the swing arm mechanism 4 and connected to the vehicle test body, and the towing mechanism 5 is used to retract and release the vehicle test body; when the surface sailing boat drags the vehicle test body through the towing mechanism 5 to navigate in the sea water, the rotation of the swing arm mechanism 4 can realize the water test of the vehicle test body with a gradual attack angle.

[0038] See also Figure 1 As shown, in an embodiment of the present invention, the sea-surface sailing boat includes two speedboats 2 and a beam 3 connected to the two speedboats 2, and a swing arm mechanism 4 is provided on the beam 3, and the two speedboats 2 provide power for sailing and towing the aircraft test body.

[0039] See also Figure 3 As shown, in an embodiment of the present invention, the swing arm mechanism 4 includes an outer ring gear slewing bearing 401, a swing arm 402, an output gear 403, a swing reducer 404 and a swing motor 405, wherein the root of the swing arm 402 is mounted on the beam 3 through the outer ring gear slewing bearing 401, the swing reducer 404 is mounted on the beam 3, and the input end is connected to the swing motor 405, the output end of the swing reducer 404 is connected to the output gear 403, and the output gear 403 is engaged with the outer ring gear of the outer ring gear slewing bearing 401; the swing motor 405 drives the swing arm 402 to rotate 360° around the beam 3 through the swing reducer 404.

[0040] Specifically, the outer ring gear slewing bearing 401 is a four-point ball bearing. The inner ring of this four-point ball bearing is fixed to the crossbeam 3, and the outer ring side of this four-point ball bearing 401 is fixed to the root of the swing arm 4. The swing arm 4 is a flat plate structure, with the plane of the swing arm 4 being orthogonal to the axis of the crossbeam 3. The swing of the swing arm 4 can provide traction acceleration for the aircraft test body.

[0041] See also Figures 2 to 4As shown, in an embodiment of the present invention, the towing mechanism 5 includes a traction motor 501, a traction reducer 502, a winch drum 503, a traction wire rope 504 and a guide wheel group, wherein the guide wheel group is arranged at the free end of the swing arm 402, the traction reducer 502 is arranged at the root of the swing arm 402, and the input end is connected to the traction motor 501, the output end of the traction reducer 502 is connected to the winch drum 503, one end of the traction wire rope 504 is wound around the winch drum 503, and the other end is connected to the aircraft test body after passing through the guide wheel group.

[0042] Specifically, the guide wheel assembly includes parallel guide wheel I 505 and guide wheel II 506. The axes of guide wheels I 505 and II 506 are perpendicular to the swing arm 402, and the traction wire rope 504 passes between guide wheels I 505 and II 506. During operation, the traction motor 501 drives the hoist drum 503 through the traction reducer 502 to rotate, thereby releasing or retrieving the traction wire rope 504.

[0043] See also Figure 2 、 Figures 5 to 10 As shown, in an embodiment of the present invention, the aircraft test body includes an aircraft thin-walled shell 7 and a test head 6 and a test tail 8 connected to the front and rear ends of the aircraft thin-walled shell 7, wherein the test head 6 is connected to the traction wire rope 504, and a head six-dimensional force sensor 606 is provided in the test head 6, and a tail six-dimensional force sensor 806 is provided in the test tail 8. The head six-dimensional force sensor 606 and the tail six-dimensional force sensor 806 can respectively sense the gradual loads at the front and rear ends of the aircraft thin-walled shell 7 when it exits the water at a gradual attack angle.

[0044] In an embodiment of the present invention, the thin-walled outer shell 7 of the aircraft is provided with a counterweight module and a stress and strain test sensor, and the stress and strain test sensor is used to detect the stress and strain inside the thin-walled outer shell 7 of the aircraft.

[0045] Furthermore, the thin-walled shell 7 of the aircraft also contains an internal pressure control device and a battery. The devices inside the thin-walled shell 7 of the aircraft can effectively counterweight and measure the internal strain and stress of the thin-walled shell 7 of the aircraft. The stress and strain test sensor preferably uses a strain gauge 9.

[0046] See also Figures 5 to 7As shown, in the embodiment of the present application, the test head 6 comprises a head body 601, a head connecting plate 602 and a head profiled rubber 605, wherein the head body 601 is connected with the head connecting plate 602 through the head profiled rubber 605 having a hollow cavity, the head six-dimensional force sensor 606 is arranged in the hollow cavity of the head profiled rubber 605 and connected with the head body 601 and the head connecting plate 602 at two ends respectively; the inside of the head profiled rubber 605 is filled with pressure-adjustable gas; the head connecting plate 602 is positioned and matched with the front curved hole 702 of the thin-walled outer shell 7 of the aircraft through the head profiled stop 603 arranged on the outer side surface of the head connecting plate 602, and the outer side surface of the head connecting plate 602 is attached to the front end surface 701 of the thin-walled outer shell 7 of the aircraft. A plurality of head connecting holes 604 are arranged on the head connecting plate 602, and the front end surface 701 of the thin-walled outer shell 7 of the aircraft is connected with the head connecting holes 604 on the head connecting plate 602 through the front screws 611. The front end of the head body 601 is connected with the traction steel wire rope 504.

[0047] Further, the left and right side wings 607 and 608 are symmetrically arranged on the two sides of the head body 601, and the left and right side wing elevators 609 and 610 are arranged on the left and right side wings 607 and 608 respectively, so that the pitch angle and the roll angle of the aircraft test body can be controlled.

[0048] Specifically, one end of the head profiled rubber 605 is sealingly bonded with the head body 601, and the other end of the head profiled rubber 605 is sealingly bonded with the head connecting plate 602. Since the inside of the head profiled rubber 605 is filled with pressure-adjustable gas, the shape of the head profiled rubber 605 is coherent with the overall shape of the test body.

[0049] Referring to Figures 8 to 10 As shown, in the embodiment of the present application, the test tail 8 comprises a tail body 801, a tail connecting plate 802 and a tail profiled rubber 805, wherein the tail body 801 is connected with the tail connecting plate 802 through the tail profiled rubber 805 having a hollow cavity, the tail six-dimensional force sensor 806 is arranged in the hollow cavity of the tail profiled rubber 805 and connected with the tail body 801 and the tail connecting plate 802 at two ends respectively, and the tail profiled rubber 805 is filled with pressure-adjustable gas; the tail connecting plate 802 is positioned and matched with the rear curved hole 704 of the thin-walled outer shell 7 of the aircraft through the tail profiled stop 803 arranged on the outer side surface of the tail connecting plate 802, and the outer side surface of the tail connecting plate 802 is attached to the rear end surface 703 of the thin-walled outer shell 7 of the aircraft; a plurality of tail connecting holes 804 are arranged on the tail connecting plate 802, and the rear end surface 703 of the thin-walled outer shell 7 of the aircraft is connected with the tail connecting holes 804 on the tail connecting plate 802 through the tail screws 811.

[0050] Furthermore, tail body 801 is symmetrically provided with a left tail wing 807 and a right tail wing 808, each equipped with a left tail elevator 809 and a right tail elevator 810. A vertical tail wing 812 is provided on top of tail body 801, each equipped with a rudder 813. The left tail elevator 809 and the right tail elevator 810 can control the pitch and roll angles of the test vehicle.

[0051] Specifically, one end of the tail profiling rubber 805 is sealed and bonded to the tail body 801, and the other end of the tail profiling rubber 805 is sealed and bonded to the tail connecting plate 802. Since the tail profiling rubber 805 is filled with pressure-adjustable gas, the shape of the tail profiling rubber 805 is consistent with the shape of the aircraft test body.

[0052] In this embodiment, the vehicle test body simulates a fixed-wing submersible with a head propeller, and the traction wire rope 504 simulates the head propeller. The rotation axis of the head propeller can be non-collinear with the axis of the submersible, and its transmission principle is similar to that of a large propeller of a helicopter.

[0053] The present invention provides a thin-walled shell testing system for sea-air cross-media vehicles with a gradual angle of attack. This system is designed to meet the relevant needs of sea-air cross-media vehicle research and is a water-exit testing system with variable initial velocity, variable acceleration and variable attitude angle, which can realize the measurement of key data.

[0054] See also Figure 11 、 Figure 12 As shown, the present invention can realize the water exit test of a full-scale sea-air cross-medium vehicle model at a gradual angle of attack, and can perform relatively precise gradual control of the initial speed, acceleration, and attitude angle of the full-scale sea-air cross-medium vehicle model, meeting the water exit test with an initial speed of 36km / h to 112km / h, an acceleration of 0.07m / s^2 to 1m / s^2, and an attitude angle of 0°-26°. It can realize the constrained model water exit test of the full-scale sea-air cross-medium vehicle model. Since the aircraft test body contains a six-dimensional force sensor 606 at the head and a six-dimensional force sensor 806 at the tail, it can sense the gradual loads on the front and rear ends of the aircraft's thin-walled shell 7 when it exits the water at a gradual angle of attack. Therefore, it can be widely used in various working conditions of sea and air cross-media aircraft model tests. At the same time, it can quickly and effectively obtain various test data such as the variable hydrodynamics, hydrodynamic torque, etc. of the full-scale model of the sea and air cross-media aircraft when it exits the water at a certain speed or a certain acceleration, as well as the free liquid surface change process during the entry and exit processes, etc., providing key data and theoretical support for the design and control algorithm of the sea and air cross-media aircraft.

[0055] Obviously, many modifications and variations of the present application are possible in light of the above teachings. It is, therefore, to be understood that within the scope of the appended claims and their equivalents, the application can be practiced otherwise than as specifically described.

Claims

1. A variable angle of attack sea-air cross-medium vehicle thin-walled enclosure test system, characterized by, The application relates to a sea surface sailing boat, a swing arm mechanism (4), a towing mechanism (5) and a vehicle test body, wherein the swing arm mechanism (4) is arranged on the sea surface sailing boat and has the freedom of rotating in a vertical plane; the towing mechanism (5) is arranged on the swing arm mechanism (4) and is connected with the vehicle test body, and the towing mechanism (5) is used for winding and unwinding the vehicle test body; when the sea surface sailing boat drags the vehicle test body to sail in seawater through the towing mechanism (5), the vehicle test body can realize the water test of gradually changing the attack angle through the rotation of the swing arm mechanism (4); The vehicle test body comprises a vehicle thin-wall shell (7) and test heads (6) and test tails (8) connected to front and rear ends of the vehicle thin-wall shell (7), wherein the test heads (6) are connected with the towing mechanism (5), the test heads (6) are internally provided with head six-dimensional force sensors (606), the test tails (8) are internally provided with tail six-dimensional force sensors (806), and the head six-dimensional force sensors (606) and the tail six-dimensional force sensors (806) can respectively sense the gradually changing loads of the front and rear ends of the vehicle thin-wall shell (7) when the vehicle thin-wall shell (7) sails in the water with gradually changing attack angles; The sea surface sailing boat comprises two speedboats (2) and a cross beam (3) connected with the two speedboats (2), and the swing arm mechanism (4) is arranged on the cross beam (3); The swing arm mechanism (4) comprises an outer gear ring rotary bearing (401), a swing arm (402), an output gear (403), a swing reducer (404) and a swing motor (405), wherein the root of the swing arm (402) is arranged on the cross beam (3) through the outer gear ring rotary bearing (401), the swing reducer (404) is arranged on the cross beam (3) and is connected with the swing motor (405) at an input end, an output end of the swing reducer (404) is connected with the output gear (403), and the output gear (403) is engaged with an outer gear ring of the outer gear ring rotary bearing (401); the swing motor (405) drives the swing arm (402) to rotate 360 DEG around the cross beam (3) through the swing reducer (404); The towing mechanism (5) comprises a traction motor (501), a traction reducer (502), a winding drum (503), a traction steel wire rope (504) and a guide wheel set, wherein the guide wheel set is arranged at a free end of the swing arm (402), the traction reducer (502) is arranged at the root of the swing arm (402) and is connected with the traction motor (501) at an input end, an output end of the traction reducer (502) is connected with the winding drum (503), one end of the traction steel wire rope (504) is wound on the winding drum (503), and the other end passes through the guide wheel set and is connected with the vehicle test body.

2. The progressive angle of attack sea-air trans-medium vehicle thin- walled enclosure test system of claim 1, wherein, The vehicle thin-wall shell (7) is provided with a counterweight module and stress and strain test sensors, and the stress and strain test sensors are used for detecting the stress and strain in the vehicle thin-wall shell (7).

3. The progressive angle of attack sea-air trans-medium vehicle thin- walled enclosure test system of claim 1, wherein, The test head (6) includes a head body (601), a head connecting plate (602) and a head profiling rubber (605), wherein the head body (601) is connected with the head connecting plate (602) through the head profiling rubber (605) with a hollow cavity, the head six-dimensional force sensor (606) is arranged in the hollow cavity of the head profiling rubber (605) and connected with the head body (601) and the head connecting plate (602) at two ends respectively; the inside of the head profiling rubber (605) is filled with pressure-adjustable gas; the head connecting plate (602) is positioned and matched with the front end of the aircraft thin-wall shell (7) through the head profiling stop (603) arranged on the outer side, and the head connecting plate (602) is connected with the aircraft thin-wall shell (7) through bolts.

4. The progressive angle of attack sea-air trans-medium vehicle thin- walled enclosure test system of claim 3, wherein, The head body (601) is symmetrically provided with a left side wing (607) and a right side wing (608) on two sides, and the left side wing (607) and the right side wing (608) are respectively provided with a left side wing elevator (609) and a right side wing elevator (610).

5. The progressive angle of attack sea-air trans-medium vehicle thin- walled enclosure test system of claim 1, wherein, The test tail (8) includes a tail body (801), a tail connecting plate (802) and a tail profiling rubber (805), wherein the tail body (801) is connected with the tail connecting plate (802) through the tail profiling rubber (805) with a hollow cavity, the tail six-dimensional force sensor (806) is arranged in the hollow cavity of the tail profiling rubber (805) and connected with the tail body (801) and the tail connecting plate (802) at two ends respectively, and the inside of the tail profiling rubber (805) is filled with pressure-adjustable gas; the tail connecting plate (802) is positioned and matched with the rear end of the aircraft thin-wall shell (7) through the tail profiling stop (803) arranged on the outer side, and the tail connecting plate (802) is connected with the aircraft thin-wall shell (7) through bolts.

6. The progressive angle of attack sea-air trans-medium vehicle thin- walled enclosure test system of claim 5, wherein, The tail body (801) is symmetrically provided with a left side fin (807) and a right side fin (808) on two sides, and the left side fin (807) and the right side fin (808) are respectively provided with a left side fin elevator (809) and a right side fin elevator (810); the top of the tail body (801) is provided with a vertical fin (812), and the vertical fin (812) is provided with a rudder (813).

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