An aerial flight experimental launching device for a gliding torpedo model

Abstract

The invention discloses an aerial flight test launch device for a gliding torpedo model, which belongs to the field of fluid dynamics experiments. The device comprises a launch mechanism, a flip mechanism, and a support structure. The launch mechanism is hinged to the support structure through the flip mechanism, and the launch angle of the launch mechanism is adjusted by adjusting the fixed angle of the flip mechanism. The launch mechanism comprises a power assembly, a pusher assembly, and a horizontal tail rail, and the test mine body is arranged at the front end of the pusher assembly. The power assembly drives the pusher assembly to perform linear motion along a set trajectory, thereby pushing the test mine body to perform accelerated motion along the horizontal tail rail until it flies out of the horizontal tail rail. The invention utilizes the boost of the pusher to provide power for the high-altitude gliding torpedo, and the front end rail of the gun barrel provides it with an acceleration stroke, so that the boost process is completed on the rail to obtain sufficient speed. The launch posture of the mine body is adjusted by designing the horizontal tail rail mechanism; and different initial pitch angle working conditions are provided for the launch of the mine body by the flip mechanism.

Description

Technical Field

[0001] The invention belongs to the field of fluid dynamics experiments, and in particular relates to an aerial flight experiment launching device for a gliding torpedo model. Background Art

[0002] Aviation anti-submarine warfare has always been a very effective form of anti-submarine warfare. Surveillance and attacks from the air have posed a huge threat to the survivability and combat effectiveness of submarines. For a long time, the confrontation between air and submarine has maintained a situation where the air is superior and the submarine is inferior. With the emergence and development of submarine-to-air missiles, submarine air defense technology has also made great progress. In the process of lowering the flight altitude and launching torpedoes from low altitude to attack submarines, the aviation anti-submarine platform must meet the conditions of lower than a certain drop altitude and drop speed. The altitude is generally required to be less than 10,000m and the speed is less than 1,000km / h. However, this height and speed restriction is undoubtedly conducive to submarine-to-air missiles attacking aviation anti-submarine platforms. The dangers faced by aviation anti-submarine platforms are becoming more and more severe, and the situation of air superiority and submarine inferiority is about to be rewritten. The key issue of aviation anti-submarine research is to increase the torpedo drop altitude of aviation anti-submarine platforms so that they can launch attacks outside the air defense range of submarines or even escort ships.

[0003] The high-altitude gliding torpedo is a new type of torpedo weapon developed based on the concept of "high-altitude anti-submarine warfare". It realizes the integration of high-altitude gliding and underwater navigation, and has the advantages of low cost, long range, and the ability to accurately perform tasks. This new type of torpedo weapon is generally a modification of the existing light torpedo, equipped with a gliding system component, carried on an aircraft, and launched from an altitude of more than 10,000 meters. After the high-altitude gliding torpedo is safely separated from the delivery carrier, it can achieve unpowered gliding of tens of kilometers in the air through the automatically ejected gliding device. When it reaches the predetermined area, it can also be attached to the rocket booster installed on the gliding device of the aircraft when performing specific tasks, so that the high-altitude gliding torpedo can penetrate at low altitude, guide and control it to fly to the water entry area, and enable it to achieve deceleration and adjust the water entry posture before entering the water, completing the aircraft variant, that is, the gliding device is separated from the water. After entering the water, the high-altitude gliding torpedo can continue to perform the established mission task driven by the torpedo propeller.

[0004] In order to achieve the predetermined technical and tactical indicators and complete the combat mission, it is necessary to ensure that the high-altitude gliding torpedo should have good aerodynamic characteristics, dynamic characteristics and good gliding range extension effect, and all three are closely related to the research on the aerodynamic shape of the high-altitude gliding torpedo. The length of the air gliding trajectory accounts for most of the total trajectory length of the high-altitude gliding torpedo, and its ballistic characteristics are one of the important indicators of whether the high-altitude gliding torpedo meets the design requirements. Therefore, designers need to perform theoretical calculations, simulation calculations, and finally and most importantly, experimental measurement and verification.

[0005] Since the experimental model high-altitude gliding torpedo is equipped with a gliding system component, its appearance is quite different from that of a conventional torpedo. The most obvious difference is the flying wing above the torpedo body, which needs to remain extended during the experiment. The commonly used launching gun barrels are not suitable for this experiment. Therefore, it is necessary to design an experimental device suitable for high-altitude gliding torpedo high-speed launch to complete the aerial flight process.

[0006] In the invention with publication number 108109489A, an auxiliary experimental device for structure entry into water is disclosed, including a launch platform and an impact water tank, which can be used for high-speed water entry experiments of structures. The launch platform can adjust the inclination angle within the range of 0°-90°, and the launch position can also be adjusted longitudinally. Special design is made to address the problem of oscillation of the launch platform under the impact of reaction force to ensure the stability of the launch platform. As a platform, the launch platform can be configured with different launch modules to form a launch system. However, the structure applicable to its device is only a regular shape of a rotating body, and the launch tube is a closed circular tube. It cannot carry a mine body equipped with a gliding wing device, and the structure model used is small in size, and it is impossible to carry out high-speed water entry experiments of large-size models. At the same time, the parameters of the gas cylinder and the size of the water tank cannot meet the requirements of higher-speed water entry experiments, and the experimental conditions that can be achieved are relatively single.

[0007] In the invention with publication number 111252264A, a UAV launch device is disclosed, including: a traction system, a buffer mechanism, an ejection guide rail, a release mechanism, a front support, an ejection trolley and a rear support; the UAV is mounted on the ejection trolley, and the ejection trolley can slide to the front end along the ejection guide rail under the action of the elastic restoring force, and the buffer mechanism is used to buffer and decelerate the ejection trolley, and the UAV can be launched relative to the ejection trolley under the action of inertia. The launch device has a simple and reliable structure, and its launch is easy to operate and safe and reliable, and can be lightweight, and has good ease of use, safety and durability. However, the launch speed that can be achieved by this device is low, and it cannot achieve the launch of UAVs with different initial postures. Summary of the invention

[0008] Technical issues to be solved:

[0009] In order to avoid the shortcomings of the prior art, the present invention proposes an aerial flight experiment launch device for a gliding torpedo model. Through the design of a propelling bullet, a high-altitude gliding torpedo that cannot be launched in a gun barrel can utilize the boosting effect of the propelling bullet. The front end guide rail of the gun barrel provides an acceleration stroke for it, and the boosting process is completed on the guide rail to obtain a sufficient speed. Through the design of the horizontal tail guide rail mechanism at the front section of the gun barrel, the height of the guide rails on both sides is adjusted, so that the guide rails on both sides have a height difference, and the torpedo body on the guide rail has different launch postures, providing different roll angle conditions for the experiment. Through the design of the flipping mechanism, different openings on the angle plate are used to provide different initial pitch angle conditions for the torpedo body launch.

[0010] The technical solution of the present invention is: an aerial flight experiment launch device for a gliding torpedo model, characterized in that: it comprises a launch mechanism, a flip mechanism, and a support structure, wherein the launch mechanism is hinged to the support structure through the flip mechanism, and the launch angle of the launch mechanism is adjusted by adjusting the fixed angle of the flip mechanism;

[0011] The launching mechanism comprises a power assembly, a propulsion missile assembly and a horizontal tail rail, and the experimental mine body is arranged at the front end of the propulsion missile; the power assembly drives the propulsion missile assembly to perform linear motion along a set trajectory, thereby pushing the experimental mine body to perform accelerated motion along the horizontal tail rail until it flies out of the horizontal tail rail.

[0012] A further technical solution of the present invention is: the launching mechanism also includes a gun barrel, the power assembly is arranged at the end of the gun barrel, the thruster assembly is located in the gun barrel, and the horizontal tail rail is coaxially arranged at the front end of the gun barrel; the front end of the thruster assembly is connected to the tail end of the experimental mine body through a magnet, and the flying wings of the experimental mine body are placed on the two side rails of the horizontal tail rail; the power assembly drives the thruster assembly to perform linear acceleration motion in the gun barrel.

[0013] A further technical solution of the present invention is: the gun barrel is welded to the gun barrel rack through four track pads arranged along the length direction, and the gun barrel rack is fixed on the flip mechanism.

[0014] A further technical solution of the present invention is: the power assembly includes a high-pressure gas cylinder, the inlet end of the high-pressure gas cylinder is connected to an air pump through a flange, and air is compressed into the high-pressure gas cylinder through the air pump; the outlet end of the high-pressure gas cylinder is sealed and connected to the rear end of the gun barrel through a flange, and the propulsion projectile assembly is pushed to accelerate movement by the high-pressure gas.

[0015] A further technical solution of the present invention is: the push bullet assembly includes a push bullet tail section, a push rod, a guide flange, and a sealing cap; the push bullet tail section is a disc structure, coaxially fixed to the tail end of the push rod, and its outer diameter is equivalent to the inner diameter of the gun barrel, and can be positioned in the gun barrel by friction in the absence of external force; the push rod is a hollow straight rod, the front end of which is sealed by a sealing cap, and a magnet is installed on the sealing cap; the guide flange is coaxially fixed to the push rod and is located before the center of mass of the push rod, ensuring that the push bullet assembly remains on the central axis of the gun barrel during the firing process.

[0016] A further technical solution of the present invention is that: the front end of the lower half ring of the gun barrel extends forward in the extension direction to form a semicircular arc plate track; the horizontal tail rail includes two parallel straight rails, which are fixedly installed above the two side edges of the semicircular arc plate track through the rear horizontal tail rail support, the front horizontal tail rail support, and the horizontal tail rail-gun barrel connecting piece;

[0017] The horizontal tail rail-barrel connecting piece is a flat plate with an arc-shaped notch on one side, and the arc-shaped notch is consistent with the outer peripheral surface of the semicircular arc plate track, and is used to support the semicircular arc plate track;

[0018] The rear horizontal tail rail support and the front horizontal tail rail support are respectively arranged at the rear end and the front end of the semicircular arc plate track, and their upper ends are connected to the two tracks of the horizontal tail rail, and their lower ends are connected to the two sides of the horizontal tail rail-barrel connecting piece through round head studs; by adjusting the axial tightening of the round head studs, the height adjustment of the tracks on both sides is achieved, so that a height difference is generated on the left and right tracks, thereby adjusting the initial launch roll angle of the mine body.

[0019] A further technical solution of the present invention is that the edge of the semicircular arc plate track at the front section of the gun barrel is higher than the center of mass height of the experimental mine body, so that the mine body can be stuck in the track, so that the mine body will not fly off the track prematurely due to the reaction force during the launching process, thereby ensuring the stability of the trajectory during the launching process.

[0020] A further technical solution of the present invention is: the support structure includes a base frame and a track support frame, the base frame is used to fix and support the flipping mechanism and the launching mechanism, and the track support frame includes a track support rod and a track support frame base; the track support rod is a Y-shaped structure, the lower end of which is slidably connected to the track support frame base and can adjust the height in the vertical direction, and the upper end fork structure is used to support the semicircular plate track of the front section of the gun barrel.

[0021] A further technical solution of the present invention is: the flip mechanism comprises an angle disc holder, an angle disc holder shaft, an angle disc, a flip shaft, a flip shaft bearing and a barrel holder, and the flip shaft bearing and the angle disc holder are respectively fixed to the front and rear ends of the support structure;

[0022] The angle disc is a fan-shaped structure, and a through hole is opened on the small end surface of the angle disc, which is hinged with the tilting shaft bearing through the tilting shaft, so that the angle disc can rotate around the tilting shaft, and a plurality of through holes are evenly distributed along the circumference of the large end surface of the angle disc as angle adjustment holes; the large end of the angle disc is connected to the angle disc holder through the angle disc clamping shaft;

[0023] The two groups of flipping mechanisms are symmetrically installed on both sides of the supporting structure, and the barrel rack is fixed to the upper side surfaces of the two angle disks; the launching mechanism is fixed to the barrel rack by a plurality of track pads arranged along the length direction; the angle adjustment of the flipping mechanism is achieved by connecting the two groups of angle disk clamping shafts with different angle adjustment holes on the angle disk, thereby achieving the adjustment of the pitch and elevation launch angle of the launching mechanism.

[0024] A further technical solution of the present invention is: the center of the angle disk is the center of the front end flip axis, and an angle adjustment hole is opened every 2° on the large end face. From 0° to 20°, angle adjustment holes of 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 16°, 18°, and 20° are opened respectively, which can meet various initial pitch angle requirements of the experiment.

[0025] Beneficial Effects

[0026] The beneficial effects of the present invention are:

[0027] 1. The launch mechanism of the present invention innovatively designs and uses a boosting form of a pusher bullet. During the launch process, the high-pressure gas in the gas cylinder pushes the pusher bullet forward, and the pusher bullet pushes the front end of the mine body forward. The pusher bullet acts as a medium to indirectly apply the thrust of the high-pressure gas in the gas cylinder to the front end of the mine body, so that the high-altitude gliding torpedo that cannot be launched in the gun barrel can use the boosting effect of the pusher bullet. The front end guide rail of the gun barrel provides an acceleration stroke for it, and the boosting process is completed on the guide rail to obtain sufficient speed. The shortcomings of the traditional rotating body launch tube are overcome, and the difficulty that the mine body with a special shape cannot be accelerated in the launch tube is solved, thereby realizing the accelerated launch process of the mine body with a special shape with flying wings.

[0028] 2. The launch mechanism of the present invention creatively uses the design of the horizontal tail rail. The left and right horizontal tail rails are respectively connected to the four front and rear horizontal tail rail supports. The horizontal tail rail supports can adjust the height through the round head studs below, thereby adjusting the height of the left and right rails. The tail of the mine body is mounted on the rails on the left and right sides to ensure that the roll angle during the launch process remains stable and does not deflect. By adjusting the height of the rails on both sides, a height difference is generated between the left and right rails, so that the initial launch roll angle of the mine body can be accurately adjusted.

[0029] 3. The flipping mechanism of the present invention is designed with an angle disk, on which a plurality of openings arranged along an arc are opened. Through these openings, the launch tube can be flipped and fixed within the range of 0°-20° by using the angle disk clamping axis. The mine body can be fixed at different angles very accurately, so that the mine body can obtain different initial pitch angles when launched.

[0030] 4. The connection between the propulsion projectile and the mine body of the present invention adopts a magnetic connection, which utilizes the magnetic connection between the tail of the mine body and the magnet at the head of the propulsion projectile. This will not affect the separation of the mine body from the propulsion projectile during the flight after the acceleration process, and avoids the separation and collision between the mine body and the propulsion projectile during the acceleration process, thereby improving the acceleration effect and ensuring the accuracy of the experimental conditions.

[0031] 5. The upper edge of the guide rail at the front section of the gun barrel of the present invention exceeds the height of the center of mass of the mine body, so that the mine body is tightly stuck in the guide rail, so that the mine body will not fly off the track prematurely due to the reaction force during the launch process, thereby ensuring the stability of the trajectory during the launch process. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the overall structure;

[0033] Figure 2 It is a schematic diagram of the launching mechanism structure;

[0034] Figure 3 It is a schematic diagram of the structure of the propulsion projectile assembly;

[0035] Figure 4 1. It is a schematic diagram of the structure of the horizontal tail rail assembly;

[0036] Figure 5 Schematic diagram of the flipping mechanism structure;

[0037] Figure 6 It is a schematic diagram of the angle plate structure;

[0038] Figure 7 It is a schematic diagram of the supporting structure;

[0039] Description of the accompanying drawings: 1-gas cylinder inlet flange, 2-gas cylinder, 3-gas cylinder outlet flange, 4-gun barrel flange, 5-gun barrel, 6-track pad frame, 7-gun barrel frame, 8-propelling projectile assembly, 9-horizontal tail rail assembly, 10-propelling projectile tail section, 11-propelling rod, 12-guide flange, 13-sealing cap, 14-rear horizontal tail rail support, 15-front horizontal tail rail support, 16-horizontal tail rail-gun barrel connecting piece, 17-horizontal tail rail, 18-angle disk clamp seat, 19-angle disk clamp shaft, 20-angle disk, 21-turning shaft, 22-turning shaft bearing, 23-base frame, 24-track support frame, 25-track support rod, 26-track support frame base. DETAILED DESCRIPTION

[0040] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0041] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0042] Figure 1 It shows the overall structure diagram of a high-altitude gliding torpedo aerial flight experimental device. Figure 2 The schematic diagram of the launching mechanism is shown. Figure 3 The schematic diagram of the structure of the propulsion projectile assembly is shown. Figure 4 The schematic diagram of the structure of the horizontal tail rail assembly is shown. Figure 5 The schematic diagram of the flip mechanism is shown. Figure 6 The schematic diagram of the angle plate is shown. Figure 7 A schematic diagram of the support structure is shown.

[0043] Reference Figure 1 As shown, a high-altitude gliding torpedo aerial flight experimental device of the present invention includes a launching mechanism, a flipping mechanism, and a supporting structure. The launching mechanism provides power and track conditions for the torpedo body. The flipping mechanism can flip the launch tube within the range of 0°-20°. The supporting structure is divided into a base frame and a track support frame. The base frame serves as the mounting bearing body of the launch frame body and the remaining devices, and plays a role of fixing and bearing; the track support frame plays a role of bearing and supporting the front section of the gun barrel.

[0044] Since the experiment needs to achieve an aerial flight process, the experimental platform is built on a small building about 6 meters high next to the pool. The entire experimental device is fixed to the ground through a track support frame and a base frame. The rear barrel of the device is welded to the barrel frame through four track pads below, and the barrel frame is fixed to the base frame. The thrust projectile is installed in the barrel, and the front barrel is fixedly supported on the ground through a track support frame. The high-altitude gliding torpedo is placed in the front barrel guide rail, and the tail is connected to the thrust projectile head at the rear end through a magnet.

[0045] The launching mechanism comprises a gas cylinder inlet flange 1, a gas cylinder 2, a gas cylinder outlet flange 3, a barrel flange 4, a barrel 5, a track pad 6, a barrel rack 7, a pusher assembly 8, and a horizontal tail rail assembly 9. The gas cylinder outlet flange 3 and the gas cylinder inlet flange 1 are respectively welded to the two sides of the gas cylinder 2, and the gas cylinder outlet flange 3 is fixedly connected to the barrel flange 4 by bolts, and a sealing gasket is installed in the middle. During the launch preparation process, the pusher assembly 8 is installed in the barrel 5 by friction. The horizontal tail rail assembly 9 is fixedly connected to the front section of the barrel 5 by welding, four track pads 6 are welded to the rear section of the barrel 5, and the barrel rack 7 is welded below the four track pads 6, and the barrel rack 7 is fixedly connected to the flip shaft 21 through the bearing below. The upper edge of the guide rail track of the front section of the barrel 5 exceeds the center of mass height of the thunder body, so that the thunder body is tightly stuck in the guide rail, so that the thunder body will not fly off the track in advance due to the reaction force during the launch process, thereby ensuring the stability of the trajectory during the launch process.

[0046] The pusher assembly includes a pusher tail section 10, a push rod 11, a guide flange 12, and a sealing cap 13. The diameter of the pusher tail section 10 is comparable to that of the gun barrel 5, and can be stuck in the gun barrel 5 by friction. The guide flange 12 is welded before the center of mass of the push rod 11 to ensure that it is basically kept on the central axis of the gun barrel 5 during the firing process. The front sealing cap 13 is connected to the mine body through a magnet. In order to reduce the weight of the pusher, a hollow rod is selected as the main body of the pusher, and the sealing cap 13 can well seal the rod body and provide an installation position for the magnet.

[0047] The horizontal tail rail assembly includes a rear horizontal tail rail support 14, a front horizontal tail rail support 15, a horizontal tail rail-barrel connector 16, and a horizontal tail rail 17. The front horizontal tail rail support 15 and the rear horizontal tail rail support 14 are respectively connected to the round head studs by bolts, and the lower end of the round head stud is fixed to the horizontal tail rail-barrel connector 16, and the horizontal tail rail-barrel connector 16 is welded to the front section of the gun barrel 5. The two horizontal tail rails 17 are respectively connected to the front horizontal tail rail support 15 and the rear horizontal tail rail support 14. The tail of the mine body is mounted on the rails on the left and right sides to ensure that the roll angle during the launch process remains stable and does not deflect at an angle. By adjusting the height of the rails on both sides, a height difference is generated between the rails on the left and right sides, thereby adjusting the initial launch roll angle of the mine body.

[0048] The flip mechanism includes an angle disc holder 18, an angle disc holder shaft 19, an angle disc 20, a flip shaft 21, a flip shaft bearing 22, and a barrel rack 7. The flip shaft bearing 22 is fixedly connected to the base frame 23 by bolts, the flip shaft 21 is installed in the flip shaft bearing 22, and can rotate in the flip shaft bearing 22, the left and right angle discs 20 are connected to the flip shaft 21 through the front shaft hole, can rotate around the axis, and are fixedly connected to the barrel rack 7 by bolts, and the barrel rack 7 is connected to the flip shaft 21 through the bearing below, and can rotate around the flip shaft 21 together with the angle disc 20. The left and right angle disk holders 18 are welded to the base frame 23, and the angle disk clamping shaft 19 passes through the axial hole on the angle disk holder 18 and the opening on the angle disk 20 at the same time, so as to fix the angle disk 20 and the base frame 23. By rotating the flip axis 21 and the barrel rack 7 and passing the different openings on the angle disk 20 with the angle disk clamping shaft 19, the barrel 5 can be fixed at different initial elevation angles. There are 11 openings on the angle disk 20, and a hole is opened every 2° with the flip axis 21 as the center, from 0° to 20°, namely 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 16°, 18°, and 20°, which can meet the various initial elevation angle requirements of the experiment.

[0049] The support structure includes a base frame 23 and a track support frame 24. The track support frame 24 includes a track support rod 25 and a track support frame base 26. The track support rod 25 and the track support frame base 26 are fixedly connected by bolts. The track support rod 25 is in a "Y" shape, and the front section guide rail of the gun barrel 5 is mounted between two rods above the track support rod 25. The base frame 23 is fixedly connected to the ground by anchor bolts.

[0050] The installation and use process of the present invention will be described below in conjunction with the accompanying drawings.

[0051] According to the experimental requirements, the launcher is placed in the designated position, and the base frame 23 is fixed to the ground by anchor bolts. The propelling bomb assembly 8 is installed from the front end of the barrel 5 into the barrel 5, the barrel diameter is 110 mm, the magnet is adsorbed on the front end of the sealing cap 13, and then the head of the thunder body is stuck in the front section guide rail and the tail is connected to the designated position with the front end of the propelling bomb assembly 8 through the magnet.

[0052] Then, according to the initial launch elevation angle determined, the overall elevation angle of the gun barrel 5 is adjusted by the flip mechanism. After adjusting to the required position, the angle disc clamping shafts 19 on both sides are respectively inserted into the angle disc clamping seat 18 holes and the angle disc holes on both sides to fix the initial elevation angle. According to the initial launch roll angle determined, the thread depth of the ball stud on the horizontal tail rail 17 is adjusted to produce a height difference between the horizontal tail rails 17 on the left and right sides. After adjusting to a suitable angle, tighten the nut. The track support frame 24 is supported under the guide rail of the front section of the gun barrel 5. The air is compressed into the high-pressure gas cylinder 2 by an air pump.

[0053] At this point, the launch is ready. The electromagnetic valve is opened by controlling the electric signal, and the high-pressure air pushes the tail section of the pusher assembly 8, and the pusher starts to accelerate. The pusher is connected to the front magnet to push the mine body to start moving in the guide rail. Due to the guiding effect of the horizontal tail rail 17, the movement of the mine body on the guide rail always maintains the set initial roll angle. After the mine body flies out of the guide rail, the pusher also flies out and then separates from the mine body. After recording the relevant data, a high-altitude gliding torpedo aerial flight experiment is completed. Afterwards, the mine body and the pusher are recovered, and the next experiment only needs to repeat the previous related operations. This set of experimental equipment is well adapted to the appearance of the high-altitude gliding torpedo, and can meet the various working conditions that need to be experimentally verified. The experimental equipment is also relatively simple, so the device can be well used for the flight experiment of the high-altitude gliding torpedo.

[0054] In this embodiment, the length of the pusher projectile is about 2533mm. It is necessary to ensure that the acceleration stroke of the mine body is at least equal to the length of the pusher projectile. The front end length of the guide rail is designed to be about 2500mm, that is, the acceleration stroke of the mine body on the guide rail is about 2500mm. In this process, it is gradually accelerated to the target initial velocity of the experiment. After the mine body flies out of the guide rail, the pusher projectile also flies out, but due to the difference in their mass and flight dynamic characteristics, the pusher projectile will separate from the mine body.

[0055] The launch device is set on a small building about 6m high beside the comprehensive pool. The comprehensive pool is 70m long×44m wide×10~15m deep (10m deep water area is 29m wide, 15m deep water area is 15m wide). By calculating the diagonal of the pool, it is about 82m. Taking into account the safety and the success of landing in the pool, according to actual needs, a test gas cylinder with L=2.5m, V0=300L and an allowable pressure of P0=0~4.6MPa in the air pressure chamber is used. Theoretically, the air cannon system can accelerate the model to a maximum of 92.42m / s. The aircraft flight test needs to accelerate the model to 60m / s, and the required pressure is 2.1MPa. According to the free fall acceleration formula, the horizontal displacement when entering the water is about 66m, and the length of the air flight trajectory is about 66.3m, which meets the safety and success requirements.

[0056] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. An aerial flight test launch device for a gliding torpedo model, characterized in that: It includes a launching mechanism, a flipping mechanism, and a supporting structure. The launching mechanism is hinged to the supporting structure through the flipping mechanism, and the launching angle of the launching mechanism is adjusted by adjusting the fixed angle of the flipping mechanism. The launching mechanism comprises a power assembly, a propelling missile assembly and a horizontal tail rail, and the test mine body is arranged at the front end of the propelling missile; The power assembly drives the missile assembly to move in a straight line along a set trajectory, thereby pushing the test mine body to move in an accelerated manner along the horizontal tail rail until it flies out of the horizontal tail rail; The launching mechanism also includes a gun barrel, the power assembly is arranged at the end of the gun barrel, the propelling projectile assembly is located in the gun barrel, and the horizontal tail rail is coaxially arranged at the front end of the gun barrel; the front end of the propelling projectile assembly is connected to the tail end of the experimental mine body through a magnet, and the flying wings of the experimental mine body are placed on the two side rails of the horizontal tail rail; the power assembly drives the propelling projectile assembly to perform linear acceleration motion in the gun barrel; The gun barrel is welded to the gun barrel rack through four track pads arranged along the length direction, and the gun barrel rack is fixed to the flip mechanism; The power assembly includes a high-pressure gas cylinder, the inlet end of which is connected to an air pump via a flange, and air is compressed into the high-pressure gas cylinder by the air pump; the outlet end of the high-pressure gas cylinder is sealed and connected to the rear end of the gun barrel via a flange, and the high-pressure gas drives the propelling projectile assembly to accelerate the movement; The push projectile assembly comprises a push projectile tail section, a push rod, a guide flange and a sealing cap; the push projectile tail section is a disc structure, coaxially fixed to the tail end of the push rod, and its outer diameter is equivalent to the inner diameter of the gun barrel, and can be positioned in the gun barrel by friction in the absence of external force; the push rod is a hollow straight rod, the front end of which is sealed by a sealing cap, and a magnet is installed on the sealing cap; the guide flange is coaxially fixed to the push rod and is located before the center of mass of the push rod, so as to ensure that the push projectile assembly remains on the central axis of the gun barrel during the firing process; The front end of the lower half ring of the gun barrel extends forward in the extension direction to form a semicircular plate track; the horizontal tail guide rail includes two parallel straight rails, which are fixedly installed above the two side edges of the semicircular plate track through the rear horizontal tail guide rail support, the front horizontal tail guide rail support, and the horizontal tail guide rail-barrel connecting piece; the horizontal tail guide rail-barrel connecting piece is a flat plate with an arc-shaped notch on one side, and the arc-shaped notch is consistent with the outer peripheral profile of the semicircular plate track, and is used to support the semicircular plate track; the rear horizontal tail guide rail support and the front horizontal tail guide rail support are respectively arranged at the rear end and the front end of the semicircular plate track, and the upper ends thereof are connected to the two tracks of the horizontal tail guide rail, and the lower ends are connected to the two sides of the horizontal tail guide rail-barrel connecting piece through round head studs; the height adjustment of the tracks on both sides is achieved by adjusting the axial tightening of the round head studs, so that a height difference is generated between the left and right tracks, thereby adjusting the initial launch roll angle of the mine body; The edge of the semicircular arc plate track at the front section of the gun barrel is higher than the center of mass of the experimental mine body, so that the mine body can be stuck in the track, so that the mine body will not fly off the track prematurely due to the reaction force during the launch process, thereby ensuring the stability of the trajectory during the launch process; The support structure includes a base frame and a track support frame, the base frame is used to fix and support the flip mechanism and the launch mechanism, and the track support frame includes a track support rod and a track support frame base; the track support rod is a Y-shaped structure, the lower end of which is slidably connected to the track support frame base and can adjust the height in the vertical direction, and the upper end bifurcated structure is used to support the semicircular arc plate track of the front section of the gun barrel; The flip mechanism comprises an angle disk holder, an angle disk shaft, an angle disk, a flip shaft, a flip shaft bearing and a gun barrel rack, and the flip shaft bearing and the angle disk holder are respectively fixed to the front and rear ends of the supporting structure; the angle disk is a fan-shaped structure, and a through hole is opened on the small end face, which is hinged with the flip shaft bearing through the flip shaft, so that the angle disk can rotate around the flip shaft, and a plurality of through holes are evenly distributed on the large end face along the circumferential direction as angle adjustment holes; the large end of the angle disk is connected to the angle disk holder through the angle disk shaft; two groups of the flip mechanisms are symmetrically installed on both sides of the supporting structure, and the gun barrel rack is fixed on the upper side surfaces of the two angle disks; the launching mechanism is fixed to the gun barrel rack through a plurality of track pads arranged along the length direction; the angle adjustment of the flip mechanism is realized by connecting the two groups of angle disk shafts with different angle adjustment holes on the angle disk, and then the adjustment of the pitch launch angle of the launching mechanism is realized; The center of the angle disk is the center of the front end flip axis, and an angle adjustment hole is opened every 2° on the large end surface. From 0° to 20°, there are angle adjustment holes of 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 16°, 18°, and 20°, respectively, which can meet various initial pitch angle requirements of the experiment.

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