CN116247468A

CN116247468A - Rocket plug traction device and installation method thereof

Info

Publication number: CN116247468A
Application number: CN202310125329.XA
Authority: CN
Inventors: 李永俊
Original assignee: Beijing Tianbing Technology Co ltd
Current assignee: Beijing Tianbing Technology Co ltd
Priority date: 2023-02-16
Filing date: 2023-02-16
Publication date: 2023-06-09

Abstract

The application provides a rocket plug traction device and an installation method thereof. This rocket plug draw gear includes: a pulling device comprising an actuation system and a pulling member; the actuating system comprises an actuating rod and a cylinder body, wherein gas enters a rod cavity of the cylinder body so as to drive the actuating rod to retract; one end of the traction piece is connected with the actuating rod, and the other end of the traction piece is connected with a pull rod arranged on the plug; when the actuating rod is retracted, the pulling piece applies pulling force to the pull rod, so that the plug is separated from the socket. In this way, the plug can be separated from the rocket and can be separated from the rocket body.

Description

Rocket plug traction device and installation method thereof

Technical Field

The invention belongs to the technical field of rocket launching, and relates to a rocket plug traction device and an installation method thereof.

Background

Before the rocket is launched, various working states of the rocket need to be tested, and a ground power supply is generally used for supplying power to on-board instruments and equipment.

The side wall of the rocket body is provided with a socket, and after the plug is inserted into the socket, a cable extending out of the tail of the plug can be connected with a ground power supply to supply power for on-rocket instruments. Typically, the cable is routed from a ground power supply, along the launch frame, and to the rocket sidewall, through a plug, and into a socket.

Before the rocket is ignited, the plug needs to be reliably separated from a socket arranged on the rocket body and fall off from the rocket body. If the plug fails to separate from the socket, if the plug fails to fall off from the rocket body, the launching task is terminated in an emergency way, and if the plug is heavy, the rocket body is damaged, and serious launching accidents occur.

In addition, after the plug drops from the rocket body, if no rebound prevention measures are taken, the dropped plug can rebound to touch the rocket, thereby causing damage or other faults of the rocket body and even failure of rocket launching tasks.

Accordingly, there is a need in the art for a rocket plug traction device that reliably separates and disengages the rocket plug from the rocket body and prevents the plug from bouncing back to touch the rocket.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a rocket plug traction device and an installation method thereof, so that a rocket plug is separated from a rocket body and falls off from the rocket body, and the rocket plug is prevented from being rebounded after falling off to touch the rocket.

In a first aspect, the present invention provides a rocket plug traction device for smoothly pulling off a plug clamped to a socket on a rocket, including:

a pulling device comprising an actuation system and a pulling member;

the actuating system comprises an actuating rod and a cylinder body, wherein gas enters a rod cavity of the cylinder body so as to drive the actuating rod to retract;

one end of the traction piece is connected with the actuating rod, and the other end of the traction piece is connected with a pull rod arranged on the plug;

when the actuating rod is retracted, the pulling piece applies pulling force to the pull rod, so that the plug is separated from the socket.

Further, the pulling device further comprises a breaking pin;

the breaking pin comprises a small end and a large end along the central axis direction; a through hole is arranged on the pull rod along the direction perpendicular to the axis of the pull rod; the breaking pin penetrates through the through hole of the pull rod;

at least 1 weakening groove is respectively arranged at two ends of the small end, and the weakening grooves are arranged outside the through hole;

the two ends of the breaking pin are respectively provided with a connecting hole, and the traction piece respectively penetrates through the connecting holes to be connected with the breaking pin;

when the plug is separated from the socket, the pulling piece is pulled by the actuating rod, and when the pulling force applied to the breaking pin is greater than or equal to the maximum pulling force bearable by the breaking pin, the breaking pin breaks at the weakening groove to separate the pulling piece from the plug.

Further, the actuating system also comprises a pneumatic circuit, wherein the pneumatic circuit comprises a gas tank and an electromagnetic valve;

after the electromagnetic valve is electrified, gas in the gas tank enters the rodless cavity of the cylinder body to drive the actuating rod to retract.

Further, the pneumatic loop further comprises a launching frame gas circuit and a ground gas circuit, wherein the ground gas circuit comprises a gas cylinder, a gas cylinder valve and a gas supply pipeline, and the gas supply pipeline is connected with a gas tank of the launching frame gas circuit and is used for inflating the gas tank of the launching frame gas circuit;

the air passage of the launching frame comprises an air tank, a parallel electromagnetic valve and an air cylinder body; when the plug is required to be pulled and falls off, the parallel electromagnetic valve is electrified, the electric control valve is opened, the gas tank supplies gas to the rod cavity of the cylinder body, and the actuating rod retracts into the cylinder body to move to generate pulling force, so that the plug and the socket are mechanically separated.

Further, the cylinder body of the actuating system is fixed on the transmitting frame, and the retraction direction of the actuating rod is basically the same as the height of the socket; the retraction direction of the actuating rod is within +/-10 DEG of the axial direction of the connection of the plug and the socket.

Further, the method further comprises the following steps:

a backstop device, the backstop device comprising: ratchet mechanism, telescopic link, tie rope;

the ratchet mechanism is arranged on the transmitting frame;

the telescopic rod is connected with the rotating shaft of the ratchet mechanism at one end and connected with the fastening rope at the other end, and the fastening rope is used for fastening the cable connected with the plug;

after the plug is separated from the socket, the telescopic rod swings along with the plug and drives the rotary shaft to rotate;

the pawl of the ratchet mechanism prevents the ratchet from rotating reversely, and further prevents the telescopic rod from pulling the plug to drive the cable to swing to one side of the rocket body.

Further, the method further comprises the following steps:

the buffer device is arranged on the transmitting frame and is used for colliding with the plug when the plug drives the cable to swing to one side of the transmitting frame.

Further, the length L of the pulling member satisfies the following constraint:

l is more than or equal to L0+A+B+C, wherein,

l0 is the theoretical distance between the connecting points of the pull rod and the actuating rod at the rocket release height; c is the inherent amount of slack in the puller; a is the maximum shaking amount of the rocket body in the horizontal direction at the rocket disengaging height; b is the maximum shaking amount of the launching frame in the horizontal direction at the rocket inserting and removing height.

Further, the stroke S of the actuating rod satisfies the following constraint:

s is more than or equal to 2A+2B+C, wherein C is the inherent relaxation amount of the traction piece; a is the maximum shaking amount of the rocket body in the horizontal direction at the rocket disengaging height; b is the maximum shaking amount of the launching frame in the horizontal direction at the rocket inserting and removing height.

In a second aspect, the present invention provides a method of installing a rocket plug traction device, for a rocket plug traction device as described in the first aspect; the method comprises the following steps:

fixing the cylinder body of the actuating system on the transmitting frame so that the retraction direction of the actuating rod is the same as the height of the socket in the horizontal direction; in the horizontal plane, the retraction direction of the actuating rod is within +/-10 degrees of the connection axial direction of the plug and the socket;

inserting the small end of the breaking pin into the through hole of the pull rod arranged on the plug;

one end of the traction piece is connected with the actuating rod, and the other end of the traction piece is connected with connecting holes respectively arranged at the large end and the small end of the breaking pin;

inserting the plug into a socket of the rocket body, wherein a cable connected with the plug is arranged on a launching frame;

mounting the backstop device to the launcher, comprising: adjusting the orientation and length of the telescopic rod so as to tie the cable connected with the plug by using a tie-down rope until the gravity of the cable is borne by the telescopic rod;

and the buffer device is tied to the transmitting frame according to the swing track of the plug separated from the socket.

These and other aspects of the application will be apparent from and elucidated with reference to the embodiment(s) described hereinafter.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and, together with the description, serve to explain the principles of the invention.

Fig. 1 is a schematic view of an installation position of a rocket plug traction device provided by the invention.

Fig. 2 is a schematic diagram of the composition and operation of the pulling device of the rocket plug pulling device provided by the invention.

Fig. 3 is an enlarged view of the snap pin and pull rod of fig. 2.

Fig. 4 is a schematic working diagram of another view of the pulling device in the rocket plug pulling device according to the present invention.

Fig. 5 is a schematic diagram of a pneumatic circuit of a pulling device in a rocket plug pulling device provided by the invention.

Fig. 6 is a schematic diagram of the composition and operation of the backstop device in the rocket plug traction device provided by the invention.

Fig. 7 is a schematic diagram of the composition and operation of the backstop device in the rocket plug traction device provided by the invention.

Description of the embodiments

Various exemplary embodiments of the invention will now be described in detail, which should not be considered as limiting the invention, but rather as more detailed descriptions of certain aspects, features and embodiments of the invention.

It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the invention described herein without departing from the scope or spirit of the invention. Other embodiments will be apparent to those skilled in the art from consideration of the specification of the present invention. The specification and examples are exemplary only.

Some terms in this application are described below:

and in a three-level test mode, three test works of rocket overall assembly test, rocket docking and transportation erection are completed in a horizontal state. The three-plane test mode is adopted, so that the test time of the rocket in a launching zone is greatly shortened, the launching preparation period can be obviously shortened, and the requirement of satellite launching short period can be met.

Three-verticality hair measuring mode: rocket vertical transport, vertical assembly, vertical test and vertical launching; a flat two-fold vertical hair measuring mode: rocket horizontal transfer, vertical assembly, vertical test and vertical launching. In the rocket one-flat two-vertical launching mode and the three-vertical launching mode, the launching farm is provided with a fixed launching tower or a movable launching tower, the air supply pipeline is convenient to lay, and the underground chamber of the launching pad is provided with an air distribution table so as to be convenient for providing an air source.

The traction piece is a spiral steel wire bundle which is formed by twisting steel wires with mechanical properties and geometric dimensions meeting the requirements together according to a certain rule. The traction piece has high strength, is not easy to break off the whole root suddenly, has light dead weight and works stably and reliably.

As shown in fig. 1, a liquid carrier rocket 1 adopting a three-level test mode is horizontally transported to a launching pad and then is arranged on a launching platform 2, a launching frame 3 is used for erecting a rocket body, the launching frame is arranged in the vertical direction, and a preset distance is reserved between the launching frame and the rocket arranged in the vertical direction in the horizontal direction. In order to meet the requirements of low cost and high emission frequency of satellite emission, the emission field level simplifies the guarantee facilities, does not provide a vertical emission tower, does not provide a basement, does not provide a gas distribution table, and also lacks a gas source for driving pneumatic equipment.

During pre-shooting test, power is supplied to the on-arrow instrument equipment through a cable communicated with a ground power supply. The cable is laid along the launching cradle, led to the side wall of the secondary rocket body, and supplies power to the socket arranged on the side wall of the secondary rocket body through the plug 10, namely the secondary inserting and extracting height or the rocket inserting and extracting height. After the pre-shooting test is completed, the plug needs to be reliably separated from the rocket body and the socket and fall off before the rocket is ignited.

As shown in fig. 1 and 5, the rocket plug traction device according to the embodiment of the present application includes a traction device 100, a backstop device 200, and a buffer device 300.

As shown in fig. 1, the plug 10 is engaged at its front end with a socket 4 (schematically shown) provided on the arrow body. Applying a pulling force to the plug along the direction of the central axis of the coupling of the plug and the socket (such as the range of separable pulling forces is denoted as Fmin to Fmax), the plug is unlocked from the socket, separated from the socket and separated from the arrow body.

As shown in fig. 2 and 3, the plug 10 is provided with a hand wheel 10A at its rear end. After rotating the hand wheel 2.5 to 3 turns in the anticlockwise direction, the threaded connection between the plug and the socket is loosened, and the plug and the socket are unlocked and can be separated.

As shown in fig. 2 and 3, the plug 10 is further provided with a pull rod 10B at its rear end. The pull rod 10B extends outwardly from the rotational center axis of the hand wheel 10A. When a pulling force is applied to the plug along the central axis direction of the pull rod 10B, the plug is unlocked from the socket and separated from the socket.

As shown in fig. 3, a through hole is provided at the rear end of the tie rod 10B, and the through hole is perpendicular to the central axis of the tie rod 10B.

As shown in fig. 4, the plug 10 provided at the secondary unplugging height is connected to the cable 5. As shown in phantom in fig. 4, the cable 5 runs along the launcher and leads to the secondary arrow side wall.

As shown in fig. 2, the pulling device 100 includes an actuation system, a pulling member 120. After the pulling member 120 is passed through the through hole shown in fig. 3, the pulling member 120 is pulled in the direction of the central axis of the pulling rod, and pulling force is applied to the plug, so that the plug is unlocked from the socket and separated from the socket.

As shown in fig. 3 and 4, the actuation system includes a pneumatic circuit, an actuation rod 112, and a cylinder body 113. The cylinder body 113 is for being disposed on the cradle 3. The actuating rod 112 extends from a rod cavity provided in the cylinder body 113 and is connected to the rear end of the pulling member 120. The front end of the pulling member 120 is connected to the pulling rod 10B, for example, the front end of the pulling member 120 is connected to the pulling rod 10B through the through hole. The height of the cylinder body 113 arranged on the transmitting frame 3 is approximately the same as the secondary plug-in height, so that the direction of the pulling force applied by the pulling member is controlled within +/-10 degrees of the axial direction of the plug-in and socket connection.

As shown in fig. 2 and 4, the pulling member 120 is connected to the actuator rod 112 at its rear end and to the pull rod 10B at its front end. If the actuating rod is retracted for a preset stroke, the loose pulling piece is tensioned, and the tensioning pulling piece applies pulling force to the plug along the central axis direction of the pulling rod, so that the plug is unlocked from the socket and separated from the socket.

In order to achieve that when the actuating rod retracts to a preset stroke, the tensioned pulling member applies pulling force to the plug, and the plug is separated from the socket, the length of the pulling member and the preset stroke of the actuating rod need to be reasonably designed.

As shown in fig. 1, after the rocket enters the field to before ignition, the rocket 1 stands above the launching platform 2, and is positioned and carried by the launching platform. The launching cradle 3 is arranged at one side of the rocket 1 and is in a state of standing up by 90 degrees. Both rocket 1 and launcher 3 are slightly rocked by wind load. In order to ensure that the socket is reliably connected with the plug, the rocket body is not separated by mistake due to the shaking of the rocket 1 and the shaking of the launching frame 3, and the shaking amount of the rocket body and the shaking amount of the launching frame under the maximum wind speed of a launching field are required to be determined, wherein the shaking amount of the rocket body is measured in a state after the rocket is filled. Through simulation calculation, the maximum shaking amount of the rocket body in the horizontal direction relative to the central axis of the rocket body in the vertical direction at the secondary transplanting height can be determined to be A, wherein the maximum shaking amount of the rocket 1 away from the launching frame 3 is recorded as +A, and the maximum shaking amount of the rocket 1 close to the launching frame 3 is recorded as-A. Through simulation calculation, the maximum shaking amount of the launching frame in the horizontal direction relative to the central axis of the launching frame in the vertical direction or the vertical direction of the rocket at the position corresponding to the plug can be determined to be B, wherein the maximum shaking amount of the launching frame 3 away from the rocket 1 is recorded as +B, and the maximum shaking amount of the launching frame 3 close to the rocket 1 is recorded as-B.

Because the pulling member 120 is connected to the actuating rod and the pulling rod, respectively, as shown in fig. 4, in order to avoid the plug 10 from being separated by mistake due to the pulling force of the pulling member under tension caused by wind load shaking, the minimum length L of the pulling member 120 is l0+a+b+c, where L0 is the theoretical distance between the connecting points of the pulling rod and the actuating rod at the secondary inserting and withdrawing height, and C is the inherent loosening amount of the pulling member, and is generally greater than 10mm to 50mm. Therefore, even if the rocket or the launching frame shakes under the maximum wind load before the pulling piece pulls the pull rod to separate the plug from the socket, the pulling piece can still be loose, so that the plug is prevented from being separated from the socket by the pulling force of the pulling piece.

Referring to the foregoing description, as shown in fig. 4, in order to ensure that the plug can be pulled out after the actuating rod is retracted by a preset stroke after the pulling separation is started, the minimum stroke of the actuating rod is S during the selection _min =2a+2b+c. After the selected cylinder is mounted on the transmitting frame according to the specification, the minimum stroke when pulling and separating is started, namely the stroke of the retracting actuating rod is not smaller than the minimum stroke 2A+2B+C. Thus, when the actuating rod retracts and pulls the pulling member, the pulling member has at least a travel of 2a+2b+c, and at this time, the maximum distance between the connecting point of the pulling member and the actuating rod at the secondary insertion-removal height limited by the pulling member 120 is l0+a+b+c- (2a+2b+c), that is, L0-a-B, so that even if the rocket 1 generates maximum shaking to the right and maximum shaking to the left of the launching frame 3, the pulling member can be tensioned and the pulling plug can be mechanically separated from the socket by controlling the retraction of the actuating rod by the preset travel.

In some embodiments, the predetermined travel of the actuator rod is between 100mm and 400 mm.

By restraining the minimum length of the traction piece and the minimum stroke of the actuating rod, the traction piece can have larger tensioning allowance, and the actuating rod can have larger stroke allowance. In this way, it is achieved that the pulling element remains in a relaxed state before the pulling separation is initiated. After the pulling separation is started, the pulling piece is in a tensioning state, and transmits the pulling force applied to the plug along the central axis direction of the pull rod 10B, so that the plug is unlocked from the socket and separated from the socket.

Compared with a rod with higher rigidity or a flexible rope with higher flexibility, the steel wire rope is used as the traction piece, and the steel wire rope has proper rigidity and flexibility, thereby being beneficial to meeting the control requirement of controlling the direction of the traction force within +/-10 degrees of the axial direction of the coupling of the plug and the socket, and having enough looseness. Therefore, the traction piece is used for connecting the actuating rod and the plug, the scheme is simple, the implementation is convenient, and the high reliability is realized.

As shown in fig. 5, the pneumatic circuit includes a firing rack air path 111A and a ground air path 111B, and the ground air path 111B is used to provide an air source for the firing rack air path 111A.

As shown in fig. 5, the rack gas path 111A includes a gas tank, a solenoid valve. The compressed gas is directed to the rod cavity of the cylinder body 113, driving the actuating rod 112 to retract. The rodless cavity of the cylinder body 113 is then directly evacuated. The electromagnetic valve can be arranged as a parallel electromagnetic valve group and comprises 2 two-position three-way electromagnetic valves, and the 2 two-position three-way electromagnetic valves are designed in a dual redundancy way. Any two-position three-way electromagnetic valve is electrified to enable compressed gas in the gas tank to be led to the rod cavity of the cylinder body 113, and the actuating rod 112 is driven to retract.

Optionally, a bleed air throttle valve may be further provided. The bleed throttle valve is used to regulate the flow of compressed gas to the rod chamber of the cylinder body 113. By adjusting the flow of compressed gas to the rod chamber of the cylinder body 113, the retraction speed of the actuating rod can be adjusted, e.g., the greater the flow, the greater the retraction speed. In order to avoid instability caused by overshoot of the actuating rod to pull the pulling piece under high flow, the flow of compressed gas from the gas tank is reduced by using the throttle valve, and the plug separation can occupy shorter operation time in the pre-shooting flow while realizing stable tensioning of the pulling piece.

The pre-cylinder pressure gauge is used in conjunction with a bleed-off throttle valve for acquiring the pressure of the compressed gas that is directed to the rod chamber of the cylinder body 113. Typically, a pre-cylinder pressure gauge is typically used in the air path adjustment. The pre-shooting procedure typically does not require taking readings of a pre-cylinder pressure gauge.

Preferably, a single-action introduction type air cylinder is selected, when the rod cavity is accessed with compressed gas, the actuating rod is retracted, and a spring arranged in the rodless cavity is compressed; when the rod cavity is not connected with compressed gas, the actuating rod is reset and extends out by the spring. Therefore, the single-rod-outlet cylinder is simple in structure, reliable in sealing and stable in movement direction, and is beneficial to reliably tensioning the traction piece and mechanically separating the traction plug from the socket.

Before firing, the gas tank of the firing rack gas circuit 111A is inflated by the ground gas circuit 111B. Preferably, the gas tank is provided with a directional valve, which, when inflated, inflates from the ground gas path 111B. After inflation is complete, the gas tank is in a deflatable state. In some embodiments, the gas tank may be an accumulator having a preset inflation pressure.

When the pulling device separates the plug from the socket according to the transmission flow requirement, a control command is sent by a remote control industrial personal computer of the ground detection and control system, the parallel electromagnetic valve group is electrified, the electric control valve of at least one two-position three-way electromagnetic valve with double redundancy design is electrically opened, the pressure or flow is regulated through the deflation throttle valve, compressed gas in the gas tank is led to a rod cavity of the cylinder body 113, the actuating rod 112 is retracted and generates pulling force, and the pulling member 120 pulls the pulling rod to separate the plug from the socket. Specifically, the gas is supplied to the side having the rod chamber, the compressed gas pushes the actuating rod to retract, tensioning the pulling member 120, and applying a pulling force to the pulling rod through the pulling member, so that the plug is separated from the socket.

Then, the remote control industrial personal computer of the ground detection and control system can send a control instruction to power off the parallel electromagnetic valve group, stop supplying air to one side of the rod cavity, and the actuating rod is reset and stretches out by means of a spring arranged in the rodless cavity.

In this way, an electrical telemetry integrated strategy is adopted, namely, a scheme that the pulling device uses a circuit to control the gas circuit so as to drive the cylinder is adopted, and compared with a scheme that the gas circuit drives the cylinder body completely, a separate matching gas distribution table is not needed, and a gas supply pipeline from the gas distribution table to the cylinder is laid along the launching tower; compared with the complete electric pushing and pulling scheme, the method has the advantages of high response speed and short operation time occupied in the shooting process.

In some embodiments, the emitter gas channel 111A is mounted within an actuator box (not shown) and the actuator box is secured to the emitter to facilitate protecting the emitter gas channel 111A from corrosion by ambient gases or from engine tail flame ablation.

As shown in fig. 5, the ground air path 111B includes an air cylinder, an air cylinder valve, a front cylinder pressure gauge, an air supply hand valve, an air filter, a pressure reducing valve, a pressure regulating gauge, an air charging throttle valve, an air release valve, and a multi-stage pipe connecting the air cylinder with each valve or pressure gauge.

In general, the gas tank of the rack gas path 111A is inflated once and used once, and is inflated again when used next time. The gas cylinder of the ground gas circuit 111B is inflated and used for multiple times. The cylinder is typically at a higher pressure and a greater capacity than the cylinder. In some embodiments, the pressure of the cylinder is between 0.8MPa and 5 MPa.

During the ground ready commissioning phase, the ground air path 111B may provide an air source for the ground test launch control system. Before firing, the ground air path 111B may inflate the air tanks of the firing rack air path 111A. For repeated use, the ground air path 111B is ground movable, and is used on the ground in a maneuvering mode, and is not mounted on the transmitting frame. Therefore, the air tank placed on the launching frame is used as an air source of the air cylinder, and the problem that the launching pad is inconvenient to place an air distribution table and then lacks an air source is solved.

Once the plug and socket are disconnected, an emergency termination of the transmission task is caused. At the same time, once the mechanical separation of the plug from the socket fails, the actuating rod will further pull the pulling rod, the plug and the socket still kept locked with the plug through the tensioned pulling member, and thus the rocket may be overturned.

For the failure mode that the mechanical separation of the plug and the socket fails, the pulling device 100 further includes a breaking pin 130, so as to break the breaking pin when the shearing force exerted on the breaking pin by the pulling force is greater than Qmax, so that the pulling member is forcedly separated from the plug and the socket, and the arrow body is prevented from being overturned or pulled off from the plug or the socket due to the pulling of the pulling member, thereby damaging the arrow body.

As shown in fig. 3, the snap pin 130 includes a small end 130B and a large end 130A along the central axis direction thereof, wherein the cross-sectional area or diameter of the small end 130B is smaller than the area or diameter of the through hole of Yu Lagan B; the cross-sectional area or diameter of the large end 130A is larger than the area or diameter of the through hole of the tie rod 10B. Thus, the small end 130B of the breaking pin 130 can pass through the through hole of the pull rod 10B and extend out of the through hole; the large end 130A of the snap pin 130 then stays out of the hole.

As shown in fig. 3, the small end 130B of the snap pin is provided with one connection hole and the large end 130A is provided with another connection hole. The 2 connection holes are parallel and perpendicular to the central axis direction of the breaking pin 130. The front end of the pulling member 120 sequentially passes through the 2 connection holes provided in the breaking pin, and then is connected to the breaking pin 130, and further to the pull rod 10B and the plug 10. In specific implementation, according to the operation specification of the pulling member, after the pulling member 120 is connected with the two connecting holes, the front end of the pulling member 120 is in a Y shape or a balloon shape.

As shown in fig. 3, the small end 130B of the snap pin is provided with at least 1 weakening groove, such as

weakening grooves

130E and 130D, respectively, at both ends thereof in the circumferential direction as the weakest stressed area on the snap pin. The cross-sectional area and the material of the small end of the breaking pin and the depth of the weakening groove (for example, the weakening groove is processed by milling or turning), namely, the groove depth of the annular groove, can be reasonably designed so that the maximum shearing force bearable at the weakening groove is Qmax, so that the maximum shearing force is larger than the separation traction force Fmax for separating the plug from the socket and is far smaller than the overturning traction force Pmax transmitted by the traction piece when the rocket is overturned, namely, the overturning traction force Pmax is larger than the separation traction force Fmax.

In this way, in the failure mode that the mechanical separation of the plug and the socket fails, if the shearing force transmitted to the weakening groove of the breaking pin by the pulling member is greater than Qmax, the breaking pin 130 is damaged at the weakening groove, and the pulling member under tension is forcibly separated from the plug and the socket while protecting the plug, so that the arrow body is prevented from overturning. At this point, the cable tied to the cradle remains connected to the plug.

Therefore, in the fault mode that the mechanical separation of the plug and the socket fails, the easily-machined, easily-replaced and low-cost breaking pin is broken at first, so that the plug is protected as a recyclable key part.

Therefore, the safety of the rocket in the fault mode that the mechanical separation of the plug and the socket fails can be improved by using the breaking pin, and the phenomenon that the rocket body is overturned or damaged due to the traction force applied by the traction device is avoided.

As shown in fig. 4, 6 and 7, the backstop device 200 includes: ratchet mechanism, telescoping rod, tether 230. The ratchet mechanism is arranged on the transmitting frame 3 and is positioned above the side of the secondary plug-in removing height. The ratchet mechanism includes a ratchet 211 and a pawl 212. Pawl 212 is used to limit one-way rotation of ratchet 211 (as indicated by the arc arrow).

As shown in fig. 6, the telescopic rod includes an outer rod 221 and an inner rod 222. By adjusting the overlapping length of the outer rod 221 and the inner rod 222, the length of the telescopic rod can be adjusted. The manner of adjusting the overlapping length of the outer rod 221 and the inner rod 222 and fixing the inner rod after adjustment can be achieved with reference to the prior art, and will not be described again.

As shown in fig. 6, the front end 221A of the outer rod 221 is fixedly connected to the rotation shaft of the ratchet 211, so that the telescopic rod and the ratchet 211 form a swinging link mechanism, and the telescopic rod can rotate along with the ratchet or drive the ratchet to rotate by changing the orientation of the telescopic rod.

As shown in fig. 6, the trailing end 222B of the inner rod 222 is provided with a fastening hole. The tether 230 passes through the tether hole for securing the cable 5 to which the plug 10 is connected. Therefore, the telescopic rod can pull the cable obliquely upwards and bear the gravity of the cable 5, and the connection deviation of the plug and the socket caused by the dead weight of the cable 5 and the like is avoided.

Before the rocket is launched, the direction of the pulling force of the cable 5 pulled by the telescopic rod can be adjusted by rotating the ratchet 211 of the ratchet mechanism. By adjusting the length of the telescopic rod, the position at which the tether line 230 is tethered to the cable 5 can be adjusted. It should be appreciated that when the ratchet 211 is rotated to adjust the direction of the telescoping rod, the pawl 212 may be lifted so that it no longer abuts against the detent of the ratchet 211 to prevent the ratchet 211 from rotating in the opposite direction.

In some embodiments, the telescopic rod and ratchet 211 form a swing link mechanism, which may also be the following: the length of the telescopic rod can be kept unchanged, a sliding groove is formed in the joint of the head end 221A of the outer rod and the rotating shaft of the ratchet wheel along the radial direction of the rotating shaft, and the head end 221A of the outer rod is kept in the sliding groove and slides along the sliding groove. At this time, the position where the fastening rope 230 is fastened to the cable 5 can be adjusted by sliding the telescopic rod relative to the rotation shaft.

As shown in fig. 4, 6 and 7, after the plug is separated from the socket, under the action of gravity, the plug 10 drives the cable 5 to swing towards the launching frame 3, and the telescopic rod is connected with the cable 5 and the plug through the fastening rope 230, so that the fastening rope 230 pulls the telescopic rod to swing towards a direction away from the rocket, and drives the ratchet 211 to rotate. In this way, the plug drives the cable 5 to do frictional single pendulum motion, and a swinging track after the plug is separated is formed.

In general, after the plug drives the cable to swing to one side of the launching cradle through the lowest point, the cable can be decelerated under the action of gravity and friction. Correspondingly, in the process that the plug drives the cable to swing to one side of the transmitting frame, the length of the telescopic rod can be adjusted in a small range so as to adapt to the swing track of the single swing motion.

When the plug 10 drives the cable 5 to reach the upper dead point of the single pendulum movement and swings to the rocket side in the opposite direction (namely rebounds), the telescopic rod drives the ratchet 211 to rotate in the opposite direction; the ratchet 211 can only rotate in one direction under the limit of the pawl 212, so that the plug and the cable can be reliably prevented from swinging reversely, and rebound is avoided.

Above, when the plug 10 is detached from the socket, the telescopic rod drives the ratchet 211 to rotate under the gravity action of the plug 10 and the cable 5 connected with the plug, and the ratchet is far away from the surface of the arrow body. Since the ratchet 211 can rotate in only one direction, the ratchet can be reliably prevented from rotating in the reverse direction, and further the plug and the cable can be prevented from swinging in the reverse direction, and the plug can be reliably prevented from bouncing back to collide with the arrow body.

Therefore, after the plug is separated from the socket and falls off, the backstop device provided with the ratchet wheel and the pawl is used for preventing the plug and the cable from rebounding, the principle is simple, the technology is mature, and the reliability is high.

In some embodiments, as shown in fig. 1, a buffer device 300 may also be provided in order to make the plug recyclable for reuse. The cushioning device typically has a reticulated porous structure. Four vertex angles of the buffer device are tied and fixed on the transmitting frame 3 at the position of the transmitting frame, which faces to the plugs and the cable and falls back, so as to receive the plugs after falling, namely to collide with the plugs, and avoid the plugs from being broken by the transmitting frame with higher strength and hardness. The cushioning device is generally made of refractory materials and can bear the ablation of engine tail flame in the rocket takeoff stage. The cushioning devices are typically flexible materials that can take on an arcuate appearance under wind load. Naturally, if it is confirmed that the plug and the cable draw-down telescopic rod are swung, the swing track or the upper dead point position of the plug and the cable draw-down telescopic rod cannot collide with the launching frame structure, and the buffer device is not required.

In some embodiments, a flexible pad may also be used as a cushioning device. When the plug is separated from the socket and drives the cable to swing, the plug repeatedly collides with a flexible pad such as a silicone rubber pad, and the flexible pad absorbs impact force generated during collision.

In some embodiments, a device with spring damping may also be used as a buffering device, such as a compression cylinder, such as a hydraulic damper, which will not be described again.

In summary, the plug traction device adopts the scheme that a circuit is used for controlling a gas circuit so as to drive a cylinder, so that the response speed is high, and the occupied operation time in the pre-injection process is short; the electromagnetic valve arranged on the gas path is controlled to be opened or closed by a circuit, and the gas tank arranged on the transmitting frame is used as a gas source of the driving action rod, so that the problems that the transmitting field apron is inconvenient to place a gas distribution table and lacks gas sources are solved. The backstop device is used for preventing the plug from rebounding after the plug is detached; the use of the snap pin can improve the safety of the rocket in the failure mode of the plug disconnection failure.

When the rocket plug traction device provided by the embodiment of the application is installed on a launching frame, the rocket plug traction device comprises the following steps:

1) The cylinder body of the actuating system is fixed on the launching frame, so that the retraction direction of the actuating rod is the same as the secondary plug-in and plug-out height of the plug on the rocket in the vertical direction; in the horizontal plane, the retraction direction of the actuating rod is within + -10 DEG of the plug-and-socket connection axis.

2) The small end of the breaking pin is inserted into the through hole of the plug pull rod.

3) One end of the traction piece is connected with the actuating rod, and the other end is connected with a connecting hole arranged at the large end and the small end of the breaking pin.

4) The plug is inserted into the socket of the arrow body according to the operation rules, and at this time, the plug 10 is connected with the cable 5.

5) The backstop is mounted to the cradle. The orientation and the length of the telescopic rod are preliminarily adjusted. And a cable for connecting the telescopic rod with the plug is fastened by using a fastening rope. The direction and length of the telescopic rod are adjusted again, for example, the position where the fastening rope 230 is fastened on the cable 5 is adjusted, for example, the direction in which the telescopic rod pulls the cable 5 is adjusted until the gravity of the cable is borne by the telescopic rod, so that the plug is prevented from deflecting relative to the socket due to the dead weight of the cable, and the plug can be separated and separated to drive the cable to pull the telescopic rod to swing.

6) The buffer device is tied to a proper position on the launching frame according to the swing track of the plug and the socket after being separated, for example, the plug and the cable are located at the falling point of the launching frame after swinging.

Finally, after the rocket is ignited, the plug and the cable are recovered according to the launching process.

The plug traction device and the installation method thereof occupy short operation time in the pre-shooting process; the problems that the launching pad is inconvenient to place a gas distribution table and lacks a gas source are solved, and the rocket plug is beneficial to being reliably separated from a rocket and falling off from a rocket body and avoiding the rocket from being touched due to rebound of the plug. The adopted technical scheme is simple, reliable, good in redundancy and high in completion, and can realize zero-second falling.

The foregoing is merely illustrative of the embodiments of this invention and any equivalent and equivalent changes and modifications can be made by those skilled in the art without departing from the spirit and principles of this invention.

Claims

1. A rocket plug draw gear for pull the plug that the joint was in the socket on with the rocket smoothly and drop, its characterized in that includes:

a pulling device comprising an actuation system and a pulling member;

2. The traction device of claim 1, wherein the traction device comprises a traction device,

the traction device further comprises a breaking pin;

3. The traction device of claim 1, wherein the traction device comprises a traction device,

the actuating system also comprises a pneumatic circuit, wherein the pneumatic circuit comprises a gas tank and an electromagnetic valve;

4. The traction device of claim 3, wherein the traction device comprises a traction device,

the pneumatic loop further comprises a launching frame gas circuit and a ground gas circuit, wherein the ground gas circuit comprises a gas cylinder, a gas cylinder valve and a gas supply pipeline, and the gas supply pipeline is connected with the gas cylinder of the launching frame gas circuit and is used for inflating the gas cylinder of the launching frame gas circuit;

the air passage of the launching frame comprises an air tank, a parallel electromagnetic valve and an air cylinder body; when the plug is required to be pulled and falls off, the parallel electromagnetic valve is electrified, the electric control valve is opened, the gas tank supplies gas to the rod cavity of the cylinder body, and the actuating rod retracts into the cylinder body to move to generate pulling force, so that the plug and the socket are separated.

5. The traction device of claim 1, wherein the traction device comprises a traction device,

the cylinder body of the actuating system is fixed on the transmitting frame, and the retraction direction of the actuating rod is basically the same as the height of the socket; the retraction direction of the actuating rod is within +/-10 DEG of the axial direction of the connection of the plug and the socket.

6. The traction device of claim 1, further comprising:

the ratchet mechanism is arranged on the transmitting frame;

7. The traction device of claim 1, further comprising:

8. The traction device of claim 1, wherein the traction device comprises a traction device,

the length L of the pulling member satisfies the following constraint:

l is more than or equal to L0+A+B+C, wherein,

9. The traction device of claim 8, wherein the traction device comprises a traction device,

the stroke S of the actuating lever satisfies the following constraint:

10. A method of installing a rocket plug traction device according to any one of claims 1 to 9;

the method comprises the following steps: