Vehicle-mounted box type rodless cylinder ejection device

Abstract

The invention discloses a vehicle-mounted box type rodless ejection device, and belongs to the field of spaceflight equipment ejection. The device comprises a launching box, a left cylinder, a right cylinder, a tray, an upper guide rail, a lower guide rail, two groups of sliding blocks, an aircraft and a gas cylinder. The launching box is a square launching box, multiple sections of square reinforcing ribs are distributed on the outer side of the launching box, and the launching box wraps the internal aircraft, the air cylinder, the guide rail sliding block and other components to isolate the external environment. The air cylinder structure comprises an external reinforcing frame, a cylinder barrel, a buffering device, a pressure relief hole and an air inlet. The tray comprises a tray main body for lifting the aircraft in the middle, a piston, a sealing ring, a sealing steel belt and a power output arm. The lower guide rail downwards extends out of the launching box body to be combined with the erecting bracket, and is fixedly connected with the frame through the front end locking device, so that the overall strength of the frame is improved. Compressed air is selected as an ejection medium. The device has the characteristics of box-type launch aircraft protection, quick response and convenience in maintenance, and also has the advantages of long effective stroke, good compatibility and adaptability and low thermal protection requirement of rodless launch.

Description

Technical Field

[0001] The present invention belongs to the field of ejection of aerospace equipment, and relates to a vehicle-mounted box-type rodless cylinder ejection device. Technical Background

[0002] With the trend of war towards informatization and systemization, there is an increasing demand for launching one's own weapons without being detected and destroyed by the enemy, that is, to improve the rapidity, stability, concealment of the weapon launching process and the reusable times of the launching device. At present, the launching methods of guided vehicles are divided into self-launching, cold ejection, dropping and combined launching, etc., among which self-launching and cold ejection are the most common. The self-launching technology is relatively mature, widely used, simple in structure and high in reliability. However, the high-temperature and high-speed exhaust jet generated during its launch may cause harm to the launching device and the surrounding personnel, and a flow guiding device needs to be configured, so it is not suitable for vehicle-mounted mobile warfare. Relatively speaking, cold ejection has the characteristics of good adaptability to the launch environment and equipment, strong concealment, etc., is friendly to mobile warfare, and has gradually become one of the main methods of vehicle-mounted mobile launch. Common cold ejection methods include gas ejection, gas-steam ejection, compressed gas ejection, etc. Electromagnetic ejection, gas-liquid phase change ejection, and rodless cylinder ejection have also gradually become research directions.

[0003] As an ejection device, the rodless cylinder has the advantages of strong versatility, rapid response and good guarantee. Compared with the traditional gas ejection that generates high-temperature and high-pressure gas and requires the design of a sealing device to prevent leakage, the rodless ejection reduces the design requirements for the thermal protection and pressure bearing of the launching device. Compared with the traditional rod cylinder, the rodless cylinder only has a transmission piston and no rigid piston rod in its structure, which makes the cylinder length of the ejection device slightly larger than the stroke of the piston, and has the characteristics of compact structure and long effective stroke. As an ejection power, the rodless cylinder can effectively shorten the axial space of the launching device and improve the flexible and mobile combat ability of the launching platform.

[0004] The absence of a rigid piston rod inside allows the rodless open cylinder to drive throughout the entire stroke without the problem of buckling. In combination with the design of the drive slider and the open cylinder, the rodless open cylinder can achieve linear and reciprocating motions at high speeds with large loads, making it very suitable for driving large-mass and large-volume objects at high speeds. It can be widely applied in fields such as industrial automation, aerospace, shipbuilding, and weaponry. Currently, a typical military application of rodless cylinders abroad is the steam catapult on aircraft carriers. For example, the C-13-1 and C-13-2 steam catapults in the United States use a set of symmetrically arranged rodless open cylinders to achieve high-speed and heavy-load catapulting of carrier-based aircraft with compressed steam as the power. However, different from its application in catapulting carrier-based aircraft, there is less research on applying rodless cylinder catapults to vehicle-mounted catapults. On the one hand, because catapulting large loads requires a large amount of compressed air, the required volume of the air storage tank is large and not convenient for vehicles to carry. On the other hand, different from carrier-based aircraft where only the catapulting process is actuated by rodless cylinders and other devices are relied on for daily transportation and maintenance, etc., most of the processes such as storage, transportation, and launch of vehicle-mounted guided vehicles need to be carried out on the vehicle. The common choice is to achieve these processes through box-type launch, and it is necessary to consider how to combine the rodless catapult device with the launch box.

[0005] In summary, rodless cylinders have a broad application prospect in the field of cold catapults. Their characteristic of a long effective stroke is suitable for catapulting large loads, and there are already mature applications in catapulting carrier-based aircraft. However, there is still no actual device for catapulting vehicle-mounted guided vehicles. Therefore, how to design a rodless cylinder catapult device that can be applicable to vehicle-mounted load catapults is an urgent problem to be solved. Summary of the Invention

[0006] To address the deficiencies of the above existing devices, the main objective of the present invention is to provide a vehicle-mounted box-type rodless cylinder catapult device that combines box-type launch and rodless cylinder catapulting. While having the characteristics of protecting the aircraft during box-type launch, rapid response, and convenient maintenance, it also has the advantages of a long effective stroke in rodless catapulting, good compatibility and adaptability, and low requirements for thermal protection. The present invention can be transported mobilely and is more suitable for vehicle-mounted catapulting of large loads.

[0007] The objective of the present invention is achieved through the following technical solutions:

[0008] A vehicle-mounted box-type rodless catapult device disclosed by the present invention includes a launch box, two cylinders on the left and right, a tray, two upper and lower guide rails, two groups of sliders, an aircraft, and an air cylinder.

[0009] The following "front, rear, upper, and lower" are all based on the state when the transportation and preparation are completed and installed.

[0010] The launch box is a square launch box, with multiple square reinforcing ribs distributed on the outside in a fixed connection manner to improve the overall strength of the launch box. An air inlet for injecting the ejection medium is provided at the rear of the launch box. As the outermost protection device, the launch box isolates the outside environment from the internal ejection device during the preparation and transportation states. A rectangular groove is opened below the launch box for the lower guide rail to pass through.

[0011] The cylinder structure includes an external strengthening frame, a cylinder barrel, a buffer device, a pressure relief hole, and an air inlet. When the launch box is placed horizontally, the cylinders are symmetrically and fixedly connected to the left and right sides of the launch box, and the strengthening frame protects and supports the cylinder barrel. A buffer device is connected to the front of the cylinder, two pressure relief holes are symmetrically arranged near the front position, and an air inlet for injecting the ejection medium is provided at the rear.

[0012] The tray includes a tray main body for supporting the aircraft in the middle, a piston, a sealing ring, a sealing steel belt, and a power output arm. The tray main body fits with the aircraft and is connected to the pistons on both sides through the power output arm. The pistons cooperate with the cylinders. The ejection medium is input into the cylinders from the air inlets of the cylinders, pushing the pistons to slide along the inner wall of the cylinder barrels, and driving the aircraft in contact with the tray main body to move through the power output arms. Sealing rings are provided before and after each piston, and the sealing steel belt is located between the openings of the cylinder barrels and the pistons. The sealing rings contact the inner walls of the cylinder barrels to reduce the leakage of the ejection medium during ejection.

[0013] To improve the airtightness of the cylinders during the ejection process, reduce the leakage of the ejection medium during the high-speed movement of the pistons, and improve the ejection efficiency, preferably, one sealing ring is provided on the low-pressure side at the front of the piston, and two sealing rings are provided on the high-pressure side at the rear. Preferably, the sealing rings are of the VL sealing structure with retaining rings. The O-ring uses nitrile rubber material, and the V-ring and retaining ring use polytetrafluoroethylene (PTFE) material.

[0014] The guide rails are fixedly connected to the upper and lower sides of the launch box when the launch box is placed horizontally. Among them, the upper guide rail is connected to the inner wall of the launch box, and the lower guide rail passes through the lower opening of the launch box and is connected to the periphery of the opening. The cross-section of the guide rail is rectangular, and there are three mating surfaces with the slider, namely the guiding surface, the supporting surface and the limiting surface. The slider is divided into upper and lower groups and is distributed on the upper and lower sides of the aircraft through detachable fixed connection. The slider and the guide rail are slidably mated to form a sliding pair, which completes the guiding and supporting functions during the aircraft ejection process, and at the same time restricts the jumping or rolling of the aircraft during the ejection and transportation processes. There are upper and lower mating clearances and lateral mating clearances between the slider and the guide rail. The lower guide rail also serves as a erection bracket. Flat surfaces extend outward from both sides of the lower guide rail as erection supports to support the launch box. A round hole extends from the rear support of the lower guide rail as the rotation center and is connected to the transport vehicle frame through a rotating pair. During transportation, the lower guide rail and the transport vehicle frame are fixedly connected through a front locking device, temporarily acting as the main shaft to improve the strength of the vehicle frame; during the erection process before launch, the locking device is unlocked, and the lower guide rail drives the launch box to be erected to the ready-to-launch state.

[0015] To prevent the guide rails from rusting and increase wear resistance, and at the same time prevent damage to the surface of the guide rails, preferably, the surface of the guide rails is chrome-plated. The slider, which is a disposable part, has a roughness of the mating surface with the guide rail one level higher than that of the guide rail and a hardness higher than that of the guide rail.

[0016] To avoid the erosion of high-temperature and high-pressure gas on the aircraft and the launch device, preferably, compressed air is used as the ejection medium for the ejection power.

[0017] The working method of a vehicle-mounted box-type rodless cylinder ejection device disclosed by the present invention is as follows: during the preparation and transportation process, the launch box isolates the internal and external environments to protect the internal aircraft and ejection device. After the carrier vehicle enters the launch state, the ejection medium flows out from the storage device, enters the cylinder through the input pipeline via the air inlet at the rear of the cylinder, increasing the pressure in the low-pressure chamber of the cylinder behind the piston and generating a thrust on the piston. After the thrust reaches the preset value, the piston starts to slide along the inner wall of the cylinder barrel, drives the tray through the power output arm, and pushes the aircraft outwards. The air in the cylinder barrel is discharged through the pressure relief hole to reduce the ejection back pressure. Compared with the ordinary pull rod type ejection, during the rodless cylinder ejection process, the piston can drive the aircraft to move along the full stroke of the cylinder barrel, with a long ejection stroke and the ability to drive a larger load. During the ejection process, the aircraft is connected to the upper slider and the lower slider, and the sliding motion pair between the slider and the guide rail ensures the stability of the aircraft's movement and plays a guiding role. After reaching the predetermined stroke, the piston is quickly decelerated and separated from the aircraft under the action of the buffer device at the front of the cylinder, and the high-pressure air in the cylinder is discharged through the pressure relief hole, ending the entire ejection process. After the ejection of a single aircraft is completed, the box-type ejection can be quickly prepared for the next launch. For aircraft of different sizes, compatibility is achieved by equipping corresponding sliders; or multiple aircraft can be launched at once through multi-packaging of the launch box due to the compact structure of the box-type ejection.

[0018] Beneficial effects:

[0019] 1. A vehicle-mounted box-type rodless cylinder ejection device disclosed by the present invention uses a launch box as the external structure to wrap components such as the internal aircraft, cylinder, and guide rail slider, isolating the external environment, ensuring the reliability of the aircraft during storage and transportation, being able to adapt to harsher environments, and being more convenient for maintenance. Compared with traditional box-type launches, with the cooperation of the upper and lower guide rails and sliders as the main orientation devices, and the two-side cylinders and pistons as auxiliary orientation, the four-way load-bearing better ensures the stability of the aircraft during transportation and launch.

[0020] 2. A vehicle-mounted box-type rodless cylinder ejection device disclosed by the present invention extends the lower guide rail downward from the launch box body to combine with the erection bracket, and is fixedly connected to the vehicle frame through the front-end locking device, enhancing the overall strength of the vehicle frame.

[0021] 3. A vehicle-mounted box-type rodless cylinder ejection device disclosed by the present invention applies the rodless cylinder ejection device to vehicle-mounted launches, removing the pull rod mechanism inside the traditional pull rod ejection cylinder. There is no problem of the pull rod being bent, and with a more compact structure, the effective ejection stroke is longer, and it can eject a larger mass of load. Compressed air is selected as the ejection medium to avoid the ablation of the aircraft and other ejection devices by high-temperature and high-pressure gas, facilitating maintenance.

[0022] 4. An in-vehicle box-type rodless cylinder ejection device disclosed by the present invention can perform the next launch through rapid preparation after a single aircraft is ejected. For aircraft of different sizes, compatibility is achieved by equipping corresponding sliders; or multiple box-type ejection structures are assembled in series for the launch box according to the compact characteristics of the box-type ejection to eject multiple aircraft at one time. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is an assembly schematic diagram of the box-type rodless cylinder ejection device;

[0024] Figure 2 is a schematic diagram of the assembly structure of the cylinder and the piston;

[0025] Figure 3 is a schematic diagram of the piston sealing structure;

[0026] Figure 4 is a schematic diagram of the lower guide rail structure and its cooperation relationship with the launch box and the vehicle frame

[0027] Figure 5 is a schematic cross-sectional view of the cooperation between the guide rail and the slider.

[0028] Wherein: 1 - launch box, 2 - cylinder, 3 - tray, 4 - upper guide rail, 5 - lower guide rail, 6 - slider, 7 - aircraft, 8 - gas cylinder, 21 - pressure relief hole, 22 - buffer device, 23 - air inlet, 24 - cylinder barrel, 25 - strengthening frame, 31 - piston, 311 - sealing ring, 312 - sealing steel belt, 32 - power output arm, 51 - erection support, 52 - rotation center. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] In order to enable those skilled in the art to better understand the solution of the present invention, the structure, features, and specific implementation manners of the box-type rodless cylinder ejection device applied for by the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. In the following description, different "embodiments" do not necessarily refer to the same embodiment. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0030] The present invention will be further described in detail below in conjunction with the drawings and embodiments. The same reference numerals are used for the same components. It should be noted that the terms "front", "rear", "left", "right", "upper", and "lower" used in the following description refer to the directions in the drawings, and the terms "bottom surface" and "top surface", "inner" and "outer" respectively refer to the directions towards or away from the geometric center of a specific component.

[0031] As Figure 1As shown in the figure, the present invention provides a box - type rodless cylinder ejection device. In the illustrated state, the cylinders 2 are fixedly connected to the left and right sides of the launch box 1. The front part of the cylinder is provided with a pressure relief hole 21 and a buffer device 22, and the rear part has an air inlet 23 for compressed air. The pistons 31 on both sides of the tray 3 can slide back and forth in the cylinder barrel 24 of the cylinder, and drive the aircraft 7 to slide through the power output arm 32; the upper guide rail 4 is fixedly connected to the inner wall of the upper side of the launch box 1, the lower guide rail 5 passes through the opening on the lower side of the launch box and is fixedly connected to the periphery of the opening, and two sets of sliders 6 are detachably connected to the upper and lower parts of the aircraft and can slide back and forth in the guide rails 4 and 5.

[0032] In Figure 1 the illustrated embodiment, the compressed air flows from the gas cylinder (high - pressure chamber) 8 along the pipeline through the pneumatic valve, passes through the reserved air inlet hole of the launch box, and enters the low - pressure chamber from the air inlet 23 at the rear of the cylinder, acting on the piston. When the pressure in the low - pressure chamber reaches the set pressure value, the tray 3 pushes the aircraft 7 to eject outwards.

[0033] Specifically, in some embodiments, as Figure 2 shown, the cylinder 2 of the box - type rodless cylinder ejection device includes a pressure relief hole 21, a buffer device 22, an air inlet 23, a cylinder barrel 24 and an external strengthening frame 25. The cylinder barrel 24 is fixedly connected to the strengthening frame 25, and the strengthening frame 25 is fixedly connected to the launch box 1. The compressed air is introduced into the low - pressure chamber of the cylinder 2 from the air inlet 23 of the cylinder, and pushes the piston 31 to move along the cylinder barrel 24.

[0034] Specifically, in some embodiments, as Figure 3 shown, in order to ensure the airtightness in the cylinder 2 during the movement of the piston 31, multiple sealing rings 311 as Figure 3 shown are distributed on the piston 31. One sealing ring is arranged on the left side (low - pressure side), and two sealing rings are arranged on the right side (high - pressure side). There is a sealing steel belt 312 at the opening part of the cylinder passing through the steel belt groove on the piston 31 to cover the entire cylinder opening area. Both seals adopt the VL sealing structure.

[0035] Specifically, in some embodiments, the slider 6 is detachably and fixedly connected to the aircraft 7 and drives the aircraft to slide along the guide rails 4 and 5. The structure of the lower guide rail 5 and the assembly schematic diagram with the launch box 1 and the vehicle frame are as Figure 4 shown. The vertical support seats 51 extend from both sides of the lower guide rail to support the launch box, and the rear end of the rear support seat is provided with a rotation center 52 for connecting with the vehicle frame. Specifically, in some embodiments, a fitting clearance as Figure 5 shown is set between the upper guide rail 4, the lower guide rail 5 and the slider 6. The fitting clearance should not be too small to avoid difficulties in loading the aircraft 7 into the launch box 1 and jamming during movement, nor should it be too large to affect the ejection accuracy and fixed stability of the aircraft. The fitting clearance mainly includes the lateral fitting clearance △ 1and the vertical clearance Δ 2 , mainly determined by the static direction angle error Δφ and the static elevation angle error selected during design:

[0036]

[0037] In the formula, S 2 is the distance of the support section. During design, Δφ can be taken as 0.3 - 0.5 mils, mils. As small a value as possible should be taken under the condition of ensuring no jamming during the aircraft ejection.

[0038] The above specific description further details the purpose, technical solution and beneficial effects of the invention. It should be understood that the above is only a specific embodiment of the present invention for explaining the present invention and is not used to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A vehicle-mounted box-type rodless cylinder ejection device, characterized in that: It includes a launch box, two left and right cylinders, a tray, two upper and lower rails, two sets of slide blocks, a flying vehicle, and a gas cylinder; The launch box is a square launch box, and multiple square reinforcement ribs are distributed on the outside in a fixed connection manner to improve the overall strength of the launch box; an air inlet for inputting ejection medium is reserved at the rear of the launch box; the launch box is the outermost protective device, isolating the external environment from the internal ejection device in the preparation and transportation state; a rectangular groove is opened at the bottom of the launch box for the lower guide rail to pass through; The cylinder structure includes an external reinforcement frame, a cylinder barrel, a sealing steel belt, and a buffer oil cylinder; when the launch box is placed horizontally, the cylinder is symmetrically fixedly connected to the left and right sides of the launch box, and the reinforcement frame protects and supports the cylinder barrel; the sealing steel belt is located between the cylinder barrel opening and the piston, the front of the cylinder is connected to the buffer oil cylinder, two pressure relief holes are symmetrically arranged near the front position, and the rear is provided with an air inlet for inputting the ejection medium; The pallet comprises a pallet body for lifting the aircraft in the middle, a piston, a sealing ring and a power output arm; the pallet body fits the aircraft and is connected to the pistons on both sides through the power output arm; the piston cooperates with the cylinder, and the ejection medium is input into the cylinder from the cylinder air inlet, pushing the piston to slide along the inner wall of the cylinder, and driving the aircraft in contact with the pallet body to move through the power output arm; each piston is provided with a sealing ring at the front and rear, and the sealing ring contacts the inner wall of the cylinder to reduce the leakage of the ejection medium during ejection; The guide rails are fixedly connected to the upper and lower sides of the launch box when the launch box is placed horizontally, wherein the upper guide rail is connected to the inner wall of the launch box, and the lower guide rail passes through the lower opening of the launch box and is connected to the peripheral side of the opening; the guide rail has a rectangular cross section, and there are three matching surfaces between the guide rail and the slider, namely, a guide surface, a support surface and a limit surface; the slider is divided into two groups, upper and lower, which are distributed on the upper and lower sides of the aircraft through a detachable fixed connection; the slider and the guide rail are slidably matched to form a sliding pair, which completes the guiding and supporting function of the aircraft during the ejection process, and at the same time limits the aircraft during the ejection and Jumping or rolling during transportation and other processes; there are upper and lower matching gaps and lateral matching gaps between the slider and the guide rail; the lower guide rail also serves as an erection bracket, and planes extend outward on both sides of the lower guide rail as erection brackets to support the launch box. A circular hole extends from the rear bracket of the lower guide rail as a rotation center, and is connected to the transport vehicle frame through a rotating pair; during transportation, the lower guide rail is fixedly connected to the transport vehicle frame through a front locking device, temporarily replacing the main shaft to improve the frame strength; during the erection process before launch, the locking device is unlocked, and the lower guide rail drives the launch box to erect to a state ready for launch.

2. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, characterized in that: A sealing ring is arranged on the low-pressure side of the front of the piston, and two sealing rings are arranged on the high-pressure side of the rear.

3. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, characterized in that: The sealing ring adopts a VL sealing structure with a retaining ring, the O-ring is made of nitrile rubber, and the V-ring and retaining ring are made of polytetrafluoroethylene.

4. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, characterized in that: The surface of the guide rail is chrome-plated; the sliding block, which is a disposable part, has a mating surface with a roughness one level higher than that of the guide rail and a higher hardness than that of the guide rail.

5. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, characterized in that: The ejection medium uses compressed air as the ejection power.

6. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, characterized in that: There is a matching clearance between the guide rails 4, 5 and the slider 6; the matching clearance includes the lateral matching clearance Δ1 and the upper and lower matching clearance Δ2. Sure: Where S2 is the support section distance.

7. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 6, characterized in that: Δφ=0.3~0.5 mil, Close position.

8. A vehicle-mounted box-type rodless cylinder ejection device as claimed in claim 1, 2, 3, 4, 5, 6 or 7, characterized in that: During the preparation and transportation process, the launch box isolates the internal and external environments to protect the internal aircraft and ejection device; after the carrier vehicle enters the launch state, the ejection medium flows out of the storage device, and is input into the cylinder through the input pipeline through the hole at the bottom of the cylinder, and the pressure in the low-pressure chamber of the cylinder after the piston is lifted generates thrust on the piston; after the thrust reaches the preset value, the piston begins to slide along the inner wall of the cylinder, and drives the tray through the power output arm to push the aircraft outward, and the air in the cylinder barrel is discharged through the pressure relief hole to reduce the ejection back pressure; compared with the ordinary pull-rod ejection, the piston of the rodless cylinder ejection process can drive the aircraft to move along the full stroke of the cylinder, and the ejection The long stroke can carry a larger load; during the ejection process, the aircraft is connected to the upper and lower sliders, and the sliding motion pairs between the sliders and the guide rails ensure the stability of the aircraft's movement and play a guiding role; after reaching the predetermined stroke, the piston is rapidly decelerated and separated from the aircraft by the buffer device at the front of the cylinder, and the high-pressure air in the cylinder is discharged through the pressure relief hole, and the entire ejection process ends; after the ejection of a single aircraft is completed, the box-type ejection is quickly prepared for the next launch, and corresponding sliders are used for compatibility with aircraft of different sizes; or the launch box can be multi-installed in view of the compact structure of the box-type ejection to eject multiple aircraft at a time.

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