A high-speed parallel water entry test launch device and method for a spacecraft

Abstract

This invention discloses a high-speed parallel water entry experimental launching device and method for a vehicle, belonging to the field of hydrodynamic experiments. It includes a supporting base, a parallel controller, a parallel launching assembly, and a power unit. The parallel launching assembly is mounted on the supporting base via the parallel controller, and the power unit provides launching power and adjusts the water entry velocity. The parallel launching assembly includes a first launching device and a second launching device arranged side-by-side, enabling parallel launching of two projectiles and adjustment of the launching angle. The parallel controller includes a parallel control mechanism and a spacing adjustment mechanism. The parallel control mechanism ensures the relative parallelism of the first and second launching devices, while the spacing adjustment mechanism adjusts the launching distance between the first and second launching devices. This invention has a simple and practical structure, is easy to assemble, has high reliability and durability, and exhibits good repeatability and safety, providing experimental assurance for studying the hydrodynamic characteristics of structures at the moment of water entry.

Description

Technical Field

[0001] This invention belongs to the field of hydrodynamic experiments, specifically relating to a high-speed parallel water entry test launch device and method for a vehicle. Background Technology

[0002] In research on high-speed water entry, theoretical studies, numerical methods, and experimental studies are often employed. The entire process of a structure entering the water generally refers to the time from initial contact with the water at the top to complete wetting. During entry, the structure undergoes four stages: impact with water, flow formation, cavitation propagation, and complete wetting. Simultaneously, strong interactions occur between air, water, and the structure, accompanied by a series of complex physical phenomena. The water entry process is a transient, rapidly changing, and complex mechanical process, making theoretical analysis of certain entry phenomena quite difficult. Therefore, water entry experiments are an indispensable part of water entry research.

[0003] In practical applications, multiple torpedoes are often launched in quick succession to increase launch density, hit rate, and destructive power, thus overwhelming enemy defense systems in a short period. Therefore, designing water entry tests also requires studying the interactions between the torpedoes. The experimental setup requires the structure to enter the water at a specific speed and attitude, while simultaneously allowing for flexible control of the relative distance between the two torpedoes and adjusting the relative release time via a timing control device. This places high demands on the launching device. Therefore, there is an urgent need to design a high-speed parallel water entry experimental device capable of flexibly controlling the launch angle, launch spacing, and relative release time.

[0004] Among existing water entry test technologies, the prior art discloses an underwater parallel launching device. This device, based on a high-speed single-projectile launching device, is designed as a parallel launching device for multiple projectiles, used for parallel water entry tests of multiple projectiles. This device uses adjustable shims to control the distance between the two barrels, but the parallel distance adjustment capability is limited, it cannot continuously adjust the axial distance, and it cannot adapt to adjustments at longer distances. Furthermore, a mechanism for adjusting the water entry angle is not considered.

[0005] Existing technology also discloses a multi-vehicle parallel water entry experimental device, including a tripod, a launch device overall fixing frame, and a launch device. This experimental device can achieve water entry of different specifications of vehicles by changing the vehicle runways with different cross-sectional dimensions and the vehicles that match the runways. Using runways of different lengths can adjust the vehicle exit speed, and the launch can be achieved using a level and a tripod gimbal. The device involves tilting the launch vehicle into the water, and multiple vehicles within the same launch track can be launched synchronously or asynchronously using electromagnets. While the launch time is controlled by electromagnets and launch propulsion is provided by free fall, the launch speed is severely limited at certain altitudes. Therefore, this invention can only be used for conducting experiments on vehicle models in... Low-speed water entry experiments cannot achieve speeds higher than [the required speed]. High-speed water entry test. Summary of the Invention

[0006] The technical problem to be solved:

[0007] To overcome the shortcomings of existing technologies, this invention provides a high-speed parallel water entry test launch device and method for a spacecraft. It achieves a launch method powered by high-pressure gas through an air compressor, high-pressure gas cylinder, pressure gauge, and pressure regulating valve. The release control of the structure is achieved through a solenoid valve and a timing controller, thereby realizing higher speed and more precise launch control. It can conduct launch tests on spacecraft models at altitudes above [insert altitude here]. High-speed water entry experiments can be conducted to achieve The continuously adjustable distance between bullet diameters enables... The tilt angle of the water entry device is continuously adjustable, enabling continuously adjustable high-speed water entry. Simultaneously, a parallel controller is designed to control the lateral spacing and tilt angle, thereby achieving water entry effects under different working conditions.

[0008] The technical solution of the present invention is: a high-speed parallel water entry test launch device for a vehicle, comprising a support base, a parallel controller, a parallel launch assembly and a power unit, wherein the parallel launch assembly is mounted on the support base via the parallel controller, and the power unit provides launch power and adjusts the water entry speed;

[0009] The parallel launch assembly includes a first launch device and a second launch device arranged side by side, which can realize the parallel launch of two projectiles and the adjustment of the launch angle;

[0010] The parallel controller includes a parallel control mechanism and a spacing adjustment mechanism. The parallel control mechanism is used to ensure the relative parallelism of the first and second launching devices, and the spacing adjustment mechanism is used to adjust the launching spacing between the first and second launching devices.

[0011] A further technical solution of the present invention is as follows: the parallel controller further includes a parallel base frame, which is a frame structure with a top surface and a bottom surface parallel, and its bottom surface is fixed parallel to the support base frame; the spacing adjustment mechanism is installed in the extension direction of the head of the parallel base frame, and the connection length is adjusted by adjusting the installation position; the bottom of the parallel control mechanism is connected to the bottom of the parallel base frame, and the top is connected to the middle of the first launching device and the second launching device in sequence along the length direction;

[0012] The bottom of the first launching device is mounted on the spacing adjustment mechanism, and the bottom of the second launching device is mounted on the head of the parallel base frame. The spacing between the first launching device and the second launching device is adjusted by adjusting the connection length of the parallel base frame to achieve launching at different spacings.

[0013] A further technical solution of the present invention is: the parallel base frame is a cuboid frame structure, the long rectangular side of its top surface extends out of the cube, and two first vertical bearing seats are symmetrically installed; two threaded nut seats are installed on the bottom surface of the parallel base frame along the central axis.

[0014] A further technical solution of the present invention is: the spacing adjuster includes a widened angle steel, a crossbeam angle steel, a second vertical bearing seat, and a pad; the heads of the two widened angle steels are symmetrically installed at both ends of the crossbeam angle steel to form a U-shaped structure; the two second vertical bearing seats are respectively symmetrically installed on the two widened angle steels through the pads;

[0015] The widened angle steel has a slot along its length on its outer side, which is located between the second vertical bearing seat and the tail of the widened angle steel. The slots on the two widened angle steels are bolted to the two slots on the two extended sides of the parallel base frame. The distance between the two launching devices can be adjusted by changing the relative position of the bolts on the slots.

[0016] A further technical solution of the present invention is as follows: the parallel control mechanism includes two slotted connecting rods, two wide threaded nuts, two parallel connecting rods, a movable parallel sleeve, a fixed parallel sleeve, a lead screw, a guide rod, a threaded nut, a through-hole shaft, and a handwheel; the lead screw and the guide rod are arranged side by side and axially parallel; the two parallel connecting rods are symmetrically arranged, one end of which is slidably connected to the lead screw near the top end through the movable parallel sleeve, and the other end is fixedly connected to the guide rod near the top end through the fixed parallel sleeve; the lead screw has an external thread in the middle, which connects to the guide rod near the head of the parallel base frame through the threaded nut. The female connector has a handwheel at its bottom. Rotating the handwheel causes the lead screw to rotate relative to the lead screw nut and move axially. The middle part of the guide rod is connected to the lead screw nut seat away from the head of the parallel base frame through a through-hole shaft. It moves with the lead screw through two parallel connecting rods and slides along the through-hole shaft. The tops of the lead screw and the guide rod are respectively installed between the rear parts of two parallel slotted connecting rods through wide lead screw nuts. The axial distance between the two wide lead screw nuts is equal to the axial distance between the movable parallel sleeve and the fixed parallel sleeve, ensuring that the two slotted connecting rods remain parallel to the ground no matter what movement they make.

[0017] A further technical solution of the present invention is: the front part of the slotted connecting rod has a second slot along the length direction, and a through hole is opened behind the second slot. The second slot and the through hole are respectively used to connect the first launching device and the second launching device.

[0018] A further technical solution of the present invention is as follows: the first launching device includes a gas storage tank, a pressure gauge, a solenoid valve, a launching tube, a launching frame, an upper pin, a lower pin, a barrel fixing frame, a plug, a magnet, and a launching structure; the launching tube is fixed on the launching frame, the radial displacement is limited by the barrel fixing frame, and the axial displacement is limited by the launching tube latch installed radially at the tail end of the launching tube; two upper pins are symmetrically installed on both sides of the middle part of the launching frame, respectively inserted into the second slots of two slotted connecting rods, and can slide along the length direction of the second slot; two lower pins are symmetrically installed on both sides of the lower part of the launching frame, respectively rotatably connected to two second vertical bearing seats;

[0019] The gas storage tank is installed on the top of the launcher, and a pressure gauge is installed on it. It is connected to the power unit through a gas supply pipeline, and is connected to the tail end of the launch tube through a solenoid valve, a gas supply pipeline, and a plug. A magnet is installed inside the plug, which attracts the armature at the end of the launch structure to ensure that the launch structure will not slip when the launch tube is tilted or vertical.

[0020] A further technical solution of the present invention is: the second launching device has the same structure as the first launching device, and its two upper pins are respectively inserted into the through holes behind the second slots of the two slotted connecting rods; the two lower pins are respectively rotatably connected to the two first vertical bearing seats.

[0021] It also includes an angle plate, one edge of which is fixed to the outside of the launcher. An arc-shaped groove is opened on the end face along the arc direction. It is installed in conjunction with a locking block installed on the extended side of the parallel base frame to fix the angle of the launcher.

[0022] A further technical solution of the present invention is: the power device includes a three-way valve, a pressure regulating valve and an air compressor. The air compressor is connected to the gas storage tanks of the first launching device and the second launching device through the air supply pipeline, the pressure regulating valve and the three-way valve. The air compressor is used to provide high-pressure gas. The high-pressure gas introduced into the gas storage tank enters the launching tube through the solenoid valve, the air supply pipeline and the plug in sequence to launch the launching structure.

[0023] A method for launching a high-speed parallel water-entry experimental launch device for a vehicle, comprising the following specific steps:

[0024] Step 1: Push the launching structure into the launching tube using a long rod, and fix the launching structure inside the launching tube using the magnet of the plug;

[0025] Step 2: Rotate the handwheel according to the required launch angle under the working conditions. The lead screw adjusts the position of the slot connecting rod through axial displacement. At the same time, after accurately determining the launch angle using a protractor and angle plate, fix the angle plate to the locking block to complete the launch angle fixing.

[0026] Step 3: Adjust the installation position of the spacing adjustment mechanism and the parallel base frame according to the required launch distance under the working conditions, and lock them in place after confirmation to complete the launch spacing fixing;

[0027] Step 4: Based on the required launch speed under the working conditions, start the air compressor to supply air to the air tank, adjust the pressure regulating valve to control the pressure of the gas flowing into the air tank, and when the gas pressure in the air tank reaches the set value of the pressure regulating valve, the gas stops flowing into the air tank. The pressure value of the high-pressure gas in the air tank is determined in real time by the pressure gauge to complete the fixation of the launch speed.

[0028] Step 5: The solenoid valve is initially in the closed state, and is opened momentarily after the switch is pressed; the high-pressure gas in the gas storage tank enters the launch tube 30 through the solenoid valve, the gas supply line, and the plug in sequence to complete the launch operation;

[0029] Repeat steps 2-5 above, changing the launch angle by adjusting the rotation of the handwheel, changing the parallel launch spacing by controlling the installation position of the spacing adjustment mechanism and the parallel base frame, and changing the launch speed by controlling the gas pressure in the gas tank.

[0030] Beneficial effects

[0031] The beneficial effects of this invention are as follows:

[0032] 1. By using a parallel controller, the two independent gun barrels are aligned in orientation and height, enabling the parallel firing of two projectiles; the two gun barrels are independent of each other and can be controlled separately to achieve asynchronous firing.

[0033] 2. The parallel control mechanism, along with the slots and bolts on the angle dial, allows for continuous adjustment of both the spacing and angle. Adding threads to the lead screw further facilitates angle adjustment, thus meeting the launch requirements of the aircraft for different spacing and angle conditions.

[0034] 3. The ground-based support frame makes the launch more stable and can support launches at higher speeds.

[0035] 4. Higher launch speeds can be achieved through air compressors, air tanks, pressure regulating valves, and pressure gauges. The speed at which the structure enters the water can be adjusted according to specific needs.

[0036] 5. The system is simple and practical, easy to build, highly reliable and durable, and has good repeatability and safety, providing experimental support for studying the hydrodynamic characteristics of structures at the moment of water immersion. Attached Figure Description

[0037] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0038] Figure 2 This is a front view of the overall structure of the present invention;

[0039] Figure 3 This is a schematic diagram of the support base of the present invention;

[0040] Figure 4 This is a schematic diagram of the parallel controller of the present invention;

[0041] Figure 5 This is a partial schematic diagram of the parallel controller (parallel base frame);

[0042] Figure 6 This is a partial schematic diagram of a parallel controller (parallel control mechanism);

[0043] Figure 7 This is a partial schematic diagram of the parallel controller (pitch adjustment mechanism);

[0044] Figure 8 This is a schematic diagram of the launching device of the present invention;

[0045] Figure 9 This is a partial structural diagram of the launching device of the present invention;

[0046] Figure 10 This is a partial structural cross-sectional view of the firing device of the present invention;

[0047] Figure 11 This is a schematic diagram of the power unit of the present invention;

[0048] Explanation of reference numerals in the attached drawings: 1—Supporting base frame, 2—Parallel controller, 3—First launching device (without angle disc), 4—Second launching device (with angle disc), 5—Power unit, 6—Parallel base frame, 7—Parallel control mechanism, 8—Gap adjustment mechanism, 9—Angle steel, 10—Vertical bearing seat, 11—Locking block, 12—Threaded nut seat, 13—Support screw, 14—Wide threaded nut, 15—Slotted connecting rod, 16—Parallel connecting rod, 17—Modible parallel sleeve, 18—Fixed parallel sleeve, 19—Handwheel, 20—Lead screw, 21—Smooth rod, 22—... 23 - Nut, 24 - Through-hole shaft, 25 - Vertical bearing seat, 26 - Widened angle steel, 27 - Crossbeam angle steel, 28 - Pad block, 29 - Upper pin, 30 - Launching rack, 31 - Launch tube, 32 - Angle disc, 33 - Lower pin, 34 - Barrel mounting bracket, 35 - Gas tank, 36 - Solenoid valve, 37 - Launching tube latch, 38 - Pressure gauge, 39 - Plug, 40 - Launching structure, 41 - Three-way valve, 42 - Pressure regulating valve, 43 - Gas supply line, 44 - Air compressor, 45 - Gas supply line. Detailed Implementation

[0049] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the invention, and should not be construed as limiting the invention.

[0050] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0051] Launch velocity of the structure and pressure at the bottom of the structure and the length of the launch tube Closely related. According to the theory in "Strong Impact Testing and Measurement Technology", the muzzle velocity of the projectile... Given by Formula 1:

[0052] (1)

[0053] in, This represents the cross-sectional area of ​​the gun barrel;

[0054] Mass of the structure;

[0055] It is the initial pressure of the pressure chamber;

[0056] It is the volume of the pressure chamber;

[0057] It is the specific heat ratio, or adiabatic index, for air medium. ;

[0058] This is a virtual quality coefficient, which needs to be determined through experimental debugging.

[0059] The structural mass used in this embodiment ,diameter ; Launch tube length Initial pressure of the pressure chamber Air pressure chamber volume Substituting into Formula 1, the muzzle velocity of the projectile can be calculated. Approximately .

[0060] In this application, "high-speed" in high-speed launch refers to... The specific speed is calculated based on the gas pressure entering the high-pressure chamber; and the launching device of this application can also achieve a lower speed launch.

[0061] This embodiment discloses a launching device for realizing a high-speed parallel water entry experiment of a vehicle, including a structural launching device and a parallel adjustable launching frame. The structural launching device includes an air compressor, an air supply pipeline, a pressure regulating valve, an air tank, a pressure gauge, a solenoid valve, a launching tube, and a base frame; the parallel adjustable launching frame includes a supporting base frame and a parallel controller. The structural launching device utilizes the air compressor to collect high-pressure gas from the air tank, uses the pressure gauge to precisely control the pressure inside the air tank, and uses the control solenoid valve to inject an appropriate amount of high-pressure gas into the launching tube, thereby enabling the structure to achieve a high-speed water entry experiment exceeding... Furthermore, the muzzle velocity is precisely adjustable. In the parallel adjustable launcher, the parallel control mechanism ensures the relative parallelism between the slide and the ground through a connecting rod, thereby keeping the two launchers constrained within the slide relatively parallel. Utilizing the adjustable constraint between the slot and the bolt on the spacing adjustment mechanism, the relative distance between the launchers is continuously adjustable. The adjustable distance is approximately the distance between the slot length and the bolt hole. The distance between the projectile diameters is twice that of the projectiles; by utilizing an angle disc mounted on the launching device, the angle between the launcher and the ground can be continuously adjusted, with the angle disc slot having a pre-reserved angle of [missing information]. This angle is an adjustable angle for the tilting water inlet angle; by using the cooperation of the lead screw and lead nut to adjust the angle by rotation, the angle control can be more precise.

[0062] The present invention includes a parallel controller and a pair of structure launching devices; the parallel controller includes a parallel base frame, a parallel control mechanism and a spacing adjustment mechanism; the pair of structure launching devices are kept relatively parallel and have equal launching heights through the parallel control mechanism, the launching spacing can be adjusted through the slots of the parallel control mechanism and the spacing adjustment mechanism, and the launching angle can be adjusted through the angle disk on the structure launching device.

[0063] like Figures 1-11 As shown, a high-speed parallel water entry test launch device for a vehicle includes a support base 1, a parallel controller 2, a launch device 3, a launch device 4, and a power unit 5. The parallel controller 2 is interconnected with the support base 1 and the parallel base 6 via bolt holes at their bottoms. The bottom ends of the first launch device 3 and the second launch device 4 are respectively mounted on the spacing adjustment mechanism 8 of the parallel controller 2 and the parallel base 6, and their middle parts are connected to the parallel control mechanism 7 of the parallel controller 2. The power unit 5 is connected to the air storage tanks 34 of the first launch device 3 and the second launch device 4 via three-way valves 41.

[0064] Reference Figure 4 , 5As shown in Figure 6, the parallel controller 2 includes a parallel base frame 6, a parallel control mechanism 7, and a spacing adjustment mechanism 8. The parallel base frame 6 is a cuboid frame structure, with its bottom surface fixed parallel to the supporting base frame. The spacing adjustment mechanism is installed in the extension direction of the head of the parallel base frame, and the connection length is adjusted by adjusting the installation position. The bottom of the parallel control mechanism is connected to the bottom of the parallel base frame, and the top is connected to the middle of the first launching device and the second launching device in sequence along the length direction. The long rectangular side of the top surface of the parallel base frame 6 extends out of the cube, and two first vertical bearing seats 10 are symmetrically installed thereon. Two threaded nut seats 12 are installed on the bottom surface along the central axis.

[0065] The spacing adjuster 8 includes a widened angle steel 25, a crossbeam angle steel 26, a second vertical bearing seat 24, and a pad 27. The heads of the two widened angle steels 25 are symmetrically installed at both ends of the crossbeam angle steel 26, forming a U-shaped structure. The two second vertical bearing seats 24 are symmetrically installed on the two widened angle steels 25 via the pad 27. The pad 27 is welded to the widened angle steel 25, and the widened angle steel 25 is welded to the crossbeam angle steel 26. The pad 27 has threaded holes for connection to the vertical bearing seats via screws. The height of the pad 27 should ensure that the vertical bearing seats 24 on the spacing adjustment mechanism 8 and the vertical bearing seats 10 on the parallel base frame 6 are at the same height. The short face of the widened angle steel 15 has a slot for connection to the parallel base frame 6 via bolts. The slot on the widened angle steel 15 is bolted to the two slots on the angle steel 9 in the parallel base frame 6. By changing the relative position of the bolts on the slots, the spacing of the launching device is adjusted to achieve different spacings of launching. The parallel control mechanism 7 is connected to the nut seat 12 on the parallel base frame 6 via the nut 22 on the lead screw 20 and the guide rod 21 and the through shaft 23, and is fixed by the support screw 13.

[0066] The parallel control mechanism 7 includes two slotted connecting rods 15, two wide threaded nuts 14, two parallel connecting rods 16, a movable parallel sleeve 17, a fixed parallel sleeve 18, a lead screw 20 and a guide rod 21, a threaded nut 22 and a through-hole shaft 23, and a handwheel 19. The handwheel 19 is fixed without rotation to the lower part of the lead screw 20. The lead screw 20 and the threaded nut 22 are connected by threads. The movable parallel sleeve 17 is loosely fitted onto the lead screw 20. The through-hole shaft 23 is loosely fitted onto the guide rod 21. The fixed parallel sleeve 18 is fixed through a through hole in the guide rod 23. The two parallel connecting rods 16 are fixed to the protrusions on the flat sleeve by cap nuts. The lead screw 20 and the guide rod 21 are respectively fixed to the slotted connecting rods 15 by the wide threaded nuts 14. The distance between the axes of the two wide threaded nuts 14 should be equal to the distance between the axes of the protrusions of the movable parallel sleeve 17 and the fixed parallel sleeve 18. The slotted connecting rod 15 has a second slot along its length at its front end, and a through hole behind the second slot. The second slot and the through hole are used to connect the first launching device and the second launching device, respectively. The parallel control mechanism 7 ensures that the slotted connecting rod 15 remains parallel to the ground regardless of its movement.

[0067] The first launching device 3 includes a gas tank 34, a pressure gauge 37, a solenoid valve 35, a gas supply line 45, a launching tube 30, a launching frame 29, four pins 28 and 32, four barrel fixing brackets 33, a plug 38, a magnet 39, and a launching structure 40. The gas tank 34 and the launching tube 30 are fixed on the launching frame 29. The launching tube 30 and the launching frame 29 are fixed to move radially through the four barrel fixing brackets 33, and the axial movement is controlled by the connection between the thread and the nut of the launching tube lock 36 on the launching tube 30. The four pins 41 are all connected to the launching frame 29 by welding. The second launching device 4 has the same structure as the first launching device 3, except that the angle plate 31 is bolted to the launching frame 29. The angle plate 31 is provided with an arc-shaped groove for fixing the angle of the launching frame 29.

[0068] The launching device 3 is connected to the vertical bearing seat 24 on the spacing adjustment mechanism 8 via the lower pin 32, and the launching device 3 is connected to the slot on the slotted connecting rod 15 in the parallel control mechanism 7 via the upper pin 28; the launching device 4 is connected to the vertical bearing seat 10 on the parallel base frame 6 via the lower pin 32, and the launching device 4 is fixed to the slot on the slotted connecting rod 15 in the parallel control mechanism 7 via the upper pin 28.

[0069] Air compressor 44 is connected to the air storage tank 34 of launching devices 3 and 4 via air supply line 43 and pressure regulating valve 42 using a three-way valve 41. The function of air compressor 44 is to provide the necessary high-pressure gas to the launching devices and to supply gas to air storage tank 34 via air supply line 45 and pressure regulating valve 42. Pressure regulating valve 42 is used to regulate the pressure of the gas flowing into air storage tank 34. Pressure regulating valve 42 is a one-way valve, and solenoid valve 35 is a normally closed valve, thus sealing the high-pressure gas entering air storage tank 34 inside the tank. When the gas pressure inside air storage tank 34 reaches the set value of pressure regulating valve 42, gas flow into air storage tank 34 stops. Pressure gauge 37 is fixed to air storage tank 34 and displays the pressure value of the high-pressure gas inside air storage tank 34 in real time. The gas storage tank 34 is connected to the launch tube 30 via a solenoid valve 35, a vent pipe 45, a plug 38, and a solenoid tube 30. The plug 38 is connected to the launch tube 30 via threads. When the solenoid valve 35 is closed, the plug 38 is hollow. When the switch is pressed, the solenoid valve 35 opens, and the high-pressure gas in the gas storage tank 34 enters the launch tube 30 sequentially through the solenoid valve 35, the vent pipe 45, and the plug 38. A magnet 39 is attached to the other end of the plug 38, and an armature is fixed to the end of the structure 40 with screws. The magnet 39 fixes the structure 40 by attracting the armature, ensuring that the structure 40 will not slip even if the launch tube 30 is tilted or even vertical.

[0070] The specific implementation method is as follows:

[0071] Installation process:

[0072] Step 1: Place the support base 1 on the ground and connect it to the parallel base 6 with bolts. Simultaneously, connect the locking block 11 and the screw nut seat 12 to the support base 6 with bolts. Do not install the vertical bearing seat 10 yet. Step 2: Fix the spacing adjustment mechanism 8 to the reserved bolt holes of the parallel base 6 through the slot with bolts. Do not install the vertical bearing seat 24 yet. Step 3: Fix the parallel control mechanism 7 to the two screw nuts 12 on the parallel base 6 through the screw nut 22 and the through-hole shaft 23 with support screws 13 respectively. Do not install the slot connecting rod 15 yet. Step 4: First, fix the angle plate 31 to one of the launchers 29 with bolts. Then connect the pins (lower part) 32 on both launchers 29 to the vertical bearing seat 10 and the vertical bearing seat 24. Place the pins (upper part) 28 in the slot and groove of the slot connecting rod 15. Both the pins (upper part) 28 and the pins (lower part) 32 are... The vertical bearing housing 10 and 24 are fixed to the pad 27 and parallel base frame 6 respectively with screws and bolts. The two slotted connecting rods 15 are connected to the lead screw 20 and the wide thread nut 14 of the smooth rod 21 respectively with screws. The eight gun barrel fixing brackets 33 are fixed to the launcher 29 respectively, and the launch tube locking buckle 36 behind the launch tube 30 is aligned with the slot reserved on the upper part of the launcher 29 and pushed into the launcher 29, and fixed with nuts. The air tank 34 is connected to the solenoid valve 35 and pressure gauge 37, and then fixed to the launcher 29, and connected to the plug 38 on the launch tube 30 through the air supply line 45. The air compressor 44 is connected to the air tank 34 through the air supply line 43 and the three-way valve 41. At this time, the high-speed parallel water entry test launch device of the vehicle is installed.

[0073] Usage process:

[0074] First, push the structure 40 into the launch tube 30 using a long rod. Secure the structure inside the launch tube using a magnet 39 attached to the other end of the plug 38 and an armature fixed to the end of the structure 40 with screws. The structure is now fixed. Second, rotate the handwheel 19 according to the required launch angle. Control the position of the slot connecting rod 15 using the threads on the lead screw 20 and nut 22. Precisely determine the launch angle using a protractor with a magnet and angle disc 31. Then, tighten the angle disc 31 and locking block 11 with bolts and nuts. The launch angle is now fixed. Third, adjust the distance between the spacing adjustment mechanism 8 and the parallel base frame 6 according to the required launch distance. Loosen the bolts at the front of the angle steel 9 to allow the spacing adjustment mechanism 8 to move horizontally along the slot. After adjusting and determining the spacing, the bolts here should be locked, and the launch spacing is now fixed. Fourth, according to the launch speed required by the working conditions, start the air compressor 44 to supply air to the air tank 34, and adjust the pressure regulating valve 42 to control the pressure of the gas flowing into the air tank 34. When the gas pressure in the air tank 34 reaches the set value of the pressure regulating valve 42, the gas stops flowing into the air tank 34. The pressure value of the high-pressure gas in the air tank 34 is determined in real time by the pressure gauge 37, and the launch speed is now fixed. Fifth, the solenoid valve 35 is initially closed. When the switch is pressed, the solenoid valve 35 is opened, and the high-pressure gas in the air tank 34 enters the launch tube 30 through the solenoid valve 35, the air supply pipe 45 and the plug 38 in sequence. At this time, the launch operation is completed.

[0075] Repeat the above test; the launch angle can be changed by controlling the rotation of handwheel 19; the parallel launch spacing can be changed by controlling the distance between spacing adjustment mechanism 8 and parallel base frame 6; and the launch speed can be changed by controlling the air pressure in gas tank 34.

[0076] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A high-speed parallel water entry test launch device for a spacecraft, characterized in that: It includes a support base, a parallel controller, a parallel launch assembly, and a power unit. The parallel launch assembly is mounted on the support base via the parallel controller, and the power unit provides launch power and adjusts the water entry speed. The parallel launch assembly includes a first launch device and a second launch device arranged side by side, which can realize the parallel launch of two projectiles and the adjustment of the launch angle; The parallel controller includes a parallel control mechanism and a spacing adjustment mechanism. The parallel control mechanism is used to ensure the relative parallelism of the first and second launching devices, and the spacing adjustment mechanism is used to adjust the launching distance between the first and second launching devices. The parallel controller also includes a parallel base frame, which is a frame structure with a parallel top and bottom surface, and its bottom surface is fixed parallel to the support base frame; the spacing adjustment mechanism is installed in the extension direction of the head of the parallel base frame, and the connection length is adjusted by adjusting the installation position; the bottom of the parallel control mechanism is connected to the bottom of the parallel base frame, and the top is connected to the middle of the first launching device and the second launching device in sequence along the length direction; The bottom of the first launching device is mounted on the spacing adjustment mechanism, and the bottom of the second launching device is mounted on the head of the parallel base frame. The spacing between the first launching device and the second launching device is adjusted by adjusting the connection length of the parallel base frame to achieve launching at different spacings. The parallel base frame is a cuboid frame structure, with the long rectangular side of its top surface extending out of the cube, where two first vertical bearing seats are symmetrically installed; two threaded nut seats are installed on the bottom surface of the parallel base frame along the central axis. The spacing adjuster includes a widened angle steel, a crossbeam angle steel, a second vertical bearing seat, and a pad; the heads of the two widened angle steels are symmetrically installed at both ends of the crossbeam angle steel to form a U-shaped structure; the two second vertical bearing seats are symmetrically installed on the two widened angle steels respectively through the pads; The widened angle steel has a slot along its length on its outer side, which is located between the second vertical bearing seat and the tail of the widened angle steel. The slots on the two widened angle steels are connected to the two slots on the two extended sides of the parallel base frame by bolts. The distance between the two launching devices can be adjusted by changing the relative position of the bolts on the slots. The parallel control mechanism includes two slotted connecting rods, two wide threaded nuts, two parallel connecting rods, a movable parallel sleeve, a fixed parallel sleeve, a lead screw, a guide rod, a threaded nut, a through-hole shaft, and a handwheel. The lead screw and guide rod are arranged side by side and axially parallel. The two parallel connecting rods are symmetrically arranged, with one end slidably connected to the lead screw near its top end via the movable parallel sleeve, and the other end fixedly connected to the guide rod near its top end via the fixed parallel sleeve. The lead screw has an external thread in its middle section, which connects to a threaded nut seat near the head of the parallel base frame via a threaded nut. A handwheel is installed at the bottom. Rotating the handwheel causes the lead screw to rotate relative to the lead nut and move axially. The middle part of the guide rod is connected to the lead nut seat away from the head of the parallel base frame through a through-hole shaft. It moves with the lead screw through two parallel connecting rods and slides along the through-hole shaft. The tops of the lead screw and the guide rod are respectively installed between the rear parts of two parallel slot connecting rods through wide lead nuts. The axial distance between the two wide lead nuts is equal to the axial distance between the movable parallel sleeve and the fixed parallel sleeve, ensuring that the two slot connecting rods remain parallel to the ground no matter what movement they make. The front part of the slotted connecting rod has a second slot along its length, and a through hole is opened behind the second slot. The second slot and the through hole are used to connect the first launching device and the second launching device, respectively.

2. The high-speed parallel water entry test launch device for a vehicle according to claim 1, characterized in that: The first launching device includes a gas tank, a pressure gauge, a solenoid valve, a launching tube, a launching frame, an upper pin, a lower pin, a barrel fixing bracket, a plug, a magnet, and a launching structure. The launching tube is fixed to the launching frame, with radial displacement limited by the barrel fixing bracket and axial displacement limited by a launching tube latch installed radially at the tail end of the launching tube. Two upper pins are symmetrically installed on both sides of the middle part of the launching frame and are respectively inserted into the second slots of two slotted connecting rods, allowing them to slide along the length of the second slot. Two lower pins are symmetrically installed on both sides of the lower part of the launching frame and are rotatably connected to two second vertical bearing seats. The gas storage tank is installed on the top of the launcher, and a pressure gauge is installed on it. It is connected to the power unit through a gas supply pipeline, and is connected to the tail end of the launch tube through a solenoid valve, a gas supply pipeline, and a plug. A magnet is installed inside the plug, which attracts the armature at the end of the launch structure to ensure that the launch structure will not slip when the launch tube is tilted or vertical.

3. The high-speed parallel water entry test launch device for a spacecraft according to claim 2, characterized in that: The second launching device has the same structure as the first launching device, with its two upper pins respectively inserted into the through holes behind the second slots of the two slotted connecting rods; and its two lower pins respectively rotatably connected to the two first vertical bearing seats. It also includes an angle plate, one edge of which is fixed to the outside of the launcher. An arc-shaped groove is opened on the end face along the arc direction. It is installed in conjunction with a locking block installed on the extended side of the parallel base frame to fix the angle of the launcher.

4. The high-speed parallel water entry test launch device for a vehicle according to claim 3, characterized in that: The power unit includes a three-way valve, a pressure regulating valve, and an air compressor. The air compressor is connected to the gas storage tanks of the first and second launching devices through the air supply pipeline, the pressure regulating valve, and the three-way valve. The air compressor is used to provide high-pressure gas. The high-pressure gas introduced into the gas storage tank passes through the solenoid valve, the air supply pipeline, and the plug in sequence to enter the launching tube and launch the launching structure.

5. A launching method for a high-speed parallel water-entry experimental launching device for a vehicle as described in any one of claims 1-4, characterized in that... The specific steps are as follows: Step 1: Push the launching structure into the launching tube using a long rod, and fix the launching structure inside the launching tube using the magnet of the plug; Step 2: Rotate the handwheel according to the required launch angle under the working conditions. The lead screw adjusts the position of the slot connecting rod through axial displacement. At the same time, after accurately determining the launch angle using a protractor and angle plate, fix the angle plate to the locking block to complete the launch angle fixing. Step 3: Adjust the installation position of the spacing adjustment mechanism and the parallel base frame according to the required launch distance under the working conditions, and lock them in place after confirmation to complete the launch spacing fixing; Step 4: Based on the required launch speed under the working conditions, start the air compressor to supply air to the air tank, adjust the pressure regulating valve to control the pressure of the gas flowing into the air tank, and when the gas pressure in the air tank reaches the set value of the pressure regulating valve, the gas stops flowing into the air tank. The pressure value of the high-pressure gas in the air tank is determined in real time by the pressure gauge to complete the fixation of the launch speed. Step 5: The solenoid valve is initially in the closed state, and is opened momentarily after the switch is pressed; the high-pressure gas in the gas storage tank enters the launching tube through the solenoid valve, the gas supply line, and the plug in sequence to complete the launching operation; Repeat steps 2-5 above, changing the launch angle by adjusting the rotation of the handwheel, changing the parallel launch spacing by controlling the installation position of the spacing adjustment mechanism and the parallel base frame, and changing the launch speed by controlling the gas pressure in the gas tank.

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