Separation assembly, fairing and carrier rocket

Abstract

The invention provides a separation assembly, a fairing and a carrier rocket, and relates to the technical field of carrier rockets. The separation assembly is arranged in the fairing and close to the top of the fairing, and the separation assembly comprises a first separation structure used for being rotationally connected with a first cover body of the fairing; the second separation structure is used for abutting against or being rotationally connected with a second cover body of the fairing; when the first cover body and the second cover body are closed, the elastic piece is in a compressed state, and the two ends of the elastic piece abut against the first separation structure and the second separation structure correspondingly; when the first cover body and the second cover body are opened, the elastic piece extends to push the first separation structure and the second separation structure to relatively move by a preset distance or be completely separated so as to push the first cover body and the second cover body to be separated. The separation assembly is arranged in the fairing and close to the top of the fairing, the load space is not occupied, the carrying capacity of the rocket can be effectively improved, and the separation mode is simple and reliable.

Description

Technical Field

[0001] The present application relates to the field of launch vehicle technology, and in particular, to a separation assembly, a fairing and a launch vehicle. Background Art

[0002] During a rocket launch mission, the satellite payload will be carried in the fairing cabin at the top of the rocket. The fairing is used to protect the satellite and other payloads to prevent the satellite from being affected by harmful environments such as aerodynamic forces, aerodynamic heating, and acoustic vibration. It is an important part of the launch vehicle. After the rocket reaches the predetermined orbit, the fairing will be opened and the payload will be separated so that the payload can enter the predetermined orbit. Therefore, in this process, the successful opening of the fairing is a very important link.

[0003] In the related art, the outer shell of the fairing is generally divided into two halves, namely a first cover body and a second cover body. An explosive bolt is arranged at the connection between the first cover body and the second cover body, and a spring structure is arranged at the lower part of the fairing. When the explosive bolt is activated in space, the first cover body and the second cover body are separated by the spring structure.

[0004] However, the spring structure in the prior art takes up load space, thereby reducing the carrying capacity of the rocket. Summary of the invention

[0005] In view of the shortcomings of the existing methods, the present application proposes a separation assembly, a fairing and a launch vehicle to solve the technical problem that the spring structure in the related technology occupies the load space and thus reduces the carrying capacity of the rocket.

[0006] In a first aspect, an embodiment of the present application provides a separation assembly, which is arranged in a fairing and close to the top of the fairing, and includes: A first separation structure is used for rotationally connecting with the first cover body of the fairing; The second separation structure is used to abut or rotate with the second cover of the fairing; The elastic member is in a compressed state and its two ends are respectively against the first separation structure and the second separation structure when the first cover body and the second cover body are closed; when the first cover body and the second cover body are opened, the elastic member stretches and pushes the first separation structure and the second separation structure to move relative to each other by a predetermined distance or to separate completely, so as to push the first cover body and the second cover body to separate.

[0007] In a possible implementation, the first separation structure includes: A first connecting member, one end of which is rotatably connected to a first connecting seat on the inner wall of the first cover body; A first mounting seat, rotatably connected to the other end of the first connecting member; The first sleeve is fixedly connected to the first mounting seat; the elastic member is sleeved on the first sleeve, and the elastic member abuts against the first mounting seat.

[0008] In a possible implementation, the other end of the first connecting member has a ball head; The first mounting seat has an arc surface matching the ball head, and the ball head is rotatably connected to the first mounting seat through the arc surface.

[0009] In a possible implementation, the second separation structure includes a top rod and a mounting structure; The push rod is fixedly connected to the mounting structure, one end of the push rod is used to abut against the second connecting seat on the inner wall of the second cover body, and the other end extends into the hollow cavity of the first sleeve; The elastic member abuts against the mounting structure.

[0010] In a possible implementation, the mounting structure includes a second mounting seat and a second sleeve; the second mounting seat is fixedly connected to the second sleeve and the push rod, and the second sleeve is coaxially arranged with the first sleeve; and / or, One end of the push rod is provided with a hemispherical portion, and the hemispherical portion is used to match with the groove formed in the second connecting seat.

[0011] In a possible implementation, the first mounting seat includes a tubular member; the tubular member is fixedly connected to the first sleeve; The tubular member has a first through hole for the limiting pin to pass through in a direction perpendicular to the axial direction of the first sleeve; The second sleeve is provided with a second through hole for the limiting pin to pass through, and the second through hole is arranged corresponding to the first through hole.

[0012] In a possible implementation, the second separation structure further includes a limiting rod; One end of the limit rod is fixedly connected to the other end of the push rod, and the other end of the limit rod is provided with a limit boss; A limiting block is arranged in the first sleeve, and a limiting hole is provided in the limiting block. The limiting rod passes through the limiting hole and can move along the axial direction of the first sleeve. The aperture of the limiting hole is smaller than the diameter of the limiting boss.

[0013] In a possible implementation, the separation assembly further includes: at least one pair of hinge structures, each hinge structure including a first hinge member and a second hinge member that are rotatably connected; In each pair of hinge structures, one first hinge is fixedly connected to the first cover, the other first hinge is fixedly connected to the second cover, and each second hinge is used to be fixedly connected to the arrow body below the fairing; During the separation process of the first cover body and the second cover body, when the first hinge and the second hinge rotate by a predetermined angle, the first hinge is separated from the second hinge.

[0014] In a second aspect, an embodiment of the present application provides a fairing, comprising: a first cover body, a second cover body, at least one second connecting member, and the separation assembly of the first aspect; The second connecting member fixedly connects the first cover body and the second cover body, and is used to be separated under the control of an external control device so that the first cover body and the second cover body are opened.

[0015] In a possible implementation, the number of the separation component is one.

[0016] In a third aspect, an embodiment of the present application provides a launch vehicle, comprising: a rocket body, and a fairing according to the second aspect; the rocket body and the fairing are detachably connected.

[0017] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: The first separation structure of the embodiment of the present application can be rotatably connected to the first cover of the fairing, and the second separation structure can be abutted or rotatably connected to the second cover of the fairing. At the same time, since the elastic member is in a compressed state when the first cover and the second cover are closed, and the two ends are respectively abutted against the first separation structure and the second separation structure, the second connection member fixedly connected to the first cover and the second cover is separated, so that when the first cover and the second cover are opened, the elastic member stretches to generate thrust, which can push the first separation structure and the second separation structure to move relative to a predetermined distance or completely separate, thereby pushing the first cover and the second cover to separate. Therefore, the embodiment of the present application is to set a separation component in the fairing and near the top of the fairing, which will not occupy the load space, and can not only effectively improve the carrying capacity of the rocket, but also can use the thrust of the elastic member of the separation component when the first cover and the second cover are opened to push the first cover and the second cover to separate, and the separation method is simple and reliable.

[0018] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic diagram of the structure of a launch vehicle provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of a separation component provided in an embodiment of the present application; Figure 3 A method provided in the embodiment of the present application Figure 2 A schematic diagram of a local structure of the separation assembly when the elastic member is in a compressed state; Figure 4 A method provided in the embodiment of the present application Figure 2 A schematic diagram of a partial structure of the separation assembly when the elastic member is in a released state; Figure 5 A schematic diagram of the structure of the connection between a fairing and a rocket body provided in an embodiment of the present application. Reference numerals: 10-separation assembly, 111-first connecting member, 112-first mounting seat, 1121-tubular member, 113-first sleeve, 114-ball head cover, 121-thrust rod, 122-second mounting seat, 123-second sleeve, 124-limiting rod, 1241-limiting boss, 125-limiting block, 130-elastic member, 140-limiting pin; 150-hinge structure, 151-first hinged member, 152-second hinged member, 1521-slide groove, 153-first connecting shaft, 154-second connecting shaft; 20- fairing, 210- first cover body, 211- first connecting seat, 220- second cover body, 212- second connecting seat, 2112- groove; 30- second connecting member; 40-Arrow body. DETAILED DESCRIPTION

[0020] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0021] It will be understood by those skilled in the art that, unless specifically stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the wording "including" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the present technical field. It should be understood that when we say that an element is "connected" or "coupled" to another element, the element may be directly connected or coupled to the other element, or it may refer to the connection relationship between the element and the other element through an intermediate element. In addition, the "connection" or "coupling" used herein may include wireless connection or wireless coupling. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0022] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0023] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0024] See also Figure 1 As shown, the present application embodiment provides a schematic diagram of the structure of a launch vehicle. Figure 1 As shown, the launch vehicle of the embodiment of the present application is used as an application scenario of the separation assembly 10. The launch vehicle comprises: a rocket body 40 and a fairing 20; the rocket body 40 and the fairing 20 are detachably connected.

[0025] See also Figure 1 As shown, an embodiment of the present application provides a fairing 20 , including: a first cover body 210 , a second cover body 220 , at least one second connecting member 30 and a separation assembly 10 .

[0026] The second connecting member 30 fixedly connects the first cover body 210 and the second cover body 220 so as to be separated under the control of an external control device so that the first cover body 210 and the second cover body 220 are opened.

[0027] A first connection seat 211 is disposed on the inner wall of the first cover body 210 , and a second connection seat 212 is disposed on the inner wall of the second cover body 220 . The first connection seat 211 is rotatably connected to one end of the separation component 10 , and the second connection seat 212 is abutted or rotatably connected to the other end of the separation component 10 .

[0028] Optionally, the second connecting member 30 may be an explosive bolt or other controllably separable components. The location and number of the second connecting member 30 are determined according to actual needs.

[0029] See also Figure 2 As shown, the embodiment of the present application provides a structural schematic diagram of a separation assembly 10. The separation assembly 10 is arranged in the fairing 20 and close to the top of the fairing 20. The separation assembly 10 includes: a first separation structure, a second separation structure and an elastic member 130.

[0030] The first separation structure is used for rotationally connecting with the first cover body 210 of the fairing 20. The second separation structure is used for abutting or rotationally connecting with the second cover body 220 of the fairing 20.

[0031] When the first cover body 210 and the second cover body 220 are closed, the elastic member 130 is in a compressed state and its two ends are respectively abutted against the first separation structure and the second separation structure; when the first cover body 210 and the second cover body 220 are opened, the elastic member 130 stretches and pushes the first separation structure and the second separation structure to move relative to each other by a predetermined distance or to completely separate, so as to push the first cover body 210 and the second cover body 220 to separate.

[0032] The first separation structure of the embodiment of the present application can be rotatably connected to the first cover 210 of the fairing 20, and the second separation structure can be abutted or rotatably connected to the second cover 220 of the fairing 20. At the same time, since the elastic member 130 is in a compressed state when the first cover 210 and the second cover 220 are closed, and the two ends are respectively abutted against the first separation structure and the second separation structure, the second connection member 30 fixedly connected to the first cover 210 and the second cover 220 is separated, so that when the first cover 210 and the second cover 220 are opened, the elastic member 130 is extended to generate thrust, which can push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or completely separate, thereby pushing the first cover 210 and the second cover 220 to separate.

[0033] Therefore, in the embodiment of the present application, the separation assembly 10 is arranged inside the fairing 20 and near the top of the fairing 20, which does not occupy the load space. Not only can the carrying capacity of the rocket be effectively improved, but also the first cover body 210 and the second cover body 220 can be pushed to separate by the thrust of the elastic member 130 of the separation assembly 10 when the first cover body 210 and the second cover body 220 are opened. The separation method is simple and reliable.

[0034] Moreover, the separation assembly 10 used in the embodiment of the present application is arranged inside the fairing 20 and close to the top of the fairing 20, so that the thrust of the elastic member 130 is more conducive to promoting the separation of the first cover body 210 and the second cover body 220, thereby improving the safety of opening the fairing 20 and effectively protecting the satellite and other payloads. The separation assembly 10 has a simple structure and strong reliability.

[0035] Optionally, the elastic member 130 is a compression spring that can be compressed and stretched under its own elastic force. The first separation structure and the second separation structure can move relative to each other by a predetermined distance according to the elastic member 130 and the space inside the fairing 20 .

[0036] The first separation structure of the embodiment of the present application is rotatably connected to the first cover body 210. The first separation structure can flexibly change the connection direction as the first cover body 210 falls off to avoid interference with other structures. Similarly, the second separation structure can also be rotatably connected to the second cover body 220 to achieve the same effect. At the same time, the first separation structure and the second separation structure can also be incompletely separated, and as a whole, the connection direction can be flexibly changed as the first cover body 210 falls off.

[0037] As an example, the first separation structure and the second separation structure are not separated, but are moved relative to each other by a predetermined distance under the push of the elastic member 130. The second separation structure can be supported by the second cover body 220, and then as the first cover body 210 and the second cover body 220 are gradually separated, the second separation structure is detached from the second cover body 220, and the entire separation assembly 10 is connected to the first cover body 210 and falls off with the first cover body 210.

[0038] As another example, the first separation structure and the second separation structure are completely separated, the second separation structure can be rotatably connected to the second cover body 220, and the elastic member 130 can be connected to the second separation structure or the first separation structure, so that after the first separation structure and the second separation structure are separated, they are respectively connected to the first cover body 210 and the second cover body 220, and fall off with the first cover body 210 and the second cover body 220.

[0039] See also Figure 2 As shown, the first separation structure includes: a first connecting member 111 , a first mounting seat 112 and a first sleeve 113 .

[0040] One end of the first connecting member 111 is rotatably connected to the first connecting seat 211 on the inner wall of the first cover body 210. The first mounting seat 112 is rotatably connected to the other end of the first connecting member 111.

[0041] The first sleeve 113 is fixedly connected to the first mounting seat 112 ; the elastic member 130 is sleeved on the first sleeve 113 , and the elastic member 130 abuts against the first mounting seat 112 .

[0042] In some embodiments, the other end of the first connecting member 111 has a ball head; the first mounting seat 112 has an arc surface matching the ball head, and the ball head is rotatably connected to the first mounting seat 112 through the arc surface.

[0043] Optionally, the first separation structure further includes a ball head cover 114, which is fixedly connected to the first mounting seat 112, and the ball head cover 114 has an arc-shaped surface matching the ball head.

[0044] See also Figure 2 As shown, one end of the first mounting seat 112 close to the elastic member 130 is fixedly connected to the first sleeve 113, and the end of the first mounting seat 112 away from the elastic member 130 has an arcuate surface for accommodating the ball head. The end of the first mounting seat 112 away from the elastic member 130 is also provided with a ball head cover 114, and the ball head cover 114 and the first mounting seat 112 together form a cavity for accommodating the ball head, thereby ensuring the free rotation of the ball head and preventing the ball head from falling off.

[0045] See also Figure 2As shown, the second separation structure includes a push rod 121 and a mounting structure. The push rod 121 is fixedly connected to the mounting structure, one end of the push rod 121 is used to abut against the second connection seat 212 on the inner wall of the second cover body 220, and the other end extends into the hollow cavity of the first sleeve 113; the elastic member 130 abuts against the mounting structure.

[0046] In some embodiments, the mounting structure includes a second mounting seat 122 and a second sleeve 123 ; the second mounting seat 122 is fixedly connected to the second sleeve 123 and the push rod 121 , and the second sleeve 123 is coaxially arranged with the first sleeve 113 .

[0047] See also Figure 2 As shown, the push rod 121 and the second sleeve 123 are fixedly connected by the second mounting seat 122 and the tightening nut. The second sleeve 123 is arranged inside the first sleeve 113, and the elastic member 130 is arranged in the gap between the first sleeve 113 and the second sleeve 123. The compression and extension of the elastic member 130 can be achieved by the relative sliding of the first sleeve 113 and the second sleeve 123.

[0048] In some embodiments, one end of the top rod 121 has a hemispherical portion, and the hemispherical portion is used to match the groove 2112 defined in the second connecting seat 212 .

[0049] Specifically, the inner wall of the groove 2112 has an arc-shaped concave surface matching the hemispherical portion, so that the push rod 121 and the second connecting seat 212 are supported.

[0050] See also Figure 2 As shown, the second separation structure further includes a limiting rod 124. One end of the limiting rod 124 is fixedly connected to the other end of the top rod 121, and the other end of the limiting rod 124 is provided with a limiting boss 1241.

[0051] A limiting block 125 is disposed in the first sleeve 113 . The limiting block 125 defines a limiting hole. The limiting rod 124 passes through the limiting hole and can move along the axial direction of the first sleeve 113 . The diameter of the limiting hole is smaller than the diameter of the limiting boss 1241 .

[0052] See also Figure 2 As shown, the left end of the first sleeve 113 is fixedly connected to the first mounting seat 112, and can be fixed by threaded connection. One end of the limiting rod 124 is fixedly connected to one end of the push rod 121 by threaded connection, and the limiting rod 124 is inserted into the first sleeve 113. The end of the limiting rod 124 inserted into the first sleeve 113 has a limiting boss 1241. The first sleeve 113 is provided with a limiting block 125. When the elastic member 130 is extended, the limiting boss 1241 contacts the limiting block 125, thereby limiting the length of the limiting rod 124 extending out of the first sleeve 113 and the length of the elastic member 130 extending.

[0053] A buffer structure, such as an aluminum honeycomb structure, a spring structure, etc., is provided on the side of the limiting boss 1241 close to the limiting block 125 , or on the side of the limiting block 125 close to the limiting boss 1241 , to achieve buffering of the contact between the limiting block 125 and the limiting boss 1241 .

[0054] See also Figure 3 As shown, the embodiment of the present application provides a Figure 2 The schematic diagram of the local structure of the separation assembly 10 when the elastic member 130 is in a compressed state is shown. Figure 4 As shown, the embodiment of the present application provides a Figure 2 The schematic diagram of the partial structure of the separation assembly 10 when the elastic member 130 is in a released state is shown. When the elastic member 130 is in a compressed state, the elastic member 130 is in an initial state, at which time the first cover 210 and the second cover 220 are closed. As the first cover 210 and the second cover 220 are opened, the elastic member 130 is released freely, and is extended in the released state, separating the first sleeve 113 from the second sleeve 123.

[0055] See also Figure 3 and Figure 4 As shown, the first mounting seat 112 includes a tubular member 1121; the tubular member 1121 is fixedly connected to the first sleeve 113. Along a direction perpendicular to the axial direction of the first sleeve 113, the tubular member 1121 has a first through hole for the stop pin 140 to pass through. Figure 2 As shown, the second sleeve 123 is provided with a second through hole for the limiting pin 140 to pass through. When the elastic member 130 is in a compressed state, the second through hole and the first through hole can be arranged correspondingly.

[0056] Optionally, one end of the tubular member 1121 has an opening for accommodating the ball head, and the inner wall of the opening has an arc surface matching the ball head, and the other end of the tubular member 1121 is fixedly connected to the first sleeve 113. The tubular member 1121 is provided with a third through hole along the axial direction of the first sleeve 113, the third through hole is connected to the second through hole, and one end of the third through hole is an opening, which can accommodate part of the ball head.

[0057] The left side of the tubular member 1121 is fixedly connected to the ball head cover 114 together with the first mounting seat 112 ; the right side of the tubular member 1121 abuts against the left end of the elastic member 130 to limit the left end of the elastic member 130 .

[0058] Combination Figures 1 to 4As shown. The left end of the second sleeve 123 has a pair of second through holes. When the elastic member 130 is in the initial compression state, the second through holes correspond to the first through holes of the tubular member 1121. The limiting pin 140 is inserted therein to limit the relative movement between the first sleeve 113 and the second sleeve 123, thereby fixing the compression state of the elastic member 130. When the first cover body 210 and the second cover body 220 are fixedly connected and in a closed state, the limiting pin 140 can be pulled out. The first separation structure and the second separation structure maintain the initial compression state of the elastic member 130 under the clamping action of the first cover body 210 and the second cover body 220 in the closed state.

[0059] When the fairing 20 needs to be separated, since the stop pin 140 has been released in advance, the first cover 210 and the second cover 220 begin to separate with the separation of the second connecting member 30. At this time, the elastic member 130 can release the elastic force and stretch, and the push rod 121, the second sleeve 123 and the stop rod 124 move to the right together. Since the ball head is connected to the first cover 210, the push rod 121 is in contact with the second cover 220 and is not fixed. Therefore, when the elastic member 130 stretches, the first cover 210 and the second cover 220 are pushed apart in opposite directions by the ball head and the push rod 121, so as to achieve the separation of the fairing 20.

[0060] See also Figure 5 As shown, the present application embodiment provides a structural schematic diagram of the connection between the fairing 20 and the rocket body 40. Figure 5 As shown, the separation assembly 10 further includes: at least one pair of hinge structures 150, each hinge structure 150 includes a first hinge member 151 and a second hinge member 152 which are rotatably connected.

[0061] In each pair of hinge structures 150 , one first hinge 151 is fixedly connected to the first cover 210 , the other first hinge 151 is fixedly connected to the second cover 220 , and each second hinge 152 is used to be fixedly connected to the arrow body 40 below the fairing 20 .

[0062] During the separation process of the first cover body 210 and the second cover body 220 , when the first hinge 151 and the second hinge 152 rotate by a predetermined angle, the first hinge 151 and the second hinge 152 are separated.

[0063] Optionally, the second hinge 152 is provided with a first connecting shaft 153, and the first hinge 151 and the second hinge 152 can be rotatably connected through the first connecting shaft 153. A circular arc-shaped concave connecting groove is provided at the connection between the first hinge 151 and the first connecting shaft 153. When the first hinge 151 and the second hinge 152 rotate at a predetermined angle, the connecting groove is separated from the first connecting shaft 153.

[0064] Optionally, the first hinge 151 is provided with a second connecting shaft 154, and the first hinge 151 and the second hinge 152 can also be rotatably connected through the second connecting shaft 154. A circular arc-shaped sliding groove 1521 is provided at the connection between the second hinge 152 and the second connecting shaft 154. As the first hinge 151 and the second hinge 152 rotate, the second connecting shaft 154 moves along the sliding groove 1521. When the first hinge 151 and the second hinge 152 rotate to a predetermined angle, the second connecting shaft 154 escapes from the sliding groove 1521 and separates from the second hinge 152.

[0065] The hinge structure 150 of the embodiment of the present application is a spin-throw hinge structure, which is used to connect the fairing 20 and the arrow body 40. When the separation assembly 10 pops open, the fairing 20 rotates around the axis below. After rotating to a certain angle, the connecting groove on the first hinge 151 and the slide groove 1521 on the second hinge 152 do not hinder the automatic separation of the fairing 20 and the arrow body 40, thereby realizing the separation of the fairing 20 and the arrow body 40.

[0066] As an example, the installation and separation process of the embodiment of the present application is as follows: During installation, the explosive bolt is locked. During the locking process, the elastic member 130 is gradually compressed. After the explosive bolt is locked, the elastic member 130 is compressed to a preset position. At this time, the second through hole on the second sleeve 123 corresponds to the first through hole of the tubular member 1121. After the limiting pin 140 is inserted, the initial compression state of the elastic member 130 of the separation component 10 is completed. After the separation component 10 is positioned, the limiting pin is released.

[0067] The explosive bolts are activated, separated, and the fairing 20 is opened. At the same time, the first sleeve 113 and the second sleeve 123 are separated and popped open under the elastic force of the elastic member 130, and the lower hinge structure 150 rotates. After rotating to a certain angle, the fairing 20 is separated from the rocket body 40, and finally the separation of the fairing 20 is achieved.

[0068] In the related art, while explosive bolts are provided at the connection between the first cover body 210 and the second cover body 220, a spring structure is provided at the inverted cone section at the bottom of the fairing 20. For example, a spring is provided inside the inverted cone section of the fairing 20, which can cooperate with the explosive bolts to realize that when the fairing 20 is opened, the fairing 20 and the lower stage are ejected by the spring. This method simplifies the control logic; however, the spring is provided inside the inverted cone section of the fairing 20, which requires multiple springs to act simultaneously, and it is also necessary to provide an additional structure outside the spring structure for protection, which increases the weight of the rocket and may also affect the overall aerodynamic shape structure of the rocket fairing 20. Moreover, multiple springs provided inside the inverted cone section will also occupy the space of the load and reduce the carrying capacity.

[0069] Based on the above, in some embodiments, the number of separation components 10 is one, the structure is simpler, and the separation method is safe and reliable.

[0070] The embodiment of the present application sets the separation assembly 10 at a position close to the top of the inside of the fairing 20, which will neither change the appearance of the rocket nor occupy the internal load space, thereby improving the carrying capacity; when the separation assembly 10 is separated, the separation assembly 10 will not cause the risk of interfering with the load structure.

[0071] Compared with using only explosive bolts, the embodiment of the present application has less impact, and compared with installing springs at the bottom of the fairing 20, fewer springs are required, and only one separation assembly 10 can be set, thereby reducing the weight of the launch vehicle.

[0072] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: (1) In the embodiment of the present application, the first cover body 210 and the second cover body 220 can be separated by the thrust of the elastic member 130 of the separation assembly 10 when the first cover body 210 and the second cover body 220 are opened. The separation method is simple and reliable.

[0073] (2) The separation assembly 10 used in the embodiment of the present application is arranged inside the fairing 20 and near the top of the fairing 20, which does not occupy the load space and can effectively improve the carrying capacity of the rocket.

[0074] (3) The embodiment of the present application sets the separation assembly 10 at a position close to the top of the inside of the fairing 20, which neither changes the appearance of the rocket nor occupies the internal payload space, thereby improving the carrying capacity; when the separation assembly 10 is separated, the separation assembly 10 will not cause the risk of interfering with the payload structure, thereby improving the safety of opening the fairing 20 and effectively protecting the satellite and other payloads.

[0075] (4) The hinge structure 150 of the embodiment of the present application is a spin-throw hinge structure, which is used to connect the fairing 20 and the rocket body 40. When the separation assembly 10 pops open, the fairing 20 rotates around the axis below. After rotating to a certain angle, the connecting groove on the first hinge 151 and the slide groove 1521 on the second hinge 152 do not hinder the automatic separation of the fairing 20 and the rocket body 40, thereby realizing the separation of the fairing 20 and the rocket body 40.

[0076] (5) Compared with the embodiment of the present application in which a spring structure is installed at the bottom of the fairing 20, the number of spring structures required is small, and only one separation assembly 10 may be provided, thereby reducing the weight of the launch vehicle.

[0077] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, changed, combined, or deleted. Furthermore, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted. Furthermore, steps, measures, and schemes in the related art that are similar to those disclosed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0078] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0079] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0080] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0081] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0082] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A separation component, characterized in that: The separation assembly is arranged in the fairing and close to the top of the fairing, and the separation assembly comprises: A first separation structure, used for rotationally connecting with the first cover body of the fairing; A second separation structure is used to abut or rotate with the second cover body of the fairing; An elastic member, when the first cover body and the second cover body are closed, the elastic member is in a compressed state and the two ends are respectively abutted against the first separation structure and the second separation structure; when the first cover body and the second cover body are opened, the elastic member stretches to push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or to completely separate, so as to push the first cover body and the second cover body to separate.

2. The separation assembly according to claim 1, characterized in that: The first separation structure comprises: A first connecting member, one end of which is rotatably connected to a first connecting seat on the inner wall of the first cover; A first mounting seat, rotatably connected to the other end of the first connecting member; The first sleeve is fixedly connected to the first mounting seat; the elastic member is sleeved on the first sleeve, and the elastic member abuts against the first mounting seat.

3. The separation assembly according to claim 2, characterized in that: The other end of the first connecting member has a ball head; The first mounting seat has an arc surface matching the ball head, and the ball head is rotatably connected to the first mounting seat via the arc surface.

4. The separation assembly according to claim 2, characterized in that: The second separation structure includes a top rod and a mounting structure; The push rod is fixedly connected to the mounting structure, one end of the push rod is used to abut against the second connecting seat on the inner wall of the second cover body, and the other end extends into the hollow cavity of the first sleeve; The elastic member abuts against the mounting structure.

5. The separation assembly according to claim 4, characterized in that The mounting structure comprises a second mounting seat and a second sleeve; the second mounting seat is fixedly connected to the second sleeve and the push rod, and the second sleeve is coaxially arranged with the first sleeve; and / or, One end of the push rod has a hemispherical portion, and the hemispherical portion is used to match the groove formed in the second connecting seat.

6. The separation assembly according to claim 5, characterized in that The first mounting seat comprises a tubular member; the tubular member is fixedly connected to the first sleeve; The tubular member has a first through hole for a limiting pin to pass through, along a direction perpendicular to the axial direction of the first sleeve; The second sleeve is provided with a second through hole for the limiting pin to pass through, and the second through hole is arranged corresponding to the first through hole.

7. The separation assembly according to claim 5, characterized in that The second separation structure further includes a limiting rod; One end of the limiting rod is fixedly connected to the other end of the push rod, and the other end of the limiting rod is provided with a limiting boss; A limiting block is disposed in the first sleeve, and a limiting hole is provided in the limiting block. The limiting rod passes through the limiting hole and can move along the axial direction of the first sleeve. The diameter of the limiting hole is smaller than the diameter of the limiting boss.

8. The separation assembly according to claim 1, characterized in that Also includes: at least one pair of hinge structures, each of which comprises a first hinge member and a second hinge member rotatably connected; In each pair of the hinge structures, one of the first hinges is fixedly connected to the first cover body, and another of the first hinges is fixedly connected to the second cover body, and each of the second hinges is used to be fixedly connected to the arrow body below the fairing; During the separation process of the first cover body and the second cover body, when the first hinge and the second hinge rotate by a predetermined angle, the first hinge is separated from the second hinge.

9. A fairing, characterized in that: include: A first cover, a second cover, at least one second connecting member, and a separation assembly as described in any one of claims 1 to 8; The second connecting member fixedly connects the first cover body and the second cover body, and is used to be separated under the control of an external control device so that the first cover body and the second cover body are opened.

10. The fairing according to claim 9, characterized in that: The number of the separation component is one.

11. A launch vehicle, characterized in that: include: An arrow body, and a fairing as claimed in any one of claims 9 to 10; The arrow body and the fairing are detachably connected.

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