Explosive bolt collecting device, aerospace craft separation system and aerospace craft

Abstract

The invention provides an explosive bolt collecting device, an aerospace craft separation system and an aerospace craft, the collecting device is installed on a separation body of the aerospace craft, the collecting device is provided with a collecting hole, the collecting hole is provided with a collecting opening, and the collecting hole extends inwards from the collecting opening in the first direction; wherein the sectional area of the collecting hole is gradually reduced in the first direction. When the separated body of the aerospace craft is separated, the explosive bolt is detonated, the broken connecting piece flying out of the explosive bolt at a high speed moves in the collecting hole in the first direction, the broken connecting piece of the explosive bolt extrudes the inner wall face of the collecting hole to form self-locking, the broken connecting piece cannot rebound, and the risk that normal work of other equipment is affected is reduced; and meanwhile, the risk that the broken connecting piece rebounds back to the mounting hole of the explosive bolt is reduced, the separation system is high in working reliability, and smooth and safe separation of the separated body of the aerospace craft is facilitated.

Description

Technical Field

[0001] The present application relates to the field of aerospace vehicle separation technology, and in particular to a collection device for explosive bolts, an aerospace vehicle separation system and an aerospace vehicle. Background Art

[0002] Separation technology is an important technology for rockets and other spacecraft to complete corresponding load tasks. Separation technology can be achieved through a separation unlocking device, which is widely used in multi-stage spacecraft represented by launch vehicles. Before receiving the output of the signal conversion device, the separation unlocking device connects the two structural parts to be separated together; after receiving the output of the signal conversion device, the two structural parts connected to each other are disconnected. For example, the separation of the fairing or the separation between rocket stages requires the use of a separation unlocking device.

[0003] At present, the most commonly used separation and unlocking device is the separation pyrotechnics, and the explosive bolt is widely used as a separation pyrotechnics. When the explosive bolt is detonated, there is a great impact force, and after detonation, the screw connected to one end of the fastening nut will be sheared off, and the sheared screw will fly out at high speed like a bullet. In order to prevent the sheared screw from hitting other equipment, a collection box is set in the flight direction of the sheared screw. When the explosive bolt is detonated, the sheared screw flies into the collection box for collection.

[0004] However, in the prior art, when the shear screw flies out at high speed and enters the collection box, it will hit the bottom of the collection box and rebound repeatedly until the energy is consumed and stored in the collection box. When the shear screw rebounds in the collection box, there are multiple high-frequency impacts. If the electrical equipment of the rocket is close to the collection box, there is a risk of affecting the normal operation of the electrical equipment; at the same time, if the shear screw rebounds, it will rebound back to the installation hole of the explosive bolt, which will generate additional interference torque on the separation body, causing separation failure and immeasurable consequences. Summary of the invention

[0005] The present application provides a collection device for explosive bolts, a spacecraft separation system and a spacecraft. When the explosive bolt is detonated, the broken connector that flies out of the explosive bolt at high speed moves in a first direction in the collection hole of the collection device, squeezes the inner wall surface of the collection hole and forms a self-locking function. The broken connector will not rebound, thereby reducing the risk of high-frequency impact caused by the rebound affecting the normal operation of other equipment. At the same time, the risk of the broken connector rebounding back to the installation hole of the explosive bolt and interfering with the separation body is reduced, which is conducive to the smooth separation of the separation body of the spacecraft.

[0006] In order to achieve the above objectives, this application adopts the following technical solutions: In a first aspect, the present application provides a collection device for explosive bolts, wherein the collection device is provided with a collection hole, the collection hole has a collection opening, and the collection hole extends inwardly from the collection opening along a first direction; Wherein, along the first direction, the cross-sectional area of ​​the collecting hole gradually decreases; When the explosive bolt is detonated, the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

[0007] In some possible implementations, the cross-sectional shape of the collecting hole is circular, square, trapezoidal, or triangular.

[0008] In some possible implementations, the collecting hole is a conical hole, the semi-conical angle of the conical hole is A, and 3.5°≤A≤7°.

[0009] In some possible implementations, when the broken connecting pieces of the explosive bolt squeeze the inner wall surface of the collecting hole to form self-locking, all of the broken connecting pieces of the explosive bolt are located in the collecting hole.

[0010] In some possible implementations, the collecting device includes a collecting piece, the collecting piece is provided with a collecting hole, and the collecting piece is made of polytetrafluoroethylene material, polycarbonate material, or polypropylene material.

[0011] In some possible implementations, the collecting device includes a collecting piece and a containing piece, the collecting piece is provided with a collecting hole, the containing piece is provided with a containing cavity with an opening on one side, the collecting piece is installed in the containing cavity, and the collecting port of the collecting piece faces outside the containing cavity.

[0012] In some possible implementations, the collecting member and the receiving member are clearance-fitted.

[0013] In some possible implementations, the receiving member is a metal member.

[0014] A second aspect of the present application provides a spacecraft separation system, the separation system comprising: The collecting device as described in the first aspect above; Explosive Bolts: Wherein, the collecting device is used to collect the broken connecting parts of the explosive bolts; When the explosive bolt is detonated, the connecting piece of the explosive bolt breaks, and the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

[0015] A third aspect of the present application provides a spacecraft, the spacecraft comprising: a first separated body and a second separated body; The separation system described in the second aspect above; The first separation body and the second separation body are connected by an explosive bolt, the collecting device is installed on the second separation body, and the connecting piece of the explosive bolt extends into the collecting hole through the collecting port; When the explosive bolt is detonated, the connecting piece of the explosive bolt breaks, and the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

[0016] In some possible implementations, the axis of the explosive bolt coincides with the axis of the collecting hole of the collecting device.

[0017] It can be seen from the above technical solution that the present application has at least the following beneficial effects: The present application provides a collection device for explosive bolts, a spacecraft separation system and a spacecraft, wherein the collection device is installed on a separation body of the spacecraft, and when the explosive bolt is detonated, the broken connecting piece of the explosive bolt flies out at high speed and enters the collection hole of the collection device and moves in a first direction in the collection hole, thereby squeezing the inner wall surface of the collection hole. After the inner wall of the collection hole is squeezed and deformed, the kinetic energy of the high-speed broken connecting piece is absorbed, and the broken connecting piece rubs against the inner wall surface of the collection hole to form a self-locking, and the broken connecting piece will not rebound, thereby reducing the secondary or multiple impacts caused by the detonation of the explosive bolt, thereby reducing the high-frequency impact caused by the rebound and the influence of the high-frequency impact on the broken connecting piece. The risk of other equipment working normally is reduced, and the risk of broken connectors rebounding back to the mounting hole of the explosive bolt and interfering with the separation body is reduced, which is conducive to the smooth separation of the separation body of the aerospace vehicle; moreover, when the broken connectors form self-locking in the collecting hole, all the broken connectors are located in the collecting hole, that is, the broken connectors can both form self-locking in the collecting hole and be completely collected in the collecting hole. The complete collection of the broken connectors of the explosive bolt can be achieved through the simple collecting device in this embodiment without adding other components. The collecting device has a simple structure and a low manufacturing cost, which improves the flexibility of the design of the separation system of the aerospace vehicle.

[0018] It should be understood that the description of technical features, technical solutions, beneficial effects or similar language in this application does not imply that all features and advantages can be realized in any single embodiment. On the contrary, it is understood that the description of features or beneficial effects means that specific technical features, technical solutions or beneficial effects are included in at least one embodiment. Therefore, the description of technical features, technical solutions or beneficial effects in this specification does not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions and beneficial effects described in the present embodiment can also be combined in any appropriate manner. Those skilled in the art will understand that the embodiment can be realized without one or more specific technical features, technical solutions or beneficial effects of a specific embodiment. In other embodiments, additional technical features and beneficial effects can also be identified in a specific embodiment that does not embody all embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A cross-sectional view of a collection device provided in the present application in a specific embodiment; Figure 2 A partial cross-sectional view of a spacecraft in a specific embodiment provided by the present application, wherein the first separation body and the second separation body are in a connected state; Figure 3 A schematic diagram of the structure of an explosive bolt provided in the present application in a specific embodiment; Figure 4 A front view of a fastening nut provided in the present application in a specific embodiment; Figure 5 This is a schematic diagram of a broken connecting piece of an explosive bolt forming self-locking in a collecting hole of a collecting device in a specific embodiment of the present application.

[0020] Figure markings: 10-collecting device; 11-collecting hole; 111-collecting port; 12-collecting piece; 13-containing piece; 20-explosive bolt; 21-connecting piece; 211-screw; 212-fastening nut; 22-nut part; 23-screw; 30-first separation body; 40-second separation body; 41-screw assembly pressure plate; X-first direction. DETAILED DESCRIPTION

[0021] The terms "first", "second", "third", etc. in the specification of this application and the accompanying drawings are used to distinguish different objects rather than to limit a specific order.

[0022] In the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific way.

[0023] Separation technology is an important technology for rockets and other spacecraft to complete corresponding load missions. Separation systems are widely used in multi-stage spacecraft represented by launch vehicles. The high reliability of the separation system is a crucial condition to ensure the complete success of flight test missions and is an important part of spacecraft design.

[0024] The separation device is a device that connects the sections (or structural parts) to be separated before receiving the output of the signal conversion device; after receiving the output of the signal conversion device, it releases the connection relationship (also called unlocking) of the sections (or structural parts) connected to each other, also known as a separation unlocking device. At present, the most commonly used separation unlocking devices are explosive bolts, cutting locks, etc.

[0025] Explosive bolts are a widely used separation and unlocking device. For example, in rocket systems, they are used in fairing separation and rocket stage separation. When explosive bolts are used as separation and unlocking devices, there is a large impact force when the explosive bolts are detonated. After detonation, the screw connected to one end of the fastening nut will be cut off. The cut screw will fly out at high speed like a bullet, with a flying speed of about 200m / s~300m / s. The high-speed flying screw needs to be collected, otherwise the screw will hit other equipment in the rocket cabin, causing fatal damage to the equipment in the rocket cabin; on the other hand, if the screw hits a flat hard metal object, there is a risk of rebounding back to the explosive bolt installation hole, causing separation interference force and affecting the normal separation of the rocket.

[0026] Therefore, when using explosive bolts as separation pyrotechnics, it is necessary to design a collection box for the shear screws of the explosive bolts. Conventional collection boxes are often designed in the shape of square boxes or cylindrical boxes. When the explosive bolts are detonated, the shear screws fly into the collection box for collection. When the shear screws enter the collection box, they will hit the bottom of the collection box and rebound repeatedly until the energy is consumed and stored in the collection box.

[0027] When the shear screw rebounds in the collection box in the prior art, there are multiple high-frequency impacts. If the electrical equipment of the rocket is close to the collection box, there is a risk of affecting the normal operation of the electrical equipment. At the same time, when the shear screw rebounds, it rebounds back to the mounting hole of the explosive bolt, which will generate additional interference torque on the separation body, causing separation failure and immeasurable consequences.

[0028] In view of this, the embodiments of the present application provide a collection device for explosive bolts, a spacecraft separation system and a spacecraft, wherein the collection device is installed on the separation body of the spacecraft, and when the explosive bolt is detonated, the broken connector that flies out of the explosive bolt at high speed enters the collection hole of the collection device and moves in the collection hole along a first direction, squeezing the inner wall surface of the collection hole. After the inner wall of the collection hole is squeezed and deformed, the kinetic energy of the high-speed broken connector is absorbed, and the broken connector rubs against the inner wall surface of the collection hole to form a self-locking, and the broken connector will not rebound, thereby reducing the secondary or multiple impacts caused by the detonation of the explosive bolt, and further reducing the high-frequency impact caused by the rebound. The risk of the broken connectors affecting the normal operation of other equipment is reduced, and the risk of the broken connectors rebounding back to the mounting holes of the explosive bolts and interfering with the separation bodies is reduced, which is conducive to the smooth separation of the separation bodies of the aerospace vehicle. Moreover, when the broken connectors are self-locked in the collecting holes, all the broken connectors are located in the collecting holes, that is, the broken connectors can be self-locked in the collecting holes and can be completely collected in the collecting holes. The complete collection of the broken connectors of the explosive bolts can be achieved through the simple collecting device in this embodiment without adding other components. The collecting device has a simple structure and a low manufacturing cost, which improves the flexibility of the design of the separation system of the aerospace vehicle.

[0029] In the first aspect, the collection device 10 of the explosive bolt 20 provided in the embodiment of the present application is introduced. Figure 1 As shown, the collecting device 10 is provided with a collecting hole 11, and the collecting hole 11 has a collecting port 111, and the collecting hole 11 extends inwardly from the collecting port 111 along the first direction X; wherein, along the first direction X, the cross-sectional area of ​​the collecting hole 11 gradually decreases; Figure 2 When the explosive bolt 20 is detonated, the broken connecting piece of the explosive bolt 20 moves in the collecting hole 11 along the first direction X, and the broken connecting piece of the explosive bolt 20 squeezes the inner wall surface of the collecting hole 11 to form a self-locking.

[0030] The collecting device 10 is applied to a spacecraft. Figure 2 A partial structural schematic diagram of a first separation body 30 and a second separation body 40 of a spacecraft in a specific embodiment is shown, wherein the first separation body 30 and the second separation body 40 are connected by an explosive bolt 20, a collecting device 10 is installed on the second separation body 40, and a connecting piece 21 of the explosive bolt 20 extends into the collecting hole 11 through a collecting port 111.

[0031] The explosive bolt 20 includes a nut portion 22 and a connecting member 21. The connecting member 21 may include a screw rod 211 and a fastening nut 212. A weak structure is provided between the nut portion 22 and the screw rod 211. Figure 2In the embodiment shown, the installation process of the explosive bolt 20 and the collecting device 10 is as follows: the nut portion 22 is fixedly connected to the first separation body 30 by means of the screw 23, and the screw rod 211 passes through the first through hole of the first separation body 30 and the second through hole of the second separation body 40; the fastening nut 212 is connected to the end of the screw rod 211 away from the nut portion 22, so that the first separation body 30 and the second separation body 40 are connected, and at this time, the fastening nut 212 is located in the mounting groove of the second separation body 40; the collecting port 111 of the collecting hole 11 of the collecting device 10 is installed into the mounting groove of the second separation body 40 in a manner facing the explosive bolt 20, and at this time, the connecting piece of the explosive bolt 20 extends into the collecting hole 11 through the collecting port 111, that is, the screw rod 211 and the fastening nut 212 are located in the collecting hole 11; the screw assembly pressure plate 41 is fixed on one side of the notch of the mounting groove, and the screw assembly pressure plate 41 restricts the collecting device 10 in the mounting groove.

[0032] The fastening nut 212 may be a self-locking nut.

[0033] When the first separation body 30 and the second separation body 40 are separated, the explosive bolt 20 is detonated. Under the energy impact generated by the explosion, the connecting piece 21 of the explosive bolt 20 is broken. The broken connecting piece 21 is a broken connecting piece. The broken connecting piece moves at high speed along the first direction X in the collecting hole 11. The broken connecting piece squeezes the inner wall surface of the collecting hole 11. The contact surface between the broken connecting piece and the inner wall of the collecting hole 11 forms an interference fit. The axial compression produces radial elastic deformation of the collecting hole 11, absorbs the kinetic energy of the high-speed broken connecting piece, and forms a positive pressure (normal force) between the contact surface between the broken connecting piece and the inner wall of the collecting hole 11. The broken connecting piece and the inner wall of the collecting hole 11 are self-locked due to the action of friction. The broken connecting piece does not rebound under the action of self-locking. The self-locking function is achieved through the geometric design of the collecting hole 11 and the friction between the broken connecting piece and the collecting hole 11, and no additional locking device is required.

[0034] Specifically, Figure 2 In the illustrated embodiment, the broken connecting piece of the explosive bolt 20 is a broken screw rod 211 and a fastening nut 212 connected to the broken screw rod 211, that is, when the explosive bolt 20 is detonated, under the energy impact generated by the explosion, the weak structure between the nut portion 22 and the screw rod 211 is broken, and the broken screw rod 211 and the fastening nut 212 connected to the broken screw rod 211 fly out at high speed in the first direction X; the broken screw rod 211 and the fastening nut 212 connected to the broken screw rod 211 move at high speed in the first direction X in the collecting hole 11, as shown in FIG. Figure 2In the illustrated embodiment, the fastening nut 212 connected to the broken screw 211 squeezes the inner wall surface of the collecting hole 11, and the contact surface between the fastening nut 212 and the inner wall of the collecting hole 11 forms an interference fit, and the axial compression produces radial elastic deformation of the collecting hole 11, absorbing the kinetic energy of the high-speed broken screw 211 and the fastening nut 212 connected to the broken screw 211, and the contact surface between the fastening nut 212 and the inner wall of the collecting hole 11 forms a positive pressure (normal force), and the fastening nut 212 and the inner wall surface of the collecting hole 11 form a self-locking due to the action of friction, that is, the broken screw 211 and the fastening nut 212 connected to the broken screw 211 stop moving in the collecting hole 11 due to the self-locking effect, and at this time, the broken screw 211 and the fastening nut 212 connected to the broken screw 211 do not rebound under the action of self-locking.

[0035] Among them, the first separation body 30 and the second separation body 40 can be two stages of a rocket, for example, the first separation body 30 is a second-stage rocket, and the second separation body 40 is a first-stage rocket; or, the first separation body 30 is the body of the rocket, and the second separation body 40 is the fairing of the rocket.

[0036] In the embodiment of the present application, when the separation bodies of the aerospace vehicle need to be separated, the explosive bolt 20 is detonated, and the broken connector that flies out of the explosive bolt 20 at high speed enters the collecting hole 11 of the collecting device 10 and moves along the first direction X in the collecting hole 11, squeezing the inner wall surface of the collecting hole 11. After the inner wall of the collecting hole 11 is squeezed and deformed, the kinetic energy of the high-speed broken connector is absorbed, and the broken connector and the inner wall surface of the collecting hole 11 are rubbed to form a self-locking, and the broken connector will not rebound, which effectively reduces the secondary or multiple impacts caused by the detonation of the explosive bolt 20, and thus reduces the risk of high-frequency impact caused by the rebound affecting the normal operation of other equipment, and at the same time reduces the risk of the broken connector rebounding back to the mounting hole of the explosive bolt 20 and interfering with the separation body, which is conducive to the smooth separation of the separation bodies of the aerospace vehicle, and the self-locking function without the need for an additional locking device is achieved through the geometric design of the collecting hole 11 and the friction between the broken connector and the collecting hole 11.

[0037] Specifically, the cross-sectional shape of the collecting hole 11 can be circular, square, trapezoidal or triangular.

[0038] For example, when the cross-sectional shape of the collecting hole is circular, the collecting hole is a conical hole; when the cross-sectional shape of the collecting hole is square, the shape of the collecting hole is similar to a pyramid.

[0039] In a specific embodiment, the collecting hole 11 is a conical hole, and the cross-sectional shape of the collecting hole 11 is circular.

[0040] When the broken connector squeezes the inner wall of the conical hole, the conical hole can be subjected to uniform force, which is less likely to cause stress concentration and reduces the risk of the collecting device 10 being damaged.

[0041] Specifically, the semi-cone angle of the conical hole is A, and 3.5°≤A≤7°.

[0042] The semi-cone angle of the tapered hole is the angle between the generatrix of the tapered hole and the axis.

[0043] The principle of self-locking of the broken connecting piece of the explosive bolt 20 in the tapered hole is to achieve the self-locking function without the need for an additional locking device through the geometric design of the tapered structure and the friction between the materials.

[0044] The principle of self-locking of the conical structure is explained as follows: When two conical surfaces are matched, the size of the semi-cone angle directly affects the self-locking ability. According to the static friction self-locking condition, if the semi-cone angle α satisfies tanα<μ (μ is the friction coefficient, which is the ratio of the friction force generated on the contact surface to the normal pressure), the friction force generated under the action of the axial force is sufficient to resist the loosening tendency and achieve self-locking.

[0045] The friction coefficient between the broken connection piece of the explosive bolt 20 and the tapered hole is generally 0.1-0.15. For example, when the broken connection piece is made of steel and the collecting device 10 is also made of steel, the friction coefficient between the two is about 0.15; when the broken connection piece is made of steel and the collecting device 10 is made of polytetrafluoroethylene, the friction coefficient between the two is about 0.1. When the friction coefficient between the broken connection piece and the tapered hole is 0.15 and the semi-cone angle A of the tapered hole is 7°, tan7°≈0.1228, 0.1228<0.15, and the self-locking condition is met; when the friction coefficient between the broken connection piece and the tapered hole is 0.1 and the semi-cone angle A of the tapered hole is 3.5°, tan3.5°≈0.061, 0.061<0.1, and the self-locking condition is met.

[0046] Furthermore, when the broken connecting pieces of the explosive bolt 20 squeeze the inner wall surface of the collecting hole 11 to form self-locking, all of the broken connecting pieces of the explosive bolt 20 are located in the collecting hole 11 .

[0047] In the present embodiment, the broken connectors can not only form self-locking in the collecting hole 11, but also be completely collected in the collecting hole 11. The complete collection of the broken connectors of the explosive bolts 20 can be achieved through the simple collecting device 10 in the present embodiment without adding other components. The collecting device 10 has a simple structure and a low manufacturing cost, which improves the flexibility of the design of the aerospace vehicle separation system.

[0048] Specifically, the depth of the collecting hole 11 is greater than the length of the broken connecting piece.

[0049] More specifically, when the collecting hole 11 is a tapered hole, the design process of the size of the tapered hole is as follows: The semi-cone angle A of the tapered hole is determined according to the friction coefficient between the broken connecting piece of the explosive bolt 20 and the inner wall surface of the collecting hole 11; the explosive bolt 20 is a standard part, and after selection, the specifications of the explosive bolt 20 and the fastening nut 212 are known quantities; Figure 3 , Figure 4 , Figure 5 As shown, after the fastening nut 212 is connected to the screw rod 211, the distance between the connection between the screw rod 211 and the nut portion 22 and the side of the fastening nut 212 away from the nut portion 22 is L, and the value of L can be calculated based on the specifications of the explosive bolt 20 and the fastening nut 212; and if the diameter d of the circumscribed circle of the fastening nut 212 is known, the diameter D of the collecting port 111 of the tapered hole, that is, the large end diameter D of the tapered hole, can be calculated according to the following formula: D = 2L·tanA+d The depth of the tapered hole is H, H=1.5L~1.8L.

[0050] The semi-cone angle A of the tapered hole, the large end diameter D of the tapered hole, and the depth H of the tapered hole are all determined, and the size design of the tapered hole is completed at this time.

[0051] In a specific embodiment, Figure 1 , Figure 2 As shown, the collecting device 10 includes a collecting member 12 , and the collecting member 12 is provided with a collecting hole 11 . The collecting member 12 is made of polytetrafluoroethylene material, polycarbonate material, or polypropylene material.

[0052] When the collecting piece 12 is made of polytetrafluoroethylene, polycarbonate or polypropylene, the broken connecting piece squeezes the inner wall of the collecting hole 11, and the collecting piece 12 is easy to produce elastic deformation, which is beneficial to ensure the energy absorption effect and the friction between the broken connecting piece and the inner wall of the collecting hole 11.

[0053] For example, the broken connecting piece is made of steel, and the collecting piece 12 is made of polytetrafluoroethylene. During the collection process, after the steel and polytetrafluoroethylene come into contact, an interference fit is formed on the contact surface. Since the Young's modulus of steel is relatively high, the steel is not easy to deform, while polytetrafluoroethylene is easy to produce elastic deformation. The axial compression of steel and polytetrafluoroethylene makes it easy for polytetrafluoroethylene to produce radial elastic deformation, increasing the positive pressure (normal force) of the contact surface, thereby significantly improving the friction and further enhancing the self-locking effect.

[0054] In addition, the collecting member 12 made of polytetrafluoroethylene, polycarbonate or polypropylene is easy to manufacture and has a low manufacturing cost.

[0055] Specifically, Figure 1 , Figure 2The collecting device 10 further includes a container 13, which is provided with a container cavity with one side open, and the collecting member 12 is installed in the container cavity, and the collecting port 111 of the collecting member 12 faces outside the container cavity.

[0056] In this embodiment, when the explosive bolt 20 is detonated, the broken connecting piece of the explosive bolt 20 is sheared off and flies out, moving along the first direction X in the collecting hole 11, squeezing the collecting piece 12 to produce elastic deformation, and the collecting piece 12 transfers the force to the containing piece 13, and the two coordinate the deformation to absorb all the kinetic energy of the broken connecting piece.

[0057] In this embodiment, the collecting member 12 is installed in the containing member 13. When the collecting member 12 is impacted by the broken connecting member, the collecting member 12 and the containing member 13 coordinately deform to absorb all the kinetic energy of the broken connecting member, thereby ensuring the energy absorption effect and the overall strength of the collecting device 10, thereby reducing the risk of the collecting member 12 being damaged under impact.

[0058] like Figure 2 As shown, the cross-sectional shape of the receiving member 13 is U-shaped, and the structure is simple.

[0059] Specifically, the collecting member 12 and the containing member 13 are clearance-fitted.

[0060] Such a configuration is conducive to deformation of the collecting member 12 under the impact of the broken connecting member, thereby improving the energy absorption effect.

[0061] Specifically, the receiving member 13 is a metal member. The receiving member 13 made of metal is easily deformed under impact and is not easily damaged.

[0062] In a specific embodiment, Figure 1 As shown, the collecting piece 12 is a collecting block, which is made of polytetrafluoroethylene material. A single-sided 3.5-degree draft taper hole is processed in the center of the collecting block, and a metal receiving piece 13 is mounted on the outside of the collecting block, and the two are clearance-matched.

[0063] In a second aspect, an embodiment of the present application provides a spacecraft separation system, the separation system comprising an explosive bolt 20 and the collecting device 10 in the above-mentioned first aspect, the collecting device 10 being used to collect broken connecting parts of the explosive bolt 20 .

[0064] The separation system is applied to aerospace vehicles. When the separation body of the aerospace vehicle is separated, the explosive bolt 20 is detonated, and the connecting piece 21 of the explosive bolt 20 is broken. The broken connecting piece rubs against the inner wall surface of the collecting hole 11 to form a self-locking, and the broken connecting piece will not rebound, thereby reducing the risk of high-frequency impact caused by the rebound affecting the normal operation of other equipment, and at the same time reducing the risk of the broken connecting piece rebounding back to the mounting hole of the explosive bolt 20 and interfering with the separation body. The separation system has high working reliability and is conducive to the smooth separation of the aerospace vehicle. The complete collection of the broken connecting piece of the explosive bolt 20 can be achieved through the simple collection device 10 in this embodiment without adding other components. The collection device 10 has a simple structure and a low manufacturing cost, which improves the flexibility of the design of the aerospace vehicle separation system.

[0065] Specifically, the separation system also includes devices such as an electrical connector; the electrical connector is used to send a separation signal and a separation timing current to the explosive bolt 20 to detonate the explosive bolt 20, and at the same time, it automatically disengages after receiving the electrical separation signal to avoid interference with the separation body.

[0066] In a third aspect, an embodiment of the present application provides a spacecraft, comprising: a first separation body 30 and a second separation body 40; an explosive bolt 20; and the separation system of the above-mentioned second aspect; wherein the first separation body 30 and the second separation body 40 are connected by the explosive bolt 20, the collecting device 10 is installed on the second separation body 40, and the connecting piece 21 of the explosive bolt 20 passes through the collecting port 111 and is located in the collecting hole 11; when the explosive bolt 20 is detonated, the connecting piece 21 of the explosive bolt 20 is broken, and the broken connecting piece of the explosive bolt 20 moves along the first direction X in the collecting hole 11, and the broken connecting piece of the explosive bolt 20 squeezes the inner wall surface of the collecting hole 11 to form a self-locking.

[0067] When the first separation body 30 and the second separation body 40 of the aerospace vehicle need to be separated, the explosive bolt 20 is detonated, and the broken connector that flies out of the explosive bolt 20 at high speed enters the collecting hole 11 of the collecting device 10 and moves along the first direction X in the collecting hole 11, squeezing the inner wall surface of the collecting hole 11. After the inner wall of the collecting hole 11 is squeezed and deformed, the kinetic energy of the high-speed broken connector is absorbed, and the friction between the broken connector and the inner wall surface of the collecting hole 11 forms a self-locking, and the broken connector will not rebound, which effectively reduces the secondary or multiple impacts caused by the detonation of the explosive bolt 20, and further reduces the risk of high-frequency impact caused by the rebound affecting the normal operation of other equipment, and at the same time reduces the risk of the broken connector rebounding back to the mounting hole of the explosive bolt 20 and interfering with the separation body, which is conducive to the smooth separation of the separation body of the aerospace vehicle, and the self-locking function without the need for an additional locking device is achieved through the geometric design of the collecting hole 11 and the friction between the broken connector and the collecting hole 11.

[0068] The axis of the explosive bolt 20 coincides with the axis of the collecting hole 11 of the collecting device 10 .

[0069] With such arrangement, when the explosive bolt 20 is detonated, the broken connecting piece more accurately squeezes the collecting hole 11 along the first direction X, and more accurately rubs against the inner wall surface of the collecting hole 11 to form a self-locking.

[0070] The above description is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application should be included in the protection scope of the present application.

Claims

1. A collection device for explosive bolts, characterized in that: The collecting device is provided with a collecting hole, the collecting hole has a collecting opening, and the collecting hole extends inwardly from the collecting opening along a first direction; Wherein, along the first direction, the cross-sectional area of ​​the collecting hole gradually decreases; When the explosive bolt is detonated, the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

2. The explosive bolt collecting device according to claim 1, characterized in that: The cross-sectional shape of the collecting hole is circular, square, trapezoidal or triangular.

3. The explosive bolt collecting device according to claim 1, characterized in that: The collecting hole is a conical hole, and the semi-conical angle of the conical hole is A, 3.5°≤A≤7°.

4. The explosive bolt collecting device according to claim 1, characterized in that: When the broken connecting pieces of the explosive bolt squeeze the inner wall surface of the collecting hole to form self-locking, all the broken connecting pieces of the explosive bolt are located in the collecting hole.

5. The explosive bolt collecting device according to claim 1, characterized in that: The collecting device comprises a collecting piece, the collecting piece is provided with the collecting hole, and the collecting piece is made of polytetrafluoroethylene material, polycarbonate material or polypropylene material.

6. The explosive bolt collecting device according to claim 1, characterized in that: The collecting device comprises a collecting member and a containing member, wherein the collecting member is provided with the collecting hole, the containing member is provided with a containing cavity with one side open, the collecting member is installed in the containing cavity, and the collecting port of the collecting member faces outside the containing cavity.

7. The explosive bolt collecting device according to claim 6, characterized in that: The collecting member is clearance-matched with the containing member.

8. The explosive bolt collecting device according to claim 6, characterized in that: The receiving part is a metal part.

9. A spacecraft separation system, characterized in that: The separation system comprises: The collecting device according to any one of claims 1 to 8; Explosive Bolts: Wherein, the collecting device is used to collect the broken connecting pieces of the explosive bolt; When the explosive bolt is detonated, the connecting piece of the explosive bolt breaks, and the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

10. A spacecraft, characterized in that: The aerospace vehicle comprises: a first separated body and a second separated body; The separation system as claimed in claim 9; Wherein, the first separation body and the second separation body are connected by the explosive bolt, the collecting device is installed on the second separation body, and the connecting piece of the explosive bolt extends into the collecting hole through the collecting port; When the explosive bolt is detonated, the connecting piece of the explosive bolt breaks, and the broken connecting piece of the explosive bolt moves in the collecting hole along the first direction, and the broken connecting piece of the explosive bolt squeezes the inner wall surface of the collecting hole to form self-locking.

11. The aerospace vehicle according to claim 10, characterized in that: The axis of the explosive bolt coincides with the axis of the collecting hole of the collecting device.

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