CN112319867A - Ejection type connecting and separating integrated device - Google Patents
Ejection type connecting and separating integrated device Download PDFInfo
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- CN112319867A CN112319867A CN202011181754.3A CN202011181754A CN112319867A CN 112319867 A CN112319867 A CN 112319867A CN 202011181754 A CN202011181754 A CN 202011181754A CN 112319867 A CN112319867 A CN 112319867A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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Abstract
The utility model provides a separation integrated device is connected to ejection formula, mainly by casing subassembly (1), push pedal subassembly (2), remote measuring device (3), connect unlocking device (4) and constitute, the satellite is locked and is placed in the casing subassembly through connecting unlocking device under the initial condition, connect the unlocking device unblock after the satellite is put into orbit, a push pedal subassembly for promoting the satellite to be launched outwards by casing subassembly sets up in the casing subassembly and contacts with the satellite, remote measuring device sends the unblock signal to connecting unlocking device under ground control station control, and send the separation signal to the push pedal subassembly, there is size constraint to the satellite in traditional satellite-rocket connection separation device has been solved, unable adaptation satellite's different configuration, can not satisfy the problem of quick transmission, stable in structure.
Description
Technical Field
The invention relates to an ejection type connection and separation integrated device, and belongs to the field of satellite and rocket separation device design.
Background
With the development of space science and technology, the technical trend of satellite development at home and abroad is mature day by day, the launching task is increased day by day, and the configuration, the size and the like of the satellite are diversified day by day. On the background that a satellite needs to carry a carrier rocket to lift off, the technical requirements of the future aerospace technology on the utilization rate of a carrying space position, the development period of a satellite-rocket separation device, small impact on the satellite, high-efficiency reliable separation realization and real-time unlocking separation remote measurement are higher and higher, and the traditional satellite-rocket separation device with a fixed structure can not meet the requirements of the satellite on carrying. Therefore, research on a novel connection and separation device which can be rapidly developed, is suitable for a satellite and a carrying space, has small impact on the satellite, and realizes high-efficiency reliable separation and real-time unlocking separation remote measurement is urgently needed.
Based on traditional satellite-rocket connection separation device, the separation device is axially installed along the rocket through the installation support on the supporting cabin, the utilization rate of cone angle space between the supporting cabin section and the fairing is not high, or the satellite is radially separated along the rocket, the separation device is uniformly installed on the cylindrical cabin section on the supporting cabin, the space of the oblique cone section of the supporting cabin is still not utilized, and the low space utilization rate is caused. The satellite-rocket separation device which is carried on the side wall of the supporting cabin and has the traditional structure has certain size constraint on the satellite, so that the design of the satellite has certain limitation, the period can be obviously increased when the novel connection and separation device is designed aiming at the new structure of the satellite, the satellite-rocket separation device can not be quickly adapted to the structure of the satellite which is increasingly diversified day by day, and the requirement for quick launching can not be met. In addition, the traditional star-arrow separation device has at least more than two initiating explosive devices, has large impact on satellites and cannot meet the requirement of satellite impact of a future satellite provided with a precise single machine. In the traditional satellite and rocket separation device which separates the satellite by the spring and the orbit, the spring does not work in the full stroke range of the guide rail, the separation efficiency of the satellite is not reliable, even clamping stagnation is possible to occur, and therefore the reliability is not high. Finally, the real-time unlocking separation telemetering function is an important functional component in the satellite and rocket separation device, and the separation device with the traditional structure realizes the real-time unlocking separation telemetering function by a travel switch and a telemetering assembly, and has the defects of more mounting positions, heavy weight and more quantity.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the problems that the traditional satellite-rocket connecting and separating device has size constraint on a satellite, cannot adapt to different configurations of the satellite and cannot meet the requirement of quick launching in the prior art, the ejection type connecting and separating integrated device is provided.
The technical scheme for solving the technical problems is as follows:
the utility model provides a separation integrated device is connected to ejection formula, includes casing subassembly, push pedal subassembly, telemetering device, connects unlocking device, casing subassembly fastening connection is on the satellite supports the cabin, and the satellite locks and places in casing subassembly through connecting unlocking device under the initial condition, connects the unlocking device unblock after the satellite orbit entry for the push pedal subassembly that promotes the satellite and outwards launch by casing subassembly sets up in casing subassembly and contacts with the satellite, telemetering device sends the unblock signal to connecting unlocking device under ground control station control, and sends the separation signal to the push pedal subassembly.
The casing assembly comprises a first guide rail, a second guide rail, a left skin, a right skin, an upper skin, a lower skin, a rear end cover, a door frame and a positioning pin, wherein the left skin and the right skin are the same trapezoidal structural skin, the upper skin and the lower skin are rectangular structural skins, the left skin, the right skin, the upper skin and the lower skin are fixed through the door frame and form a box structure of a trapezoidal body through the rear end cover, the positioning pin connected with a satellite in a matched mode is arranged on the door frame, the first guide rail and the second guide rail are arranged on the inner side of the box structure and used for sliding of the push plate assembly, and the door frame and the lower skin are connected to the satellite supporting cabin through fastening pieces.
The first guide rail and the second guide rail are fixed on the inner side of the upper skin and the inner side of the lower skin through fasteners and are semi-hollow guide rails.
The push plate component comprises a front baffle plate, a rear baffle plate, a first guide column, a second guide column, a reinforcing column, a spring cylinder, a side baffle plate, a separation spring and a pressing block, wherein the front baffle plate, the rear baffle plate, the first guide column, the second guide column, the reinforcing column, the spring cylinder and the side baffle plate are fixed through fasteners to form a rectangular flat plate push plate structure, a through hole is formed in a rear end cover, the through hole is respectively connected with the pressing block and the reinforcing column through the fasteners, the first guide column, the second guide column, the reinforcing column, the spring cylinder and the side baffle plate are all arranged on the front baffle plate, the rear baffle plate is in contact with the rear end cover, the rear end of the separation spring is respectively fixed at four top corners of the rear end cover through the pressing block, the front end of the separation spring is arranged on the rear baffle plate at the rear end of the push plate structure through the spring cylinder, the first guide column, the second guide column, the reinforcing column, the push plate structure is contacted with the bottom surface of the satellite and matched with the satellite to slide along the directions of the first guide column and the second guide column in a matched manner with the first guide rail and the second guide rail.
The separation spring promotes the guide cylinder ring that reinforcing post, spring case, side shield are constituteed in the push pedal subassembly and slides, all be provided with the arch in the slip direction on first guide post, second guide post, door frame, the lower covering for it is spacing to carry out the push pedal subassembly.
The remote measuring device comprises a reed switch and a magnet, wherein a round hole is designed on the second guide column and used for placing the magnet, a round hole is designed on the second guide rail and used for leading out a reed switch wire, the reed switch is arranged at the front end and the rear end of the semi-hollow inner cavity of the second guide rail through glue, the magnet is close to the reed switch in distance during locking, a compression signal is obtained by measuring a wire led out of the reed switch through the round hole of the second guide rail, and a separation signal is obtained by measuring a wire led out of the reed switch through the round hole of the second guide rail in the separation process of the satellite and the shell assembly so as to realize real-time unlocking and separation remote measuring.
And central round holes are formed in the front baffle and the rear baffle and used for the connection unlocking device to penetrate through and be fixed with the satellite ground.
The connecting and unlocking device is arranged in the center of the rear end cover, passes through the shell assembly and passes through the central circular hole of the push plate assembly to be connected with the satellite base, and comprises an adapter cylinder, an explosive bolt, a ball pad, a base plate, a square nut, a stainless steel plate, a magnesium alloy plate, an epoxy glass plate, a honeycomb, a rubber plate and an explosive bolt protective cover, wherein the explosive bolt passes through the ball pad and the rear end cover and is connected and locked with the square nut arranged in the adapter cylinder in a threaded manner; stainless steel plate, magnesium alloy board, epoxy glass board, honeycomb, rubber slab all set up and are used for reducing the satellite impact effect in switching section of thick bamboo bottom, the ball pad sets up and is used for guiding orientation on the preceding baffle, sets up honeycomb, rubber slab in the switching section of thick bamboo, and the explosion bolt safety cover sets up and realizes the protection in the explosion bolt outside to the explosion bolt.
When the satellite is locked, pretightening force is applied to the explosion bolt, the pretightening force is applied to the positioning pin, the satellite and the separating device are reliably connected and locked under the common supporting action of the positioning pin of the rear end cover, the explosion bolt is detonated when the satellite enters the orbit, the connecting and unlocking device is unlocked, and the satellite slides out of the shell assembly along the first guide rail and the second guide rail under the action of the separating spring and the push plate assembly to realize satellite separation.
The space of the shell component is determined and manufactured according to the shape and the volume of the satellite, the shell is machined by adopting a plate machine, and the door frame is machined according to the angle of the carrying support cabin.
Compared with the prior art, the invention has the advantages that:
(1) the invention provides an ejection type connecting and separating integrated device, wherein a door frame and a lower skin in a separating device can be arranged on a carrying support cabin, the door frame can adapt to and be processed according to the angle of the carrying support cabin, so that a satellite fully utilizes the space position between a fairing and the support cabin, the space utilization rate is improved, the space size and the shape of a connecting and unlocking device can be processed according to the shape and the volume of the satellite, meanwhile, a plate machine is adopted for processing, the development period of a shell is short, the satellite can be quickly adapted to the requirements of the satellite, meanwhile, the single connecting and unlocking device is connected with a satellite base, a positioning pin is matched with the satellite through the door frame to bear the load of the satellite, the satellite has the function of prestress under the combined action of the pretightening force applied to an explosion bolt and the positioning pin, the rigidity of the combined body of the, the number of the connecting and separating devices is reduced, so that initiating explosive devices are reduced, and smaller impact is realized;
(2) the connecting and unlocking device adopted by the invention realizes reliable connection with the satellite through an explosive bolt, and three layers of base plates, rubber plates and honeycomb plates made of three materials are adopted to reduce the impact; the explosive bolt protective cover and the adapter cylinder are adopted, so that the collecting effect of the explosive bolt after detonation is realized, and the generation of redundancy is prevented; the ball socket is adopted to realize the automatic position adjustment function when the pretightening force of the explosive bolt is applied; the explosion bolt is used for providing counter torque in the loading process by adopting a square nut, the loading is convenient, guide rails are fixed on four corners of an inner cavity of a shell assembly, a satellite slides in the shell assembly through the guide rails, a space constraint effect on the satellite is achieved in a spring separation device through a push plate structure when the spring separation device is locked, the satellite is reliably supported, the push plate structure pushes the satellite to separate after unlocking, the satellite keeps force transmissibility in the separation process of the inner cavity of the shell, the mechanism is not blocked, the separation efficiency and reliability are improved, when the push plate continues to move to the later stage along the guide rails, the push plate structure is limited, and the satellite is separated out of the device to complete separation;
(3) the door frame and the lower skin of the invention are raised to play a limiting role for the front baffle of the push plate assembly and prevent the push plate assembly from being pushed out of the separation device, the rear end of the positioning pin is designed into a hexagon and can be adjusted forwards and backwards to complete position matching with the satellite, the positioning pin can be screwed by a wrench to be pushed against the satellite and have a certain force effect, the rear end cover is provided with a pressing block, the separation spring can be fixed by a fastener, the separation reliability is ensured, meanwhile, the rear end cover is provided with a push plate tightening screw, the push plate assembly can be firstly folded during assembly to facilitate the installation of the satellite, the tightening screw is removed after the installation of the satellite is completed, the separation function can be realized, the rear end cover is provided with a push plate compression screw, the installation of a connecting and unlocking device can be completed after the satellite is installed in the separation device, the attachment of the push plate to the, the effect of realizing physical constraint on the satellite is achieved;
(4) the separation spring adopted by the invention realizes guiding through the spring cylinder, the guide column, the reinforcing column and the side baffle, the reed pipe of the remote measuring device is placed in the guide rail, the guide column of the push plate structure is provided with the round hole for placing the magnet of the remote measuring device, according to the principle that when the distance between the magnet and the reed pipe is close, the loop resistance of the reed pipe is small, and when the distance between the magnet and the reed pipe of the guide rail is far, the loop resistance of the reed pipe is large, the signal is measured through the lead led out from the reed pipe. According to the compression position of the pushing half combination body when the satellite is locked and the limit position of the push plate structure when the satellite is separated, the distance between the magnet in the guide column and the reed switch in the guide rail is close when the magnet is locked, a compression signal is obtained by measuring a lead led out by the reed switch through the guide rail round hole, the push plate structure has no signal when the shell assembly moves and separates, the distance is close when the magnet is separated, a separation signal is obtained by measuring the lead led out by the reed switch through the guide rail round hole, and the remote measurement function of unlocking and separating in an intensive mode is achieved.
Drawings
FIG. 1 is a schematic structural view of an ejection type connection and separation integrated device provided by the invention;
FIG. 2 is a schematic view of the position relationship between the integrated connection and separation device and the satellite and the carrying support cabin;
FIG. 3 is a schematic structural view of a housing assembly provided by the present invention;
FIG. 4 is a schematic diagram of the position of the reed switch provided by the invention;
FIG. 5 is a schematic structural diagram of a push plate assembly provided by the present invention;
FIG. 6 is a schematic diagram of the position of the magnet provided by the present invention;
FIG. 7 is a schematic structural diagram of a connecting and unlocking device provided by the invention;
Detailed Description
A launch type connecting and separating integrated device belongs to connecting and separating devices in the field of satellite-rocket separation and other related connecting and separating, and mainly comprises a shell assembly 1, a push plate assembly 2, a telemetering device 3 and a connecting and unlocking device 4, wherein the shell assembly 1 comprises a first guide rail 1-1, a second guide rail 1-2, a left skin 1-3, a right skin 1-4, an upper skin 1-5, a lower skin 1-6, a rear end cover 1-7, a door frame 1-8 and a positioning pin 1-9;
the push plate component 2 comprises a front baffle 2-1, a rear baffle 2-2, a first guide column 2-3, a second guide column 2-4, a reinforcing column 2-5, a spring cylinder 2-6, a side baffle 2-7, a separating spring 2-8 and a pressing block 2-9;
the remote measuring device 3 comprises a reed switch 3-1 and a magnet 3-2;
the connecting and unlocking device 4 comprises an adapter cylinder 4-1, an explosive bolt 4-2, a ball pad 4-3, a backing plate 4-4, a square nut 4-5, a stainless steel plate 4-6, a magnesium alloy plate 4-7, an epoxy glass plate 4-8, a honeycomb 4-9, a rubber plate 4-10 and an explosive bolt protective cover 4-11;
the satellite positioning device comprises a shell assembly 1, a satellite, a connecting unlocking device 4, a push plate assembly 2, a remote measuring device 3 and a separation signal, wherein the shell assembly 1 is tightly connected to a satellite supporting cabin, the satellite is locked and placed in the shell assembly 1 through the connecting unlocking device 4 in an initial state, the unlocking device 4 is connected to unlock after the satellite enters an orbit, the push plate assembly 2 is used for pushing the satellite to be outwards ejected from the shell assembly 1 and is arranged in the shell assembly 1 and is in contact with the satellite, and the remote measuring device 3 sends an unlocking signal to the connecting unlocking device 4 under the.
The shell assembly 1 is a box structure formed by a left skin 1-3, a right skin 1-4, an upper skin 1-5, a lower skin 1-6, a rear end cover 1-7 and a door frame 1-8 through fasteners, the size and the shape of the space of the box structure can be manufactured according to the shape and the volume of a satellite, the development period of machining the shell by adopting a plate machine is short, and the box structure can quickly adapt to the requirement of the satellite; the door frame can be adapted to and processed according to the angle of the carrying support cabin, so that the satellite can fully utilize the space position between the fairing and the support cabin, and the space utilization rate is improved;
positioning pins 1-9 which are connected with a satellite in a matching way are arranged on the door frames 1-8, a first guide rail 1-1 and a second guide rail 1-2 are arranged on the inner side of the box body structure and used for the push plate assembly 2 to slide, and the door frames 1-8 and the lower skin 1-6 are connected to the satellite supporting cabin through fasteners; the number of the fasteners is not limited, and the number and the positions of the fasteners can be determined according to the size and the stress of the shell assembly, so that the separation device is fixed on the carrying support cabin.
The first guide rail 1-1 and the second guide rail 1-2 are fixed on the inner side of an upper skin 1-5 and the inner side of a lower skin 1-6 through fasteners and are fixed on four corners of an inner cavity of the shell assembly 1 through fasteners, the first guide rail 1-1 and the second guide rail 1-2 are designed into semi-hollow shapes and used for placing a reed switch 3-1 of the telemetering device 3, and round holes are designed on the second guide rail 1-2 and used for leading out a lead of the reed switch 3-1 and communicating with a telemetering carrying signal.
The door frame 1-8 and the lower skin 1-6 are provided with bulges which play a role in limiting the front baffle plate 2-1 of the push plate component 2, the positioning pins 1-9 are arranged on the door frame 1-8 through threaded holes, the front ends are designed into a convex conical pin form, and the convex conical pin is matched with a concave conical pin of a satellite to bear the transverse and longitudinal load of the satellite; the rear end is designed into a hexagonal shape, the position can be adjusted back and forth to complete position matching with the satellite, and the positioning pin can be pushed to the satellite through screwing the positioning pin by a wrench and has certain force action.
The front baffle 2-1, the rear baffle 2-2, the first guide column 2-3, the second guide column 2-4, the reinforcing column 2-5, the spring cylinder 2-6 and the side baffle 2-7 are fixed through fasteners to form a rectangular flat plate push plate structure, the rear end cover 1-7 is provided with a through hole, and the through hole is respectively connected with the pressing block 2-9 and the reinforcing column 2-5 through the fasteners, so that the mounting of the spring is realized, the push plate assembly 2 is folded during the satellite mounting, and the mounting is convenient; the first guide post 2-3, the second guide post 2-4, the reinforcing post 2-5, the spring cylinder 2-6 and the side baffle 2-7 are all arranged on the front baffle 2-1, the rear baffle 2-2 is in contact with the rear end cover 1-7, the rear end of the separation spring 2-8 is respectively fixed at four vertex angles of the rear end cover 1-7 through pressing blocks 2-9, the front end of the separation spring 2-8 is in contact with the bottom surface of the satellite and is matched with the satellite to prop against the push plate structure through the spring cylinder 2-6, the first guide post 2-3, the second guide post 2-4, the reinforcing post 2-5 and the side baffle 2-7 which are arranged on the rear baffle 2-2 at the rear end of the push plate structure, and the push plate structure is in contact with the bottom surface of the satellite and is matched with the first guide rail 1-1 along the directions of the first guide post 2-3 and the second guide post 2-4, The second guide rail 1-2 slides in a matching way;
the rear end covers 1-7 are provided with threaded holes which are pressed against the push plate component 2 through fasteners, so that physical restraint on a satellite is realized; the rear end cover 1-7 is provided with a through hole which penetrates through the explosive bolt 4-2 and is connected with a satellite, the through hole is far away from the satellite end and is designed with a ball pad 4-3 to play a role in preventing the explosive bolt 4-2 from being clamped when being screwed, and the through hole is close to the satellite end and is designed with a frustum to play a role in bearing the load of the satellite, so that the explosive bolt 4-2 is reliably connected; the rear end cover 1-7 is provided with a threaded hole connected with the explosive bolt protective cover 4-11, so that no excess can be collected after the explosive bolt 4-2 is detonated.
The separation springs 2-8 push guide cylinder rings consisting of the reinforcement columns 2-5, the spring cylinders 2-6 and the side baffles 2-7 in the push plate assembly 2 to slide, and bulges are arranged on the first guide columns 2-3, the second guide columns 2-4, the door frames 1-8 and the lower skins 1-6 in the sliding direction and used for limiting the push plate assembly 2.
The front end of the separation spring 2-8 realizes the guiding through the spring cylinder 2-6, the guide post, the reinforcing post 2-5, the side baffle 2-7 and the push plate structure, the rear end of the push plate structure is propped against the separation spring 2-8, the front end is contacted with the bottom surface of the satellite, the periphery is smoothly matched with the guide rail through the guide post made of material with small friction coefficient, and the friction efficiency can be improved; the push plate component 2 can work within the full travel range of each guide rail under the action of the separation springs 2-8, so that clamping stagnation in the separation process is prevented, and the effect of improving reliability in the satellite separation process is realized; a round hole which is large enough is designed in the middle of the front baffle 2-1 and the rear baffle 2-2 of the push plate structure, so that the connecting and unlocking device 4 can penetrate through the push plate structure to be fixed with the bottom surface of the satellite and ensure the separation safety distance when the separation is carried out; the second guide column 2-4 of the push plate structure is provided with a round hole for placing the magnet 3-2 of the telemetering device 3, and forms a magnetic field effect with the reed pipe 3-1 to be used as a telemetering signal in a resistance mode.
When the satellite is locked, the pressing position of the push plate structure and the limiting position of the push plate structure when the satellite is separated are determined, the reed pipe 3-1 of the remote measuring device 3 is arranged at the front end and the rear end in the semi-hollow inner cavity of the second guide rail 1-2 through glue, the magnet 3-2 of the remote measuring device 3 is arranged in the second guide column 2-4, the distance between the magnet 3-2 in the second guide post 2-4 and the reed switch 3-1 in the second guide rail 1-2 is close when the locking is carried out, a lead led out from the reed pipe 3-1 is measured through a round hole of the second guide rail 1-2 to obtain a compaction signal, the push plate structure has no signal in the moving and separating process of the shell component 1, when the distance is close during separation, a separation signal is obtained by measuring a lead led out from the reed pipe 3-1 through the round hole of the second guide rail 1-2, and the functions of real-time unlocking and separation remote measurement are achieved.
The connecting and unlocking device 4 is positioned in the center of the rear end cover 1-7, the central circular holes in the front baffle plate 2-1 and the rear baffle plate 2-2, the shell component 1 is connected with the satellite base, and the explosion bolt 4-2 penetrates through the ball pad 4-3 and the rear end cover 1-7 to be in threaded connection with the square nut 4-5 placed in the adapter cylinder 4-1, so that locking is realized; 4-6 parts of stainless steel plate, 4-7 parts of magnesium alloy plate, 4-8 parts of epoxy glass plate, 4-9 parts of honeycomb and 4-10 parts of rubber plate play a role in reducing impact, and 4-3 parts of ball pad play a role in guiding and positioning; honeycomb 4-9 and a rubber plate 4-10 are placed in an adapter cylinder 4-1 connected with an unlocking device 4, and honeycomb 4-9 is placed in an explosion bolt protective cover 4-11, so that the effect of reducing impact is realized;
in the connecting and unlocking device 4, an explosion bolt 4-2 penetrates through a ball pad 4-3 and a rear end cover 1-7 to be in threaded connection and locking with a square nut 4-5 arranged in an adapter cylinder 4-1; 4-6 parts of a stainless steel plate, 4-7 parts of a magnesium alloy plate, 4-8 parts of an epoxy glass plate, 4-9 parts of a honeycomb and 4-10 parts of a rubber plate are all arranged at the bottom of an adapter cylinder 4-1 and used for reducing the impact effect of a satellite, a ball pad 4-3 is arranged on a front baffle plate 2-1 and used for guiding and positioning, 4-9 parts of the honeycomb and 4-10 parts of the rubber plate are arranged in the adapter cylinder 4-1, and an explosion bolt protective cover 4-11 is arranged at the outer side of an explosion bolt 4-2 and used for protecting the explosion bolt 4-2;
when the satellite is locked, pre-tightening force is applied to the blasting bolt 4-2, pre-tightening force is applied to the positioning pin 1-9, so that the satellite is reliably connected and locked with the separating device under the common supporting action of the positioning pin 1-9 of the rear end cover 1-7 of the satellite, the blasting bolt 4-2 is detonated when the satellite is in orbit, the connecting and unlocking device 4 is unlocked, and the satellite slides out of the shell assembly 1 along the first guide rail 1-1 and the second guide rail 1-2 to realize satellite separation under the action of the separating spring 2-8 and the push plate assembly 2;
the integral device of the ejection type connection and separation integrated device is similar to an L-shaped device, can adapt to the space between a fairing and a supporting cabin of a satellite carrying space, and improves the space utilization rate; the separation device shell assembly 1 can be quickly adapted according to the satellite configuration so as to meet the requirement of quick launching; the satellite passes through the common supporting form of the frustum of the rear end cover 1-7 of the separating device and the positioning pin 1-9, and the arrangement form can effectively reduce the number of the connecting and separating devices, thereby reducing initiating explosive devices and realizing smaller impact.
The following is further illustrated with reference to specific examples:
as shown in fig. 1 to 7, the ejection type connection and separation integrated device is composed of a shell assembly 1, a push plate assembly 2, a remote measuring device 3 and a connection unlocking device 4, the separation integrated device is installed on a carrier rocket supporting cabin, a satellite is initially locked and placed in the shell assembly 1 through the connection unlocking device 4, the connection unlocking device 4 is unlocked after the satellite enters an orbit, the satellite is ejected out of the shell assembly 1 under the action of the push plate assembly 2 to realize satellite and rocket separation, and the remote measuring device 3 provides unlocking and separation signals.
The separation spring 2-8 is mounted on a rear end cover 1-7 of the shell assembly 1 through a pressing block 2-9, a first guide column 2-3 and a second guide column 2-4 of the push plate assembly 2 are matched with a first guide rail 1-1 and a second guide rail 1-2 of the shell assembly 1 to enable the push plate assembly to slide, and the separation spring 2-8 pushes against a guide cylinder ring consisting of a reinforcing column 2-5, a spring cylinder 2-6 and a side baffle 2-7 in the push plate assembly 2 to enable the push plate assembly to slide within a certain range by means of the protrusion of a door frame 1-8 and a lower skin 1-6 of the shell assembly 1 and the protrusion of the first guide column 2-3 and the second guide column 2-4.
In the ejection type connection and separation integrated device, a reed switch 3-1 is arranged in a first guide rail 1-1 of a shell assembly 1, a lead is led out, a magnet is arranged in a push plate assembly 2, and the resistance value of the reed switch 3-1 is changed through the magnetic field effect of the magnet 3-2 and the reed switch 3-1, so that the reed switch can be used as a telemetering signal. The reed pipes 3-1 are respectively arranged at the head end and the tail end of the first guide rail 1-1, and the unlocking signals can be remotely measured through the movement of the push plate component 2;
the ejection type connection and separation integrated device connects and locks the satellite through the connection unlocking device 4, the explosive bolt 4-2 penetrates through the rear end cover 1-7 to be connected with the satellite bottom plate and applies pretightening force, and the positioning pin 1-9 is in contact with the satellite front plate and applies pretightening force to keep certain rigidity, so that the satellite can be locked;
in the ground stage, firstly, the push plate component 2 is pressed to the rear end cover of the shell component 1, the push plate component 2 is restrained through the tension screws on the rear end covers 1-7, then the satellite is placed into the shell component 1 along the guide rail, the explosion bolt 4-2 penetrates through the rear end cover and is screwed with the square nut 4-5, and a certain pre-tightening force is applied to lock the satellite. Removing the tensioning screws on the rear end covers 1-7 to enable the push plate assembly 2 to be in contact with the satellite bottom plate under the action of spring force, and screwing the jacking screws on the rear end covers 1-7 to enable the push plate assembly 2 to be in contact with the satellite bottom plate under the action of the jacking screws to achieve constraint of the satellite; the positioning pin is adjusted to move back and forth by screwing the hexagonal columns at the rear ends of the positioning pins 1-9 so as to be in close contact with the conical surface of the satellite, and a certain pretightening force is applied to keep the satellite at a certain rigidity. And finally, connecting the explosive bolt 4-2 with a conductor of the carrier rocket through a cable connector, and connecting a telemetered reed switch 3-1 conductor with the conductor of the carrier rocket, so as to realize the functions of unlocking and telemetering the ejection type connection and separation integrated device by the carrier rocket. As the reed switches 3-1 are positioned at the front end and the rear end of the separating device, the satellite is mechanically connected with the separating device through the explosion bolts 4-2, the distance between the reed switch 3-1 and the guide rail magnet 3-2 is close, and the closed loop resistance value detected when two wires led out from the reed switch 3-1 are connected to the carrier rocket is smaller and is used as a locking signal
The satellite is locked by an explosive bolt 4-2 connected with an unlocking device 4, and under the supporting action of a rear end cover frustum and a positioning pin 1-9 frustum, external load is resisted, and reliable locking in the launching stage is realized.
After the last sub-stage of the rocket enters the orbit, the carrier rocket supplies current to the explosive bolt 4-2 through a conducting wire and an electrical interface cable, so that the separating device is unlocked, the satellite is pushed out along the guide rail under the action of the spring and the push plate structure until the push plate structure slides to the limit position, namely the push plate structure is limited by the separating device, the satellite is pushed out of the separating device, and the mutual separation of the satellite and the separating device is completed. In the pushing-out process, when the push plate structure slides to the middle position of the separating device, the lead led out from the reed pipe 3-1 is infinite at the moment; when the push plate structure slides to the limit position, the distance between the reed pipe 3-1 and the guide rail magnet 3-2 is close, and the closed loop resistance value detected when two wires led out from the reed pipe 3-1 are connected to a carrier rocket is smaller and serves as a separation signal.
The present invention has been described in terms of the specific embodiments, which are provided for the purpose of illustration and not for the purpose of limitation, and it is intended that all changes and modifications which can be made by one skilled in the art and which are within the spirit of the invention and the scope of the invention include all modifications and equivalents thereof without departing from the spirit and scope of the invention.
Claims (10)
1. The utility model provides a launch formula connection separation integrated device which characterized in that: including casing subassembly (1), push pedal subassembly (2), telemetering measurement device (3), connect unlocking device (4), casing subassembly (1) fastening connection is on the satellite supports the cabin, and the satellite is locked and is placed in casing subassembly (1) through connecting unlocking device (4) under the initial condition, connects unlocking device (4) unblock after the satellite orbit-in for push pedal subassembly (2) that promote the satellite to launch by casing subassembly (1) outside set up in casing subassembly (1) and contact with the satellite, telemetering measurement device (3) send the unblock signal to connecting unlocking device (4) under ground control station control, and send the separation signal to push pedal subassembly (2).
2. The ejection type integrated connecting and separating device of claim 1, wherein: the shell assembly (1) comprises a first guide rail (1-1), a second guide rail (1-2), a left side skin (1-3), a right side skin (1-4), an upper skin (1-5), a lower skin (1-6), a rear end cover (1-7), a door frame (1-8) and a positioning pin (1-9), wherein the left side skin (1-3) and the right side skin (1-4) are same trapezoidal structural skins, the upper skin (1-5) and the lower skin (1-6) are rectangular structural skins, the left side skin (1-3), the right side skin (1-4), the upper skin (1-5) and the lower skin (1-6) are fixed through the door frame (1-8) and form a box body structure of a trapezoidal body through the rear end cover (1-7), the positioning pin (1-9) which is connected with the satellite in a matched mode is arranged on the door frame (1-8), the first guide rail (1-1) and the second guide rail (1-2) are arranged on the inner side of the box body structure and used for enabling the push plate assembly (2) to slide, and the door frame (1-8) and the lower skin (1-6) are connected to the satellite supporting cabin through fasteners.
3. The ejection type integrated connecting and separating device of claim 2, wherein: the first guide rail (1-1) and the second guide rail (1-2) are fixed on the inner sides of the upper skins (1-5) and the inner sides of the lower skins (1-6) through fasteners and are semi-hollow guide rails.
4. The ejection type integrated connecting and separating device of claim 3, wherein: the push plate component (2) comprises a front baffle (2-1), a rear baffle (2-2), a first guide column (2-3), a second guide column (2-4), a reinforcing column (2-5), a spring cylinder (2-6), a side baffle (2-7), a separating spring (2-8) and a pressing block (2-9), wherein the front baffle (2-1), the rear baffle (2-2), the first guide column (2-3), the second guide column (2-4), the reinforcing column (2-5), the spring cylinder (2-6) and the side baffle (2-7) are fixed through fasteners to form a rectangular flat plate push plate structure, the rear end cover (1-7) is provided with through holes, and the through holes are respectively connected with the pressing block (2-9) and the reinforcing column (2-5) through fasteners, the first guide column (2-3), the second guide column (2-4), the reinforcing column (2-5), the spring cylinder (2-6) and the side baffle (2-7) are all arranged on the front baffle (2-1), the rear baffle (2-2) is in contact with the rear end cover (1-7), the rear end of the separation spring (2-8) is respectively fixed at four vertex angles of the rear end cover (1-7) through pressing blocks (2-9), the front end of the separation spring (2-8) is arranged on the rear baffle (2-2) at the rear end of the push plate structure through the spring cylinder (2-6), the first guide column (2-3), the second guide column (2-4), the reinforcing column (2-5) and the side baffle (2-7) to prop against the push plate structure, the push plate structure is in contact with the bottom surface of the satellite and is matched with the satellite along the first guide column (2-3), The second guide post (2-4) is matched with the first guide rail (1-1) and the second guide rail (1-2) to slide in the direction.
5. The ejection type integrated connecting and separating device of claim 4, wherein: the separation spring (2-8) pushes a guide cylinder ring composed of a reinforcing column (2-5), a spring cylinder (2-6) and a side baffle (2-7) in the push plate assembly (2) to slide, and bulges are arranged on the first guide column (2-3), the second guide column (2-4), the door frame (1-8) and the lower skin (1-6) in the sliding direction and used for limiting the push plate assembly (2).
6. The ejection type integrated connecting and separating device of claim 5, wherein: the telemetering device (3) comprises a reed switch (3-1) and a magnet (3-2), a round hole is designed on the second guide column (2-4), used for placing the magnet (3-2), the second guide rail (1-2) is provided with a round hole for leading out a lead of the reed pipe (3-1), the reed switch (3-1) is arranged at the front end and the rear end in the semi-hollow inner cavity of the second guide rail (1-2) through glue, the distance between the magnet (3-2) and the reed switch (3-1) is close when the reed switch is locked, a lead led out from the reed pipe (3-1) is measured through a round hole of the second guide rail (1-2) to obtain a pressing signal, and in the separation process of the satellite and the shell assembly (1), a lead led out of the reed pipe (3-1) is measured through a round hole of the second guide rail (1-2) to obtain a separation signal so as to realize real-time unlocking and separation remote measurement.
7. The ejection type integrated connecting and separating device of claim 6, wherein: and central round holes are formed in the front baffle (2-1) and the rear baffle (2-2) and used for the connection unlocking device (4) to penetrate through and be fixed with the satellite ground.
8. The integrated catapult-type connecting and disconnecting device according to claim 7, wherein: the connection unlocking device (4) is arranged in the center of the rear end cover (1-7), passes through the shell component (1) and penetrates through a central circular hole of the push plate component (2) to be connected with the satellite base, and comprises an adapter cylinder (4-1), an explosion bolt (4-2), a ball pad (4-3), a base plate (4-4), a square nut (4-5), a stainless steel plate (4-6), a magnesium alloy plate (4-7), an epoxy glass plate (4-8), a honeycomb (4-9), a rubber plate (4-10) and an explosion bolt protective cover (4-11), wherein the explosion bolt (4-2) penetrates through the ball pad (4-3), and the rear end cover (1-7) and the square nut (4-5) placed in the adapter cylinder (4-1) to be in threaded connection and locked; the anti-corrosion device is characterized in that the stainless steel plate (4-6), the magnesium alloy plate (4-7), the epoxy glass plate (4-8), the honeycomb (4-9) and the rubber plate (4-10) are arranged at the bottom of the adapter cylinder (4-1) and used for reducing the impact effect of a satellite, the ball pad (4-3) is arranged on the front baffle plate (2-1) and used for guiding and positioning, the honeycomb (4-9) and the rubber plate (4-10) are arranged in the adapter cylinder (4-1), and the explosion bolt protective cover (4-11) is arranged on the outer side of the explosion bolt (4-2) and used for protecting the explosion bolt (4-2).
9. The integrated catapult-type connecting and disconnecting device according to claim 8, wherein: when the satellite is locked, pretightening force is applied to the explosion bolt (4-2), pretightening force is applied to the positioning pin (1-9), so that the satellite is reliably connected and locked with the separation device under the common supporting action of the positioning pin (1-9) of the rear end cover (1-7), the explosion bolt (4-2) detonates when the satellite is in orbit, the connection unlocking device (4) is unlocked, and the satellite slides out of the shell assembly (1) along the first guide rail (1-1) and the second guide rail (1-2) to separate the satellite under the action of the separation spring (2-8) and the push plate assembly (2).
10. The integrated catapult-type connecting and disconnecting device according to claim 9, wherein: the space of the shell component (1) is determined and manufactured according to the shape and the volume of the satellite, the shell is machined by adopting a plate machine, and the door frames (1-8) are machined according to the angle of the carrying support cabin.
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| CN202011181754.3A CN112319867B (en) | 2020-10-29 | 2020-10-29 | Ejection type connecting and separating integrated device |
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| CN112319867B CN112319867B (en) | 2022-05-31 |
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| CN112319867B (en) | 2022-05-31 |
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