Reverse thrust fairing structure of carrier rocket

Abstract

The invention relates to the technical field of liquid rockets, and provides a reverse thrust fairing structure of a carrier rocket, which comprises a fairing main body and an end socket part, the end socket part is connected with the fairing body through a connecting assembly and located at the end of the fairing body. The connecting assembly comprises a turnover connecting piece and a fixed connecting piece, and the turnover connecting piece is arranged between the end socket part and the fairing main body; and fixed connecting pieces are arranged on the two sides and the top of the sealing head part. Through the arrangement of the turnover connecting piece and the fixed connecting piece, when separation is needed, the fixed connecting piece is separated from the connecting state, so that the end socket part can be turned over around the turnover connecting piece, on one hand, the guide of turning over of the end socket part can be realized, and the separation of the end socket part is more stable; and on the other hand, through the mechanical connection mode of the fixed connecting piece and the turnover connecting piece, the stability of the whole structure is higher when separation is not needed.

Description

Technical Field

[0001] The invention relates to the technical field of liquid rockets, and in particular to a reverse thrust fairing structure of a carrier rocket. Background Art

[0002] The reverse thrust rocket is used in the process of cold separation of the substage or booster of liquid launch vehicle, and is mainly installed in the middle section of a substage or booster. Since the reverse thrust rocket ejects the fuel gas flow upward during the separation process, the part of the rocket body that needs to be separated and detached obtains a downward recoil force to accelerate away from the upper stage rocket body.

[0003] Moreover, the reverse rockets of liquid-propellant rockets are all installed on the outside of the rocket body, so a fairing needs to be installed on the outside of the reverse rocket to prevent rain and water and reduce wind resistance. The fairings of the exposed parts of other rocket bodies only need to meet the fairing function, but the fairing of the reverse rocket not only needs to protect the reverse rocket during the rocket flight but also play a fairing role. When the reverse rocket ignites at the moment of sub-stage separation, the front head of the reverse fairing needs to fly out in time to avoid affecting the airflow of the reverse rocket nozzle. Therefore, the reverse rocket fairing needs to meet the requirements of having sufficient strength before separation and being able to be destroyed or fly out in time when the reverse rocket is working.

[0004] In the related art, most of the reverse thrust rocket fairings are equipped with a single reverse thrust fairing for a single reverse thrust rocket, and the front head is fixed by a bent spring sheet through a snap-on method, that is, the front head is connected to the reverse thrust fairing column section and the front head through a bent spring, and in order to achieve the recovery of the front head, it is recovered by setting a towing rope. This method requires the release of the elastic potential energy of the spring sheet, so it is easy to fail prematurely when the vibration of the rocket body is too large, affecting the overall stability. When recovered by the towing rope, the front head as a whole will easily cause the flying fairing front head to return and hit the reverse thrust fairing or the rocket body, increasing the risk of damage to the front head and the rocket body. Summary of the invention

[0005] The invention provides a reverse thrust fairing structure of a launch vehicle, which is used to solve the defects in the related art that the head portion has poor stability and is prone to damage to the head portion and the rocket body.

[0006] The present invention provides a reverse thrust fairing structure of a launch vehicle, comprising: a fairing main body and a head portion; an installation space for installing a reverse thrust device is formed in the fairing main body; the head portion is connected to the fairing main body through a connecting assembly and is located at the end of the fairing main body, so that the main body of the reverse thrust device is located in the installation space, and the nozzle of the reverse thrust device is located in the head portion; the connecting assembly comprises a folding connector and a fixed connector, the folding connector is arranged between the head portion and the fairing main body, and is located at the outer side wall of the fairing main body; the fixed connector is arranged on both sides of the head portion and on the top of the head portion, and the fixed connector is used for fixed connection between the head portion and the fairing main body and the rocket body; wherein the fixed connector is configured so that when the reverse thrust device generates a reverse thrust airflow, the fixed connector can be disconnected, so that the head portion can be folded around the folding connector toward the outer side of the fairing main body.

[0007] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the reverse thrust fairing structure also includes a reverse flow baffle, and the reverse flow baffle is arranged in the installation space and located at one end close to the head portion.

[0008] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, a connecting lug is provided on the main body of the reverse thrust device, one side of the reverse flow baffle is connected to the connecting lug, and the other side of the reverse flow baffle is used to be connected to the body of the launch vehicle.

[0009] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the folding connecting member includes a folding plate, one end of the folding plate is connected to the head portion, and the other end of the folding plate is connected to the fairing body, and a breaking groove is provided between the two ends of the folding plate so that the head portion can be folded along the breaking groove.

[0010] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the cross-section of the breaking groove is a V-shaped groove structure, so that when the head portion is folded, the two surfaces of the V-shaped groove structure fit together and break.

[0011] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the notch angle of the V-shaped groove structure is 45°-60°.

[0012] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the folding plate includes a copper-aluminum alloy plate, and the minimum thickness of the copper-aluminum alloy plate is 0.3 mm.

[0013] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, the fixed connecting member includes a fixed connecting aluminum sheet, and a plurality of the fixed connecting aluminum sheets for connecting to the body of the launch vehicle are arranged at intervals on the edge of the head portion.

[0014] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, connecting screws are provided on the side walls on both sides of the fairing body, and correspondingly, the fixed connecting aluminum sheets are provided on both sides of the head portion, and the fixed connecting aluminum sheets are connected to the connecting screws.

[0015] According to the reverse thrust fairing structure of the launch vehicle provided by the present invention, a plurality of bolt holes are opened on a circle of the bottom edge of the fairing body, so that the fairing body can be connected to the body of the launch vehicle through the bolt holes.

[0016] The reverse thrust fairing structure of the launch vehicle provided by the present invention, through the arrangement of a folding connector and a fixed connector, enables the head portion to be turned over around the folding connector when separation is required, by disengaging the connection state through the fixed connector. On the one hand, the turning of the head portion can be guided, making the separation of the head portion more stable and avoiding collision with the fairing main body or the rocket body. On the other hand, the mechanical connection method of the fixed connector and the folding connector makes the stability of the overall structure higher when separation is not required. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 It is a schematic diagram of the overall structure of the reverse thrust fairing structure provided by the present invention.

[0019] Figure 2 It is a schematic diagram of the internal structure of the reverse thrust fairing structure provided by the present invention.

[0020] Figure 3 The figure is a schematic diagram of the reverse thrust fairing structure provided by the present invention when viewed from above.

[0021] Figure 4 It is a specific structural schematic diagram of the folding connector in the reverse thrust fairing structure provided by the present invention.

[0022] Figure 5 It is a structural schematic diagram of the reverse thrust fairing structure provided by the present invention in a folded state.

[0023] Figure 6 It is a schematic diagram of the reverse thrust fairing structure in the related technology.

[0024] Reference numerals: 1. Fairing body; 2. End cap; 3. Connecting assembly; 31. Folding connector; 311. Breaking groove; 32. Fixed connector; 4. Reverse thrust device; 41. Nozzle; 42. Connecting lug.

[0025] 601. Fairing; 602. Front head; 603. Spring leaf; 604. Pull rope. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of explaining the embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limitations on the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0028] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" 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 mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0029] In the embodiments of the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0030] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the present invention. In this specification, the schematic representations of the above terms are not necessarily for the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0031] In related technologies, such as Figure 6 As shown, it includes a front head 602 and a fairing 601. The front head 602 and the fairing 601 are snap-fitted, and a spring sheet 603 is provided inside to connect them. A pull rod or a pull rope 604 is also installed on the outside of the fairing 601. One end of the pull rod or the pull rope 604 is connected to the reverse thrust fairing 601 itself, and the other end is installed at the front head 602 of the reverse thrust fairing 601, which is used for traction and recovery when the reverse thrust fairing 601 flies out. The entire front head 602 of the reverse thrust fairing 601 is generally machined as a whole to meet the strength requirements and appearance fairing requirements. Figure 6 As shown, the installation form of the existing reverse thrust fairing 601 front head 602 uses a spring sheet 603 to clamp the reverse thrust fairing 601 column section. During installation, external force is required to squeeze and bend the spring sheet 603 and the front head 602 to ensure that the bending position of the spring sheet 603 can be smoothly clamped into the groove of the fairing 601 column section, and the installation is relatively complicated. In addition, when installing the reverse thrust fairing 601 front head 602, it is impossible to observe the installation of the bending position of the spring sheet 603, and the front head 602 may not be able to pop out due to the deformation of the spring sheet 603. Since the connection method of the front head 602 is a non-mechanical fixed connection of a spring buckle, when the vibration of the arrow body is too large, the spring sheet 603 may fail and the connection may be disconnected in advance. The traction of the pull rod or the pull rope 604 may cause the flying fairing 601 front head 602 to return and hit the reverse thrust fairing 601 or the arrow body.

[0032] Regarding the problems in related technologies, such as Figure 1-Figure 3As shown, the present embodiment provides a reverse thrust fairing structure of a launch vehicle, comprising a fairing body 1 and a head portion 2; an installation space for installing a reverse thrust device 4 is formed in the fairing body 1; the head portion 2 is connected to the fairing body 1 through a connecting assembly 3, and is located at the end of the fairing body 1, so that the main body of the reverse thrust device 4 is located in the installation space, and the nozzle 41 of the reverse thrust device 4 is located in the head portion 2; the connecting assembly 3 comprises a folding connector 31 and a fixed connector 32, the folding connector 31 is arranged between the head portion 2 and the fairing body 1, and is located on the outer side wall of the fairing body 1; both sides of the head portion 2 and the top of the head portion 2 are provided with fixed connectors 32, and the fixed connectors 32 are used for fixed connection between the head portion 2 and the fairing body 1 and the rocket body; wherein the fixed connector 32 is configured so that when the reverse thrust device 4 generates a reverse thrust airflow, the fixed connector 32 can be broken to be disconnected, so that the head portion 2 is folded around the folding connector 31 toward the outer side of the fairing body 1. The fairing is located on the outer wall of the launch vehicle under normal conditions. When separation is required, the head portion 2 is opened to achieve reverse thrust and accelerate separation. The head portion 2 of this embodiment is connected by a folding connector 31 and a fixed connector 32, so that it has higher stability under normal conditions. When separating, the fixed connector 32 is detached and the folding connector 31 is set, so that it can be stably folded under the guidance of the folding connector 31 to avoid collision of the head portion 2.

[0033] Specifically, the fairing body 1 is a cylindrical shell structure, and the installation space inside it can accommodate the installation of the reverse thrust device 4. The head portion 2 is connected to the fairing and the internal space is not connected to the installation space. The reverse thrust device 4 is a reverse thrust rocket, which is arranged in the installation space by connecting fixings and the like, and most of the nozzle of the reverse thrust rocket is located in the head portion 2, and the tail of the nozzle is a nozzle 41, which is located in the head portion 2, so that when the reverse thrust rocket is working, a force can be applied to the head portion 2, and the fixed connection 32 of the head portion 2 can be disconnected after the force is applied, so that the head portion 2 can be folded and rotated along the folding connection 31.

[0034] When applying specific Figure 1 , Figure 5As shown, the end cap 2 is an arc-shaped shell structure, and the nozzle 41 of the reverse thrust device 4 is directly opposite to the column of the end cap 2. Preferably, the nozzle of the reverse thrust device 4 can be inclined to the side of the end cap 2 away from the arrow body, so that the airflow ejected by the reverse thrust device 4 can better act on the arc-shaped shell structure of the end cap 2 to obtain a better pushing effect. When the reverse thrust device 4 is started, the nozzle 41 can eject airflow to act on the end cap 2, thereby applying a force to the end cap. The connection preload force of the fixed connection member 32 and the fracture stress of the connecting piece body are much smaller than the force applied by the reverse thrust device 4, so that the fixed connection member 32 is separated under the force of the reverse thrust device 4, and the end cap 2 can be pushed to rotate along the folding connection member 31. This method can ensure that the end cap 2 can be stably folded when the reverse thrust device 4 acts, so that the end cap 2 can be opened, and in the process of folding, due to the restriction of the folding connection member 31, it will not collide with other parts, and opening by folding can improve the stability of opening and improve the success rate of opening.

[0035] It is understandable that during the launch of the carrier rocket, the rocket body will vibrate, and this vibration will be transmitted to the reverse thrust fairing. In this embodiment, the fixed connector 32 and the folding connection are set, so that the head portion 2 is initially connected to the rocket body by a mechanical connection, thereby improving its stability. When it is necessary to open, the fixed connector 32 can be disengaged under the action of the reverse thrust device 4 and the head portion 2 is folded around the folding connector 31, so that the head portion 2 can be stably opened, and the stability of the opening is improved. In addition, since the folding is performed with the folding member as the folding center during the opening process, it will not collide with other components, further improving its stability. The head portion 2 and the fairing body 1 are connected in a split manner, and the split connection can reduce the connection difficulty and greatly reduce the processing difficulty of the head portion 2, thereby realizing mass production. In addition, the split connection method can observe the installed docking surface during the entire installation process, thereby ensuring the quality of the installation and improving the consistency.

[0036] According to some embodiments provided by the present invention, the reverse thrust fairing structure further includes a reverse flow baffle, which is arranged in the installation space and located at one end close to the head portion 2. When the reverse thrust device 4 is in action, the high-temperature airflow will be in the head portion 2 and will be transmitted to the installation space to affect the action of the reverse thrust device 4. This embodiment can isolate the installation space of the head portion 2 and the reverse thrust device 4 by setting the reverse flow baffle, thereby effectively preventing the high-temperature airflow from returning to the installation space.

[0037] It can be understood that the reverse flow baffle is arranged at the throat of the reverse thrust rocket nozzle, and the nozzle throat of the reverse thrust rocket is located near the connection position between the head portion 2 and the fairing body 1, thereby effectively preventing the reverse thrust rocket nozzle from backflow.

[0038] In some embodiments, a connecting lug 42 is provided on the body of the reverse thrust device 4, one side of the reverse flow baffle is connected to the connecting lug 42, and the other side of the reverse flow baffle is used to connect to the body of the launch vehicle. The reverse flow baffle is used to block the space in the end cap 2, and when connected, the reverse flow baffle can improve its bearing capacity through the connection of the connecting lug 42, so that the stability of the reverse flow baffle is higher.

[0039] Specifically, one side of the reverse baffle is connected to the connecting ear 42 by screws, and the other side of the reverse baffle is provided with a screw hole, so that the reverse baffle is connected to the outer wall of the rocket body by screws during connection, thereby enabling the reverse thrust fairing to be connected and attached to the outer wall of the rocket body.

[0040] It is understandable that the connection of the reverse flow baffle makes the structural strength of the reverse thrust fairing structure connected to the rocket body higher, and a high-strength connection can be achieved. In specific applications, the reverse flow baffle can be made of high-temperature resistant metal or non-metal material.

[0041] According to some embodiments provided by the present invention, the folding connector 31 includes a folding plate, one end of which is connected to the end cap 2, and the other end of which is connected to the fairing body 1, and a breaking groove 311 is provided between the two ends of the folding plate, so that the end cap 2 is folded along the breaking groove 311. Conventional folding plates have a certain resistance when folding, and the provision of the breaking groove 311 in this embodiment can effectively reduce the resistance during the folding process, thereby improving the response speed and smoothness of the folding of the end cap 2.

[0042] Specifically, the folding plate is a block structure. By processing the breaking groove 311 on the block structure, the resistance at the beginning of the breaking groove 311 is made smaller, so that quick folding can be achieved.

[0043] In some specific examples, the cross section of the breaking groove 311 is a V-shaped groove structure, so that the two surfaces of the V-shaped groove structure fit together and break when the end cap 2 is folded. After the end cap 2 is opened, in order to avoid the end cap 2 from affecting the arrow body or other parts, this embodiment sets the breaking groove 311 as a V-shaped groove structure, so that it can break during the folding process, so that the end cap 2 can be separated from the fairing body 1, thereby avoiding the end cap 2 from affecting other parts.

[0044] It is understandable that the V-groove structure makes the two opposite surfaces of the breaking groove 311 inclined surfaces, and can provide space for the folding of the head portion 2 during the rotation process, so that it can be broken when folded to a certain extent, thereby achieving the detachment of the head portion 2.

[0045] Specifically, the folding plate can be made of a material with a certain toughness, and the depth of the V-groove structure can be designed so that the connection can be disconnected after folding, so that the end cap 2 can be detached.

[0046] In the specific configuration, the folding plate includes a copper-aluminum alloy plate, and the minimum thickness of the copper-aluminum alloy plate is 0.3 mm. It is understandable that the configuration of the copper-aluminum alloy plate can make it have a certain toughness, so that it can be folded under a force and can be broken along the breaking groove 311, so that the head portion 2 is disconnected.

[0047] Specifically, the folding plate is made of 2214-T6 aluminum material, and a breaking groove 311 is machined on the copper-aluminum alloy plate, so that the minimum thickness of the copper-aluminum alloy plate is 0.3 mm, so that it can be broken after being folded into place.

[0048] In a specific implementation manner, Figure 4 As shown, the notch angle a of the V-shaped groove structure is 45°-60°. By limiting the design of the angle a, the material can be broken just after folding, and the head portion 2 can be stably separated. Furthermore, the notch angle can be adjusted according to actual needs to control the flying angle.

[0049] According to some embodiments provided by the present invention, the fixed connection member 32 includes a fixed connection aluminum sheet, and a plurality of fixed connection aluminum sheets for connecting to the body of the launch vehicle are arranged at intervals on the edge of the head portion 2. The fixed connection sheet needs to be disconnected when the reverse thrust device 4 is in motion. In this embodiment, the aluminum sheet structure is limited so that it can be broken under the force of the reverse thrust device 4, thereby achieving stable folding of the head portion 2.

[0050] Specifically, the fixed connection aluminum sheet is a thin aluminum sheet structure, which is connected by welding or screwing, etc. Through the design of the material, the fracture stress of the fixed connection aluminum sheet is less than the force applied by the reverse thrust device 4, so that when the reverse thrust device 4 applies the force, the fixed connection aluminum sheet breaks instantly, and the head portion 2 is folded and separated, thereby improving the structural strength in the normal state, and the difficulty of connection and installation is relatively low. It can also respond quickly when the head portion 2 is opened, and realize the bending and separation of the head portion 2.

[0051] In the specific configuration, connecting screws are provided on the side walls on both sides of the fairing body 1, and correspondingly, fixed connecting aluminum sheets are provided on both sides of the head portion 2. The fixed connecting aluminum sheets are connected to the connecting screws. The connecting screws are connected to the fairing body 1, and the fixed connecting aluminum sheets are connected to the connecting screws so that they have a pre-tightening force, thereby being able to maintain the stability of the head portion 2. When the reverse thrust device 4 acts, the stress required for the fixed connecting aluminum sheet strength is much smaller than the force of the reverse thrust device 4, and the fixed connecting aluminum sheet breaks, thereby causing the head portion 2 to be separated from the connection with the fairing body 1, thereby realizing the folding of the head portion 2.

[0052] It can be understood that the connection between the head portion 2 and the arrow body adopts a fixed connection aluminum sheet, and the connection between the head portion 2 and the fairing main body 1 also adopts a fixed connection aluminum sheet, so that it can break quickly under the action of force, so that the head portion 2 can be quickly folded and detached.

[0053] According to some embodiments provided by the present invention, a plurality of bolt holes are provided on a circle around the bottom edge of the fairing body 1, so as to connect the fairing body 1 to the body of the launch vehicle through the bolt holes. The connection method through the bolt holes can reduce the difficulty of assembly, and the overall stability can be improved through the mechanical connection method.

[0054] Specifically, the bottom surface of the bottom of the fairing main body 1 is in contact with the rocket body. A sealing ring is provided on the bottom surface of the bottom of the fairing main body 1. Similarly, a sealing ring is also provided on a circle at the bottom of the head portion 2. The setting of the sealing ring can achieve sealing between the reverse thrust fairing structure and the rocket body, thereby avoiding the influence of the external environment on the internal structure of the reverse thrust fairing.

[0055] It is understandable that the bolt connection can make the fairing body 1 tightly attached to the arrow body, thereby compressing the sealing ring and improving the sealing performance. Similarly, the head 2 can compress the sealing ring by fixing the connecting piece 32 to improve the sealing performance.

[0056] Through the description of the above embodiments, the technicians in this field can clearly understand that each embodiment, through the arrangement of the folding connector 31 and the fixed connector 32, can make it possible to detach the fixed connector 32 from the connection state when separation is required, so that the head portion 2 can be flipped around the folding connector 31. On the one hand, it can guide the flipping of the head portion 2, making the detachment of the head portion 2 more stable and avoiding collision with the fairing body 1 or the rocket body. On the other hand, through the mechanical connection of the fixed connector 32 and the folding connector 31, the stability of the overall structure is higher when separation is not required. The purely mechanical connection using screws and support plate nuts is more reliable than the existing spring buckle connection, and different thicknesses of connecting plates can be calculated according to the loads of different types of launch vehicles to meet diverse usage requirements.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A reverse thrust fairing structure of a launch vehicle, characterized in that: include: A fairing body, wherein a mounting space for mounting a thrust reverser is formed in the fairing body; A head portion, which is connected to the fairing body through a connecting assembly and is located at the end of the fairing body, so that the main body of the thrust reverser is located in the installation space and the nozzle of the thrust reverser is located in the head portion; The connection assembly includes a folding connection piece and a fixed connection piece, wherein the folding connection piece is arranged between the end cap and the fairing body and is located on the outer side wall of the fairing body; the fixed connection pieces are arranged on both sides of the end cap and the top of the end cap, and are used for fixed connection between the end cap, the fairing body and the arrow body; Wherein, the fixed connection piece is configured so that when the reverse thrust device generates a reverse thrust airflow, the fixed connection piece can be disconnected so that the head portion can be folded around the folding connection piece toward the outside of the fairing body.

2. The reverse thrust fairing structure of a launch vehicle according to claim 1, characterized in that: The reverse thrust fairing structure also includes a reverse flow baffle, which is arranged in the installation space and located at one end close to the head portion.

3. The reverse thrust fairing structure of a launch vehicle according to claim 2, characterized in that: A connecting lug is provided on the main body of the reverse thrust device, one side of the reverse flow baffle is connected to the connecting lug, and the other side of the reverse flow baffle is used to be connected to the body of the launch vehicle.

4. The reverse thrust fairing structure of a launch vehicle according to claim 1, characterized in that: The folding connecting member includes a folding plate, one end of which is connected to the head portion, and the other end of which is connected to the fairing body. A breaking groove is provided between the two ends of the folding plate so that the head portion can be folded along the breaking groove.

5. The reverse thrust fairing structure of a launch vehicle according to claim 4, characterized in that: The cross section of the breaking groove is a V-shaped groove structure, so that when the head portion is folded, two surfaces of the V-shaped groove structure fit together and break.

6. The reverse thrust fairing structure of a launch vehicle according to claim 5, characterized in that: The notch angle of the V-shaped groove structure is 45°-60°.

7. The reverse thrust fairing structure of a launch vehicle according to claim 5, characterized in that: The folding plate comprises a copper-aluminum alloy plate, and the minimum thickness of the copper-aluminum alloy plate is 0.3 mm.

8. The reverse thrust fairing structure of a launch vehicle according to claim 1, characterized in that: The fixed connection member includes a fixed connection aluminum sheet, and a plurality of the fixed connection aluminum sheets for connecting with the body of a launch vehicle are arranged at intervals on the edge of the head portion.

9. The reverse thrust fairing structure of a launch vehicle according to claim 8, characterized in that: Connecting screws are arranged on the side walls on both sides of the fairing body, and correspondingly, the fixing connecting aluminum sheets are arranged on both sides of the head portion, and the fixing connecting aluminum sheets are connected to the connecting screws.

10. The reverse thrust fairing structure of a launch vehicle according to claim 1, characterized in that: A plurality of bolt holes are provided on a circle around the bottom edge of the fairing main body, so that the fairing main body can be connected to the body of the launch vehicle through the bolt holes.

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