Rotary throwing hinge mechanism for detachable fairing

Abstract

The invention provides a detachable fairing rotary throwing hinge mechanism. The detachable fairing rotary throwing hinge mechanism comprises a fairing upper half cover, a fairing lower half cover, a rotary throwing hinge structure and a hinge support. The rotary throwing hinge structure is mounted on the upper half fairing and the lower half fairing through screws; the hinge support is installed on a cabin structure at the rear end of the fairing, the groove face of the arc section at the root of the rotary throwing hinge structure is in contact fit with a guide rib on the hinge support, transverse locking of the fairing and the hinge support is achieved, and a limiting pin of the rotary throwing hinge structure is arranged in a limiting groove in the hinge support. Longitudinal locking of the fairing and the hinge support is achieved. After transverse unlocking and longitudinal unlocking of the fairing are completed, longitudinal separation force provided by the separation energy enables the groove face of the arc section of the root of the rotary throwing hinge structure to rotate along a guide rib of the hinge support, and therefore reliable rotary throwing of the fairing is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of fairing separation, and in particular relates to a detachable fairing rotation-throw hinge mechanism, and in particular to a quick-detachable fairing rotation-throw hinge mechanism. Background Art

[0002] The fairing is an important component of rockets and other aircraft, maintaining the aerodynamic shape and protecting the internal equipment. When the flight reaches a certain altitude, the fairing must be separated in time to allow the internal equipment to operate.

[0003] The rotational throwing separation method means that after the fairing is unlocked horizontally and vertically, the two halves of the fairing rotate around the root of the hinge under the push of the separation energy, and when they rotate to a certain angle, they disengage from the hinge support at the rear end, thereby realizing the rotational throwing of the fairing.

[0004] Patent document CN113203326A discloses a fairing spin-throw hinge structure. When the fairing half-cover rotates around the hinge under the action of separation, when the rotation angle of the fairing half-cover is less than the top angle α, the limit pin on the rotating support and the limit groove on the fixed support limit the fairing half-cover from separating from the rotating shaft; when the rotation angle of the fairing half-cover is greater than the top angle α, before reaching the unhooking angle θ, the rotating hole on the rotating support must ensure that the thrust of the rocket body can fully act on the rotating support; after the rotation angle of the fairing half-cover exceeds the unhooking angle θ, the rotating hole on the rotating support and the limit groove on the fixed support do not hinder the automatic separation of the fairing half-cover and the rocket body.

[0005] In existing technologies, some hinge mechanisms suffer from complex structures, heavy weight, and difficulty in positioning and installation. Furthermore, the hinge and hinge support achieve fairing rotation solely through the rotation of a stop pin and a rotating shaft, placing high demands on assembly clearance and material strength between the stop pin and the rotating shaft, making deviation from the movement trajectory a problem. To address this issue, the present invention designs a fairing spin-and-throw hinge mechanism that allows for rapid assembly and disassembly, with a high degree of rigidity in the rotating assembly, addressing these issues. Summary of the Invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a detachable fairing rotation and throwing hinge mechanism.

[0007] According to the present invention, a detachable fairing rotation and throwing hinge mechanism includes: a fairing upper half cover 1, a fairing lower half cover 2, a rotation and throwing hinge structure 3, and a hinge support 6;

[0008] The hinge support 6 is installed on the rear end cabin structure of the upper half cover 1 and the lower half cover 2 of the fairing, and the rotary hinge structure 3 is installed on the upper half cover 1 and the lower half cover 2 of the fairing.

[0009] Preferably, the spin-throw hinge structure 3 includes: a hinge body 31, a limit pin 4, and a positioning screw 5;

[0010] A mounting hole is provided inside one end of the hinge body 31 , a limiting pin 4 is placed in the mounting hole, and a positioning screw 5 is placed on the hinge body 31 and parallel to the mounting hole.

[0011] Preferably, a rotation hole 41 is provided at the front end of the tight limiting pin 4, and a positioning platform 42 is provided at the rear end.

[0012] Preferably, the hinge support 6 is provided with a limiting groove 62 and a guide rib 61;

[0013] The guide rib 61 is connected to the arc segment groove surface, and the upper half cover 1 of the fairing, the lower half cover 2 of the fairing and the hinge support 6 are laterally locked.

[0014] Preferably, one end of the hinge body 31 is a circular arc segment groove surface.

[0015] Preferably, when the rotary-throw hinge mechanism 3 is in the initial installation state, the limiting pin 4 is placed in the installation hole of the hinge body 31 and is tightened and fixed by the positioning screw 5 .

[0016] Preferably, when the rotary hinge mechanism 3 is in the final installation state, the limit pin 4 slides out of the installation hole to the final position, the limit pin 4 is placed on both sides of the hinge body 31, and the positioning platform 42 of the limit pin 4 is pressed and fixed by the positioning screw 5.

[0017] Preferably, when the hinge mechanism 3 is in the final installation state, the limit pin 4 is placed in the limit groove 62 on the hinge support 6, and the upper half cover 1 of the fairing, the lower half cover 2 of the fairing and the hinge support 6 are longitudinally locked.

[0018] Preferably, when installing the hinge 3:

[0019] First, the groove surface of the root arc segment is brought into contact with the guide rib 61 on the hinge support 6, and then the guide rib 61 is rotated inward to be installed on the upper half cover 1 and the lower half cover 2 of the fairing, thereby achieving the horizontal locking of the fairing and the hinge support 6;

[0020] Loosen the positioning screw 5 to release the limit pin 4, use a tool to press the root of the limit pin 4 through the channel in the middle of the hinge body 31 to push the limit pin 4 out of the mounting hole to the final position, so that the limit pin 4 is placed on both sides of the hinge body 31; rotate the limit pin 4 with the tool so that the positioning platform 42 of the limit pin 4 faces upward; tighten the positioning screw 5 to press the positioning platform 42 of the limit pin 4 to complete the assembly of the spin-throw hinge structure 3; at this time, the limit pin 4 is just placed in the limit groove 62 on the hinge support 6, realizing the longitudinal locking of the fairing and the hinge support 6.

[0021] A fairing mechanism provided according to the present invention includes the detachable fairing rotation and throwing hinge mechanism.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention has a simple and compact structure, is easy to process, can be quickly assembled and disassembled, has low cost, and has high reliability in rotation and throwing.

[0024] 2. The present invention enables the split-flap fairing to have better assembly performance and a larger effective space. The fairing can maximize the use of the internal space, which is beneficial to the assembly and lightweight requirements of the fairing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0026] Figure 1 This is a schematic diagram of the structure of the rotary-throwing hinge of the present invention;

[0027] Figure 2 It is a schematic diagram of the main cross-sectional view structure of the present invention;

[0028] Figure 3 This is a schematic diagram of the assembly of the spin-throw hinge structure, fairing, and hinge support of the present invention;

[0029] Figure 4 This is a schematic diagram of the layout of the rotary-throwing hinge structure of the present invention;

[0030] Figure 5 This is a schematic diagram of the assembly of the components of the rotary-throwing hinge structure of the present invention;

[0031] Figure 6 This is a schematic structural diagram of the initial state of the spin-throw hinge structure of the present invention;

[0032] Figure 7 This is a schematic structural diagram of the final state of the spin-throw hinge structure of the present invention;

[0033] Figure 8 It is a schematic diagram of the hinge support structure of the present invention.

[0034] The figure shows:

[0035] DETAILED DESCRIPTION

[0036] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0037] An embodiment of the present invention provides a detachable fairing rotation-throw hinge mechanism, comprising a fairing upper half 1 and a fairing lower half 2 , a rotation-throw hinge structure 3 , and a hinge support 6 .

[0038] like Figure 2-Figure 5 The hinge structure 3 is fixed to the upper and lower fairing halves 1 and 2 by screws. The hinge support 6 is mounted on the rear end of the fairing. The hinge support 6 is equipped with a retaining groove 62 and a guide rib 61. When installing the hinge 3, the grooved surface of the circular arc section at the base is first brought into contact with the guide rib 61 on the hinge support 6. The hinge is then rotated inwardly onto the upper and lower fairing halves 1 and 2, allowing the guide rib 61 to secure the fairing to the hinge support 6 laterally.

[0039] like Figure 1 As shown, the rotary hinge structure 3 includes: a hinge body 31, a limit pin 4, and a positioning screw 5; a mounting hole is provided in one end of the hinge body 31, the limit pin 4 is placed in the mounting hole, and the positioning screw 5 is placed on the hinge body 31 and is parallel to the mounting hole.

[0040] like Figure 6 As shown, the initial installation state of the rotary hinge structure 3 is that the two limit pins 4 are placed in the mounting hole of the hinge body 31 without being exposed. In the middle channel, it can be seen that the root of the limit pin 4 is in contact with the end face of the channel, and the limit pin 4 is tightened by the positioning screw 5 to prevent the limit pin 4 from slipping out of the mounting hole of the hinge body 31.

[0041] The front end of the limit pin 4 is provided with a rotating hole 41 that allows for adjustment of rotation, and the rear end is provided with a positioning platform 42 that allows for compression. The limit pin 4 can be compressed or loosened by tightening or loosening the positioning screw 5, thereby adjusting the position of the limit pin 4 inside the mounting hole of the hinge body 31.

[0042] like Figure 7 As shown, loosen the positioning screw 5 to release the limit pin 4, use a tool to press the root of the limit pin 4 through the channel in the middle of the hinge body 31 to push the limit pin 4 out of the mounting hole to the final position, so that the limit pin 4 is placed on both sides of the hinge body 31; the limit pin 4 can be rotated by a tool so that the positioning platform 42 of the limit pin 4 faces upward; tighten the positioning screw 5 to press the positioning platform 42 of the limit pin 4 to complete the assembly of the spin-throw hinge structure 3; at this time, the limit pin 4 is just placed in the limit groove 62 on the hinge support 6, realizing the longitudinal locking of the fairing and the hinge support 6.

[0043] After the fairing is unlocked laterally and longitudinally, the longitudinal separation force provided by the separation energy causes the groove surface of the arc segment at the root of the rotary-throwing hinge structure 3 to rotate along the guide rib 61 of the hinge support 6, thereby realizing reliable rotary throwing of the fairing.

[0044] The present invention can optimize the longitudinal locking force by adjusting the diameter of the limiting pin 4 .

[0045] The present invention can optimize the transverse locking force and the fairing separation angle by adjusting the contact area and arc segment shape between the arc segment groove surface at the root of the hinge body 31 and the guide rib 61 of the hinge support 6 .

[0046] The arc groove surface at the root of the hinge body 31 of the present invention and the guide rib 61 of the hinge support 6 have greater rigidity, which significantly improves the reliability of the fairing rotation and ejection compared to the traditional limit shaft and shaft rotation method.

[0047] It should be noted that this specification is merely an illustrative description and elaboration of the spirit and essence of the present invention, and any changes and substitutions to the present invention fall within the scope of protection of the present invention.

[0048] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0049] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A detachable fairing spin-throw hinge mechanism, characterized in that: include: Fairing upper half cover (1), fairing lower half cover (2), spin-throw hinge structure (3), hinge support (6); The hinge support (6) is installed on the rear end cabin structure of the upper fairing half cover (1) and the lower fairing half cover (2), and the rotary hinge structure (3) is installed on the upper fairing half cover (1) and the lower fairing half cover (2).

2. The detachable fairing spin-throw hinge mechanism according to claim 1, characterized in that: The rotary-throw hinge structure (3) comprises: a hinge body (31), a limiting pin (4), and a positioning screw (5); A mounting hole is provided inside one end of the hinge body (31), a limiting pin (4) is placed in the mounting hole, and a positioning screw (5) is placed on the hinge body (31) and is parallel to the mounting hole.

3. The detachable fairing spin-and-throw hinge mechanism according to claim 2, characterized in that: The front end of the tight limiting pin (4) is provided with a rotation hole (41), and the rear end is provided with a positioning platform (42).

4. The detachable fairing rotation hinge mechanism according to claim 1, characterized in that: The hinge support (6) is provided with a limiting groove (62) and a guide rib (61); The guide rib (61) is connected to the arc segment groove surface, and the upper half cover (1) and the lower half cover (2) of the fairing are laterally locked with the hinge support (6).

5. The detachable fairing spin-and-throw hinge mechanism according to claim 2, characterized in that: One end of the hinge body (31) is a circular arc segment groove surface.

6. The detachable fairing spin-and-throw hinge mechanism according to claim 2, characterized in that: When the rotary-throwing hinge mechanism (3) is in an initial installation state, the limiting pin (4) is placed in the installation hole of the hinge body (31) and is pressed and fixed by the positioning screw (5).

7. The detachable fairing spin-and-throw hinge mechanism according to claim 2, characterized in that: When the rotary hinge mechanism (3) is in the final installation state, the limit pin (4) slides out of the installation hole to the final position, the limit pin (4) is placed on both sides of the hinge body (31), and is fixed by pressing the positioning platform (42) of the limit pin (4) with the positioning screw (5).

8. The detachable fairing spin-and-throw hinge mechanism according to claim 1, characterized in that: When the hinge mechanism (3) is in the final installation state, the limit pin (4) is placed in the limit groove (62) on the hinge support (6), and the upper half cover (1) and the lower half cover (2) of the fairing are locked with the hinge support (6) in the longitudinal direction.

9. The detachable fairing spin-and-throw hinge mechanism according to claim 4, characterized in that: When installing the hinge (3): First, the groove surface of the root arc segment is brought into contact with the guide rib (61) on the hinge support (6), and then the guide rib (61) is rotated inwardly and installed on the upper half cover (1) and the lower half cover (2) of the fairing, thereby achieving lateral locking of the fairing and the hinge support (6); Loosen the positioning screw (5) to release the limiting pin (4), use a tool to press the root of the limiting pin (4) through the channel in the middle of the hinge body (31) to push the limiting pin (4) outward to slide out of the installation hole to the final position, so that the limiting pin (4) is placed on both sides of the hinge body (31); rotate the limiting pin (4) with the tool so that the positioning platform (42) of the limiting pin (4) faces upward; tighten the positioning screw (5) to press the positioning platform (42) of the limiting pin (4), and complete the assembly of the rotary hinge structure (3); at this time, the limiting pin (4) is just placed in the limiting groove (62) on the hinge support (6), realizing the longitudinal locking of the fairing and the hinge support (6).

10. A fairing mechanism, characterized in that: The invention comprises the detachable fairing spin-throw hinge mechanism according to any one of claims 1 to 9.

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