Separation Component, Fairing and Launch Vehicle

Abstract

The present application provides a separation component, a fairing and a launch vehicle, relating to the technical field of launch vehicles. The separation component is disposed inside the fairing and near the top of the fairing. The separation component includes: a first separation structure for rotatably connecting with a first cover body of the fairing; a second separation structure for abutting against or rotatably connecting with a 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 its two ends respectively abut 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 extends to push the first separation structure and the second separation structure to relatively move a predetermined distance or completely separate, so as to push the first cover body and the second cover body to separate. In the present application, the separation component is disposed inside the fairing and near the top of the fairing, which will not occupy the load space, can effectively improve the carrying capacity of the rocket, and the separation method is simple and reliable.

Description

Technical Field

[0001] This application relates to the technical field of launch vehicles. Specifically, this application relates to a separation assembly, a fairing, and a launch vehicle. Background Art

[0002] In a rocket launch mission, a satellite payload is 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 force, aerodynamic heating, and acoustic vibration. It is an important part of the launch vehicle. After the rocket reaches the predetermined orbit, the fairing is opened, and then the payload is 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 parts, namely a first cover body and a second cover body. Explosion bolts are provided at the connection between the first cover body and the second cover body. At the same time, a spring structure is provided below the interior of the fairing. Thus, when the explosion bolts are 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 will occupy the load space, thereby reducing the carrying capacity of the rocket. Summary of the Invention

[0005] In view of the shortcomings of the existing method, this application provides a separation assembly, a fairing, and a launch vehicle to solve the technical problem that the spring structure in the related art occupies the load space and reduces the carrying capacity of the rocket.

[0006] In a first aspect, an embodiment of this application provides a separation assembly. The separation assembly is disposed in the fairing and near the top of the fairing. The separation assembly includes:

[0007] A first separation structure for rotatably connecting with the first cover body of the fairing;

[0008] A second separation structure for abutting or rotatably connecting with the second cover body of the fairing;

[0009] An elastic member. When the first cover body and the second cover body are closed, the elastic member is in a compressed state and its two ends respectively abut 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 elongates to push the first separation structure and the second separation structure to move a predetermined distance relative to each other or completely separate, so as to push the first cover body and the second cover body to separate.

[0010] In a possible implementation, the first separation structure includes:

[0011] A first connecting member, one end of which is rotatably connected to a first connection seat on the inner wall of the first cover body;

[0012] The first mounting seat is rotatably connected to the other end of the first connecting member;

[0013] 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.

[0014] In a possible implementation, the other end of the first connecting member has a ball head;

[0015] 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.

[0016] In a possible implementation, the second separation structure includes a ejector rod and a mounting structure;

[0017] The ejector rod is fixedly connected to the mounting structure. One end of the ejector 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;

[0018] The elastic member abuts against the mounting structure.

[0019] In a possible implementation, the mounting structure includes a second mounting seat and a second sleeve; the second mounting seat is fixedly connected to both the second sleeve and the ejector rod, and the second sleeve is coaxially arranged with the first sleeve; and / or,

[0020] One end of the ejector rod has a hemispherical portion in the shape of a hemisphere, and the hemispherical portion is used to match the groove formed in the second connecting seat.

[0021] In a possible implementation, the first mounting seat includes a tubular member; the tubular member is fixedly connected to the first sleeve;

[0022] Along a direction perpendicular to the axial direction of the first sleeve, the tubular member has a first through hole for the limit pin to pass through;

[0023] The second sleeve is provided with a second through hole for the limit pin to pass through, and the second through hole is correspondingly arranged with the first through hole.

[0024] In a possible implementation, the second separation structure further includes a limit rod;

[0025] One end of the limit rod is fixedly connected to the other end of the ejector rod, and a limit boss is provided at the other end of the limit rod;

[0026] A limit block is arranged in the first sleeve, and a limit hole is formed in the limit block. The limit rod passes through the limit hole and can move along the axial direction of the first sleeve, and the diameter of the limit hole is smaller than the diameter of the limit boss.

[0027] In a possible implementation, the separation assembly further includes: at least a pair of hinge structures, and each hinge structure includes a first hinge member and a second hinge member that are rotatably connected;

[0028] In each pair of hinge structures, one first hinge member is fixedly connected to the first cover body, and the other first hinge member is fixedly connected to the second cover body. Each second hinge member is used to be fixedly connected to the rocket body below the fairing.

[0029] During the separation process of the first cover body and the second cover body, when the first hinge member and the second hinge member rotate by a predetermined angle, the first hinge member and the second hinge member are separated.

[0030] In a second aspect, an embodiment of the present application provides a fairing, including: a first cover body, a second cover body, at least one second connecting member, and the separation assembly of the first aspect.

[0031] 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.

[0032] In a possible implementation manner, the number of separation assemblies is one.

[0033] In a third aspect, an embodiment of the present application provides a launch vehicle, including: a rocket body and the fairing of the second aspect; the rocket body and the fairing are detachably connected.

[0034] The beneficial technical effects brought by the technical solutions provided by the embodiments of the present application include:

[0035] The first separation structure of the embodiment of the present application can be rotatably connected to the first cover body of the fairing, and the second separation structure can abut against or be rotatably connected to the second cover body of the fairing. At the same time, since the elastic member is in a compressed state when the first cover body and the second cover body are closed and abuts against the first separation structure and the second separation structure at both ends respectively, the second connecting member that fixedly connects the first cover body and the second cover body is separated. When the first cover body and the second cover body are opened, the elastic member elongates to generate a thrust force, which can push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or be completely separated, thereby pushing the first cover body and the second cover body to separate. Therefore, in the embodiment of the present application, the separation assembly is arranged inside the fairing and near the top of the fairing, which does not occupy the load space. It can not only effectively improve the carrying capacity of the rocket, but also utilize the thrust force of the elastic member of the separation assembly when the first cover body and the second cover body are opened to push the first cover body and the second cover body to separate, and the separation method is simple and reliable.

[0036] The additional aspects and advantages of the present application will be partially given in the following description, and these will become obvious from the following description, or can be understood through the practice of the present application. Description of the Drawings

[0037] The above and / or additional aspects and advantages of the present application will become apparent and readily understood from the following description of embodiments in conjunction with the accompanying drawings, where:

[0038] Figure 1 FIG. 4 is a schematic structural diagram of a launch vehicle provided for an embodiment of the present application;

[0039] Figure 2 FIG. 8 is a schematic structural diagram of a separation assembly provided for an embodiment of the present application;

[0040] Figure 3 FIG. 12 is a schematic partial structural diagram of an elastic member of the separation assembly provided for an embodiment of the present application when the elastic member is in a compressed state; Figure 2 FIG. 14 is a schematic partial structural diagram of an elastic member of the separation assembly provided for an embodiment of the present application when the elastic member is in a released state;

[0041] Figure 4 FIG. 18 is a schematic structural diagram of a connection between a fairing and a rocket body provided for an embodiment of the present application. Figure 2 FIG. 20 is a schematic partial structural diagram of an elastic member of the separation assembly provided for an embodiment of the present application when the elastic member is in a released state;

[0042] Figure 5 FIG. 24 is a schematic structural diagram of a connection between a fairing and a rocket body provided for an embodiment of the present application.

[0043] Reference numerals:

[0044] 10 - separation assembly, 111 - first connecting member, 112 - first mounting seat, 1121 - tubular member, 113 - first sleeve, 114 - ball head cover, 121 - ejector 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 hinge member, 152 - second hinge member, 1521 - chute, 153 - first connecting shaft, 154 - second connecting shaft;

[0045] 20 - fairing, 210 - first fairing body, 211 - first connecting seat, 220 - second fairing body, 212 - second connecting seat, 2112 - groove;

[0046] 30 - second connecting member;

[0047] 40 - rocket body. Detailed implementation manners

[0048] The embodiments of the present application will be described below with reference to the accompanying drawings in the present application. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute limitations on the technical solutions of the embodiments of the present application.

[0049] Those skilled in the art can understand that, unless specifically stated otherwise, the terms "the" and "said" used herein may also include the plural form. It should be further understood that the term "comprising" used in the specification of this application means the presence of the described features, integers, steps, operations, elements, and / or components, but does not exclude the presence of other features, information, data, steps, operations, elements, components, and / or combinations thereof supported by the art. It should be understood that when we say an element is "connected" or "coupled" to another element, the element can be directly connected or coupled to the other element, or it can mean that the element and the other element establish a connection relationship through an intermediate element. In addition, the "connection" or "coupling" used herein can include wireless connection or wireless coupling. The term "and / or" used herein means at least one of the items defined by the term. For example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0050] To make the objectives, technical solutions, and advantages of this application clearer, the following will further describe the embodiments of this application in detail with reference to the accompanying drawings.

[0051] The following uses specific embodiments to detail the technical solutions of this application and how the technical solutions of this application solve the above technical problems. It should be noted that the following embodiments can refer to, draw on, or combine with each other. For the same terms, similar features, and similar implementation steps in different embodiments, they will not be described repeatedly.

[0052] See Figure 1 As shown, the embodiments of this application provide a schematic structural diagram of a launch vehicle. As Figure 1 shown, the launch vehicle in the embodiments of this application is an application scenario of the separation component 10. The launch vehicle includes: a rocket body 40 and a fairing 20; the rocket body 40 and the fairing 20 are detachably connected.

[0053] See Figure 1 As shown, the embodiments of this application provide a fairing 20, including: a first fairing body 210, a second fairing body 220, at least one second connecting member 30, and a separation component 10.

[0054] The second connecting member 30 fixedly connects the first fairing body 210 and the second fairing body 220 and is used to separate under the control of an external control device so that the first fairing body 210 and the second fairing body 220 open.

[0055] A first connection seat 211 is provided on the inner wall of the first fairing body 210, and a second connection seat 212 is provided on the inner wall of the second fairing body 220. One end of the separation component 10 is rotatably connected to the first connection seat 211, and the other end of the separation component 10 abuts or is rotatably connected to the second connection seat 212.

[0056] Optionally, the second connecting member 30 may be an explosive bolt or other controllable separation components. The installation position and quantity of the second connecting member 30 are determined according to actual needs.

[0057] See Figure 2 As shown, an embodiment of the present application provides a schematic structural diagram of a separation assembly 10. The separation assembly 10 is arranged inside the fairing 20 and near the top of the fairing 20. The separation assembly 10 includes: a first separation structure, a second separation structure, and an elastic member 130.

[0058] The first separation structure is used for rotatably connecting with the first housing 210 of the fairing 20. The second separation structure is used for abutting against or rotatably connecting with the second housing 220 of the fairing 20.

[0059] When the first housing 210 and the second housing 220 are closed, the elastic member 130 is in a compressed state and its two ends respectively abut against the first separation structure and the second separation structure; when the first housing 210 and the second housing 220 are opened, the elastic member 130 elongates to push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or to be completely separated, so as to push the first housing 210 and the second housing 220 to separate.

[0060] In the embodiment of the present application, the first separation structure can be rotatably connected with the first housing 210 of the fairing 20, and the second separation structure can be abutted against or rotatably connected with the second housing 220 of the fairing 20. At the same time, since the elastic member 130 is in a compressed state and its two ends respectively abut against the first separation structure and the second separation structure when the first housing 210 and the second housing 220 are closed, the second connecting member 30 that fixedly connects the first housing 210 and the second housing 220 is separated. When the first housing 210 and the second housing 220 are opened, the elastic member 130 elongates to generate a thrust force, which can push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or to be completely separated, thereby pushing the first housing 210 and the second housing 220 to separate.

[0061] 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. It can not only effectively improve the carrying capacity of the rocket, but also utilize the thrust of the elastic member 130 of the separation assembly 10 when the first housing 210 and the second housing 220 are opened to push the first housing 210 and the second housing 220 to separate, and the separation method is simple and reliable.

[0062] Moreover, the separation component 10 adopted in the embodiment of the present application is arranged inside the fairing 20 and near 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, improving the safety of opening the fairing 20, effectively protecting the satellite and other payloads. The structure of the separation component 10 is simple and has strong reliability.

[0063] Optionally, the elastic member 130 is a compression spring, which can be compressed and elongated under its own elastic force. The relative movement of the first separation structure and the second separation structure by a predetermined distance can be set according to the elastic member 130 and the space inside the fairing 20.

[0064] 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, avoiding 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 may not be completely separated and can flexibly change the connection direction together as a whole as the first cover body 210 falls off.

[0065] As an example, the first separation structure and the second separation structure are not separated. Only under the push of the elastic member 130, they move relative to each other by a predetermined distance. The second separation structure can abut against 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 disengaged from the second cover body 220, and the entire separation component 10 is connected to the first cover body 210 and falls off with the first cover body 210.

[0066] 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. The elastic member 130 can be connected to the second separation structure or the first separation structure. In this way, 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.

[0067] See Figure 2 As shown, the first separation structure includes: a first connecting member 111, a first mounting seat 112, and a first sleeve 113.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] Optionally, the first separating structure further includes a ball head cover 114, the ball head cover 114 is fixedly connected to the first mounting seat 112, and the ball head cover 114 has an arc surface matching the ball head.

[0072] See 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. The first mounting seat 112 has an arc surface for accommodating the ball head at the end away from the elastic member 130. A ball head cover 114 is further provided at the end of the first mounting seat 112 away from the elastic member 130. The ball head cover 114 and the first mounting seat 112 together form a cavity for accommodating the ball head, ensuring the free rotation of the ball head and preventing the ball head from falling off.

[0073] See Figure 2 As shown, the second separating 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 connecting seat 212 on the inner wall of the second cover 220, and the other end extends into the hollow cavity of the first sleeve 113; the elastic member 130 abuts against the mounting structure.

[0074] 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 both the second sleeve 123 and the push rod 121, and the second sleeve 123 is coaxially arranged with the first sleeve 113.

[0075] See Figure 2 As shown, the push rod 121 and the second sleeve 123 are fixedly connected through the second mounting seat 122 and a 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 elongation of the elastic member 130 can be realized by the relative sliding of the first sleeve 113 and the second sleeve 123.

[0076] In some embodiments, one end of the push rod 121 has a hemispherical portion, and the hemispherical portion is used to match the groove 2112 opened in the second connecting seat 212.

[0077] Specifically, the inner wall of the groove 2112 has an arc-shaped concave surface matching the hemispherical portion, so that the push rod 121 abuts against the second connecting seat 212.

[0078] See Figure 2As shown, the second separation structure further includes a limit rod 124. One end of the limit rod 124 is fixedly connected to the other end of the ejector rod 121, and a limit boss 1241 is provided at the other end of the limit rod 124.

[0079] A limit block 125 is provided in the first sleeve 113. The limit block 125 is provided with a limit hole. The limit rod 124 passes through the limit hole and can move along the axial direction of the first sleeve 113. The diameter of the limit hole is smaller than the diameter of the limit boss 1241.

[0080] See 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 limit rod 124 is fixedly connected to one end of the ejector rod 121 by thread. The limit rod 124 is inserted into the first sleeve 113. The end of the limit rod 124 inserted into the first sleeve 113 has a limit boss 1241. A limit block 125 is provided in the first sleeve 113. When the elastic member 130 elongates, the limit boss 1241 contacts the limit block 125, thereby limiting the length of the limit rod 124 extending out of the first sleeve 113 and the elongation length of the elastic member 130.

[0081] A buffer structure is provided on the side of the limit boss 1241 close to the limit block 125 or on the side of the limit block 125 close to the limit boss 1241, such as an aluminum honeycomb structure, a spring structure, etc., to achieve buffering of the contact between the limit block 125 and the limit boss 1241.

[0082] See Figure 3 As shown, an embodiment of the present application provides a Figure 2 Partial structural schematic diagram of the elastic member 130 of the separation assembly 10 in a compressed state as shown. See Figure 4 As shown, an embodiment of the present application provides a Figure 2 Partial structural schematic diagram of the elastic member 130 of the separation assembly 10 in a released state as shown. When the elastic member 130 is in a compressed state, the elastic member 130 is in an initial state. At this 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 freely released and elongates in a released state, separating the first sleeve 113 from the second sleeve 123.

[0083] See 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 limit pin 140 to pass through. In combination with Figure 2As 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 correspondingly arranged.

[0084] 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. 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 communicates with the second through hole, and one end of the third through hole serves as an opening and can accommodate a part of the ball head.

[0085] The left side of the tubular member 1121 and the first mounting seat 112 are fixedly connected to the ball head cover 114 together; 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.

[0086] Combined Figures 1 to 4 As shown. The left end of the second sleeve 123 has a pair of second through holes. When the elastic member 130 is in an initial compressed 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 compressed 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 removed. Under the clamping action of the first separating structure and the second separating structure in the closed state of the first cover body 210 and the second cover body 220, the initial compressed state of the elastic member 130 is maintained.

[0087] When the fairing 20 needs to be separated, since the limiting pin 140 has been released in advance, as the second connecting member 30 separates, the first cover body 210 and the second cover body 220 start to separate. At this time, the elastic member 130 can release its elastic force and elongate, and the ejector rod 121, the second sleeve 123 and the limiting rod 124 move to the right together. Since the ball head is connected to the first cover body 210 and the ejector rod 121 abuts against the second cover body 220 and is not fixed. Therefore, when the elastic member 130 elongates, the first cover body 210 and the second cover body 220 are respectively pushed in opposite directions through the ball head and the ejector rod 121 to realize the separation of the fairing 20.

[0088] See Figure 5 As shown, the embodiment of the present application provides a schematic structural diagram of the connection between the fairing 20 and the rocket body 40. As Figure 5 As shown, the separation assembly 10 further includes: at least a pair of hinge structures 150, and each hinge structure 150 includes a first hinge member 151 and a second hinge member 152 that are rotatably connected.

[0089] In each pair of hinge structures 150, one first hinge member 151 is fixedly connected to the first cover 210, and the other first hinge member 151 is fixedly connected to the second cover 220. Each second hinge member 152 is used to be fixedly connected to the rocket body 40 below the fairing 20.

[0090] During the separation process of the first cover 210 and the second cover 220, when the first hinge member 151 and the second hinge member 152 rotate by a predetermined angle, the first hinge member 151 is separated from the second hinge member 152.

[0091] Optionally, the second hinge member 152 is provided with a first connecting shaft 153. The first hinge member 151 and the second hinge member 152 can be rotatably connected through the first connecting shaft 153. A connecting groove with an arc-shaped concave is formed at the connection between the first hinge member 151 and the first connecting shaft 153. When the first hinge member 151 and the second hinge member 152 rotate by a predetermined angle, the connecting groove is separated from the first connecting shaft 153.

[0092] Optionally, the first hinge member 151 is provided with a second connecting shaft 154. The first hinge member 151 and the second hinge member 152 can also be rotatably connected through the second connecting shaft 154. An arc-shaped sliding groove 1521 is formed at the connection between the second hinge member 152 and the second connecting shaft 154. As the first hinge member 151 and the second hinge member 152 rotate, the second connecting shaft 154 moves along the sliding groove 1521. When the first hinge member 151 and the second hinge member 152 rotate by a predetermined angle, the second connecting shaft 154 disengages from the sliding groove 1521 and is separated from the second hinge member 152.

[0093] The hinge structure 150 in the embodiment of the present application is a rotary and throwing hinge structure for connecting the fairing 20 and the rocket body 40. When the separation assembly 10 pops open, the fairing 20 rotates around the lower shaft. After rotating to a certain angle, the connecting groove on the first hinge member 151 and the sliding groove 1521 on the second hinge member 152 do not prevent 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.

[0094] As an example, the installation and separation process in the embodiment of the present application is as follows:

[0095] During installation, the explosive bolt is tightened. During the tightening process, the elastic member 130 is gradually compressed. After the explosive bolt is tightened, 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 inserting the limit pin 140, the initial compression state of the elastic member 130 of the separation assembly 10 is completed. After the separation assembly 10 is positioned, the limit pin is removed and released.

[0096] The explosion bolt is activated, and the explosion bolt separates, opening the fairing 20. At the same time, the first sleeve 113 and the second sleeve 123 separate and spring open under the elastic force of the elastic member 130, and the lower hinge structure 150 rotates. After rotating a certain angle, the fairing 20 separates from the rocket body 40, and finally the separation of the fairing 20 is achieved.

[0097] In the related art, while an explosion bolt is 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 lower part of the fairing 20. For example, a spring is provided inside the inverted cone section of the fairing 20, which can cooperate with the explosion bolt to spring open the fairing 20 and the lower stage when the fairing 20 is opened. This method simplifies the control logic; however, the spring is provided inside the inverted cone section of the fairing 20, multiple springs need to act simultaneously, and additional structures need to be provided outside the spring structure for protection, increasing the weight of the rocket and possibly affecting 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 payload, reducing the carrying capacity.

[0098] Based on the above content, in some embodiments, the number of the separation assemblies 10 is one, the structure is simpler, and the separation method is safe and reliable.

[0099] In the embodiments of the present application, the separation assembly 10 is arranged at a position close to the top inside the fairing 20, which neither changes the shape of the rocket nor occupies the internal payload space, improving the carrying capacity; when the separation assembly 10 separates, the separation assembly 10 also does not pose a risk of interfering with the payload structure.

[0100] Compared with only using explosion bolts, the embodiments of the present application have less impact. Compared with installing springs at the bottom of the fairing 20, the number of springs required is less, and only one separation assembly 10 can be provided, reducing the weight of the launch vehicle.

[0101] Applying the embodiments of the present application can at least achieve the following beneficial effects:

[0102] (1) In the embodiments of the present application, the elastic force of the elastic member 130 of the separation assembly 10 can be used to push the first cover body 210 and the second cover body 220 to separate when the first cover body 210 and the second cover body 220 are opened, and the separation method is simple and reliable.

[0103] (2) The separation assembly 10 adopted in the embodiments of the present application is arranged inside the fairing 20 and close to the top of the fairing 20, which does not occupy the load space and can effectively improve the carrying capacity of the rocket.

[0104] (3) In the embodiment of the present application, the separation component 10 is arranged at a position near the top inside the fairing 20, which neither changes the shape of the rocket nor occupies the internal payload space, thus improving the carrying capacity; when the separation component 10 separates, there is no risk of interference to the payload structure, enhancing the safety of opening the fairing 20 and effectively protecting the satellite and other payloads.

[0105] (4) The hinge structure 150 in the embodiment of the present application is a rotary throw hinge structure for connecting the fairing 20 and the rocket body 40. When the separation component 10 pops open, the fairing 20 rotates around the lower axis. After rotating to a certain angle, the connection groove on the first hinge member 151 and the chute 1521 on the second hinge member 152 do not prevent the automatic separation of the fairing 20 from the rocket body 40, thereby realizing the separation of the fairing 20 from the rocket body 40.

[0106] (5) Compared with installing a spring structure at the bottom of the fairing 20 in the embodiment of the present application, the number of spring structures required is small. Only one separation component 10 can be set, reducing the weight of the launch vehicle.

[0107] Those skilled in the art of the present technology can understand that the steps, measures, and solutions in the various operations, methods, and processes discussed in the present application can be alternated, changed, combined, or deleted. Further, the other steps, measures, and solutions in the various operations, methods, and processes discussed in the present application can also be alternated, changed, rearranged, decomposed, combined, or deleted. Further, the steps, measures, and solutions in the related technologies that are the same as those disclosed in the present application can also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0108] In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are the exemplary directions or positional relationships based on the drawings, which are for the convenience of describing or simplifying the embodiments of the present application, rather than indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application.

[0109] The terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise specified, the meaning of "plurality" is two or more.

[0110] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" 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 directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0111] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any one or more embodiments or examples in a suitable manner.

[0112] The above description is only a partial implementation manner of the present application. It should be noted that for those of ordinary skill in the art, without departing from the technical concept of the solution of the present application, other similar implementation means based on the technical idea of the present application also belong to the protection scope of the embodiments of the present application.

Claims

1. A separation component, characterized in that, The separation component is arranged inside the fairing and near the top of the fairing, and the separation component includes: A first separation structure, including: a first connecting piece, one end of which is rotatably connected to a first connecting seat on the inner wall of the first housing of the fairing; a first mounting seat, rotatably connected to the other end of the first connecting piece; a first sleeve, fixedly connected to the first mounting seat; A second separation structure, configured to abut against or be rotatably connected to the second housing of the fairing, including a top rod and a mounting structure, the top rod being fixedly connected to the mounting structure; the mounting structure includes a second mounting seat and a second sleeve; one end of the top rod is configured to abut against a second connecting seat on the inner wall of the second housing, and the other end extends into the hollow cavity of the first sleeve; the second mounting seat is fixedly connected to both the second sleeve and the top rod, and the second sleeve is coaxially arranged with the first sleeve; and / or, one end of the top rod has a hemispherical portion, and the hemispherical portion is configured to match a groove formed in the second connecting seat; The first mounting seat includes a tubular member; the tubular member is fixedly connected to the first sleeve; along a direction perpendicular to the axial direction of the first sleeve, the tubular member has a first through hole for a limit pin to pass through; the second sleeve is provided with a second through hole for the limit pin to pass through, and the second through hole is correspondingly arranged with the first through hole; An elastic member, the elastic member is sleeved on the first sleeve, and the elastic member abuts against the first mounting seat and the mounting structure. When the first housing and the second housing are closed, the elastic member is in a compressed state and its two ends respectively abut against the first separation structure and the second separation structure; when the first housing and the second housing are opened, the elastic member elongates to push the first separation structure and the second separation structure to move relative to each other by a predetermined distance or be completely separated, so as to push the first housing and the second housing to separate.

2. The separation component according to claim 1, characterized in that The other end of the first connecting piece 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.

3. The separation component according to claim 1, characterized in that, The second separation structure further includes a limit rod; One end of the limit rod is fixedly connected to the other end of the top rod, and a limit boss is arranged at the other end of the limit rod; A limit block is arranged inside the first sleeve, a limit hole is formed in the limit block, the limit rod passes through the limit hole and can move along the axial direction of the first sleeve, and the diameter of the limit hole is smaller than the diameter of the limit boss.

4. The separation component according to claim 1, wherein Further included: 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 member is fixedly connected to the first housing, and the other first hinge member is fixedly connected to the second housing. Each second hinge member is configured to be fixedly connected to a rocket body below the fairing; During the separation process of the first housing and the second housing, when the first hinge member and the second hinge member rotate by a predetermined angle, the first hinge member and the second hinge member are separated.

5. A fairing, characterized in that, Including: A first cover body, a second cover body, at least one second connecting member, and a separation assembly as described in any one of claims 1-4; The second connecting member fixedly connects the first cover body and the second cover body and is used to separate under the control of an external control device so that the first cover body and the second cover body are opened.

6. The fairing according to claim 5, wherein The number of the separation assemblies is one.

7. A launch vehicle, characterized in that, Comprising: A rocket body and a fairing as described in any one of claims 5-6; The rocket body and the fairing are detachably connected.

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