A built-in fairing pre-tightening and rotation separation hinge mechanism

Abstract

The present invention discloses a built-in fairing pre-tightening and rotational separation hinge mechanism, which relates to the field of launch vehicle technology and solves the problems of fairing separation methods such as complex structure, leakage of the separation mechanism affecting the aerodynamic shape of the aircraft, and lack of axial pre-tightening function. The present invention has an upper fairing and a cabin body movably connected; a hinge structure is provided on the upper fairing, and a cabin body slot structure is provided on the cabin body; one end of the hinge structure is inserted into a slot in the cabin body slot structure, and a pre-tightening structure is provided on the other end, and the pre-tightening structure rests on the inner wall of the cabin body slot structure. The hinge structure, the pre-tightening structure and the cabin body slot cooperate to achieve circumferential positioning and axial pre-tightening of the upper fairing; a step structure is provided on the cabin body, and the upper fairing is buckled on the step structure. The present invention can achieve circumferential positioning and axial pre-tightening functions of the fairing, and uses the hinge as a flip fulcrum to ensure that the flip trajectory is controllable, avoiding collisions or locking; at the same time, it reduces the influence of the separation mechanism on the aerodynamic shape of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of launch vehicles, in particular to a built-in fairing pre-tightening and rotation separation hinge mechanism. Background Art

[0002] When a launch vehicle flies in the atmosphere, the fairing is used to protect the satellite from harmful environmental effects such as aerodynamic forces, aerodynamic heating, and acoustic vibrations, and is an important component of the launch vehicle. When the rocket reaches a certain altitude, the fairing must be separated and discarded in a timely manner to allow the payload to operate normally and reduce the subsequent mass of the vehicle, so that the vehicle can effectively perform its functions. Currently, the methods for separating rocket fairings at home and abroad include integral fairing removal, two-petal rotational separation, two-petal horizontal push separation, multi-petal rotational separation, and multi-petal horizontal push separation. However, existing fairing separation methods have problems such as complex structure, lack of axial preload function, and exposed separation mechanism that affects the aerodynamic shape of the vehicle. Summary of the Invention

[0003] To address the aforementioned issues with existing fairing separation methods, including complex structures, leaky separation mechanisms that affect the aircraft's aerodynamic shape, and a lack of axial preload, the present invention proposes a built-in fairing preload and rotary separation hinge mechanism. This mechanism achieves circumferential positioning of the fairing on the cabin and provides axial preload. Using the hinge as a flipping fulcrum ensures a controllable flipping trajectory, preventing collisions or locking. Furthermore, the built-in fairing preload and rotary separation hinge mechanism is simple and reliable, minimizing the impact of the separation mechanism on the aircraft's aerodynamic shape.

[0004] The present invention proposes a built-in fairing pre-tightening and rotational separation hinge mechanism, which specifically includes an upper fairing and a cabin, and the upper fairing and the cabin are movably connected; a hinge structure is provided on the upper fairing, and a cabin slot structure is provided on the cabin, and the hinge structure and the cabin slot structure are movably connected; one end of the hinge structure is inserted into a slot in the cabin slot structure, and a pre-tightening structure is provided at the other end of the hinge structure, and the pre-tightening structure rests on the inner wall of the cabin slot structure; a step structure is provided on the cabin, and the upper fairing is buckled on the step structure.

[0005] Furthermore, the hinge structure includes an upper inner block and several upper fairing screws, and the upper fairing is connected to the upper inner block through the several upper fairing screws; two hinges are provided at one end of the upper inner block, and a pre-tightening structure is provided at the other end, and the hinges are inserted into slots in the cabin slot structure.

[0006] Furthermore, the hinge is a wedge-shaped structure.

[0007] Furthermore, the head of the hinge exceeds the lower surface of the upper inner block.

[0008] Furthermore, the pre-tightening structure includes an upper outer block and two top screws. The upper inner block is provided with two internal threaded holes. The top screws are arranged in the internal threaded holes and their ends are in contact with the upper outer block to press the upper outer block against the inner wall of the cabin groove structure.

[0009] Furthermore, the upper outer block is a U-shaped structure, two sliders are provided on the inner side of the upper outer block, and a slide groove is provided on both side edges of the upper inner block, and the sliders are slidably arranged in the slide grooves.

[0010] Furthermore, a plurality of grooves are provided on the upper surface of the upper inner block, and a plurality of bosses are provided on the upper fairing, and the bosses are embedded in the grooves.

[0011] Furthermore, the cabin groove structure includes a shallow cabin groove, a deep cabin groove and an upper pressure block. The shallow cabin groove and the deep cabin groove are connected. The hinge structure and the pre-tightening structure are arranged in the shallow cabin groove, and the upper pressure block is arranged in the deep cabin groove. Two slots are arranged on the upper pressure block, and the cross-section of the slots is triangular.

[0012] Furthermore, the upper pressing block is provided with three through holes, and the through holes are waist-shaped holes.

[0013] Furthermore, a chamfered structure is provided on the stepped structure.

[0014] The beneficial effects of the built-in fairing pre-tightening and rotation separation hinge mechanism described in the present invention are:

[0015] (1) The present invention discloses a built-in fairing pre-tightening and rotational separation hinge mechanism, which overcomes the problems of the existing fairing separation method, such as complex structure, lack of axial pre-tightening function, and exposed separation mechanism affecting the aerodynamic shape of the aircraft. The hinge connection structure is an insert-type design, and the hinge shape is wedge-shaped. The upper fairing is flipped with the hinge as the flip fulcrum and separated according to a predetermined motion trajectory, thereby avoiding collision or locking between the upper fairing and the aircraft.

[0016] (2) The present invention describes a built-in fairing pre-tightening and rotational separation hinge mechanism, in which the upper fairing is buckled on the stepped structure of the cabin, the upper outer block and the upper inner block are slidably matched, and the upper outer block is pressed against the inner wall of the cabin groove under the action of the top screw, thereby applying a pre-tightening force to the upper fairing to achieve the axial pre-tightening function; at the same time, by embedding the upper outer block and the upper inner block into the cabin groove, the upper inner block and the upper fairing are connected, thereby achieving the circumferential positioning function of the upper fairing. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0018] In the attached figure:

[0019] Figure 1 It is a cross-sectional view of a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

[0020] Figure 2 It is a top view of a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

[0021] Figure 3 The invention discloses a built-in fairing pre-tightening and rotation separation hinge mechanism that does not include the axonometric measurement of the upper fairing. Figure 1 ;

[0022] Figure 4 The invention discloses a built-in fairing pre-tightening and rotation separation hinge mechanism that does not include the axonometric measurement of the upper fairing. Figure 2 ;

[0023] Figure 5 It is an axonometric view of a cabin with a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

[0024] Figure 6 It is a structural schematic diagram of the upper inner block of a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

[0025] Figure 7 It is a partial cross-sectional view of the upper inner block of the built-in fairing pre-tightening and rotation separation hinge mechanism of the present invention;

[0026] Figure 8 It is a structural schematic diagram of the upper outer block of a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

[0027] Figure 9 This is a front view of an upper pressing block of a hinge mechanism with a built-in fairing pre-tightening and rotation separation according to the present invention;

[0028] Figure 10 It is a side view of an upper pressing block of a hinge mechanism with built-in fairing pre-tightening and rotation separation according to the present invention;

[0029] Figure 11 It is a top view of an upper pressing block of a hinge mechanism with built-in fairing pre-tightening and rotation separation according to the present invention;

[0030] Among them: 1-upper fairing, 1.1-boss, 2-cabin, 2.1-shallow cabin groove, 2.2-deep cabin groove, 2.3-step structure, 3-upper inner block, 3.1-inner threaded hole, 3.2-groove, 3.3-hinge, 3.4-slide, 4-upper pressure block, 5-pressure block screw, 6-upper fairing screw, 7-upper outer block, 7.1-slider, 8-top screw, 9-slot. DETAILED DESCRIPTION

[0031] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0032] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0033] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0034] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0035] Specific implementation method 1: See Figures 1-11The embodiment of the present invention is described in detail. The built-in fairing pre-tightening and rotation separation hinge mechanism described in the embodiment of the present invention specifically includes an upper fairing 1 and a cabin 2, and the upper fairing 1 and the cabin 2 are movably connected; a hinge structure is provided on the upper fairing 1, and a cabin slot structure is provided on the cabin 2, and the hinge structure and the cabin slot structure are movably connected; one end of the hinge structure is inserted into a slot 9 in the cabin slot structure, and a pre-tightening structure is movably provided on the other end of the hinge structure, and the pre-tightening structure rests on the inner wall of the cabin slot structure; at the same time, the upper fairing The inner side of the fairing 1 is connected to a hinge structure, which contacts the wall of the cabin groove through a pre-tightening structure to achieve the circumferential positioning function of the upper fairing 1. The cabin 2 is provided with a stepped structure 2.3, and the upper fairing 1 is provided with a raised structure. The raised structure of the upper fairing 1 is snapped onto the stepped structure 2.3. Under the action of the pre-tightening structure, the upper fairing 1 moves in the direction opposite to the movement of the pre-tightening structure, so that the raised structure abuts against the stepped structure 2.3, achieving the pre-tightening function of the upper fairing 1. The stepped structure 2.3 is provided with a chamfered structure to prevent the upper fairing 1 from interfering with the stepped structure 2.3 when it is turned over.

[0036] The hinge structure includes an upper inner block 3 and a plurality of upper fairing screws 6. The upper fairing 1 is connected to the upper inner block 3 via the plurality of upper fairing screws 6. Two hinges 3.3 are provided at one end of the upper inner block 3, and a pre-tightening structure is provided at the other end. The hinges 3.3 are inserted into slots 9 in the cabin slot structure. The hinges 3.3 are wedge-shaped structures. The head of the wedge-shaped structure of the hinge 3.3 exceeds the lower surface of the upper inner block 3, that is, the head of the wedge-shaped structure of the hinge 3.3 protrudes a certain distance below the lower surface of the main part of the upper inner block 3, as shown in FIG. Figure 6 shown.

[0037] The pre-tightening structure includes an upper outer block 7 and two top screws 8. Two internal threaded holes 3.1 are provided on the upper inner block 3. The top screws 8 are arranged in the internal threaded holes 3.1 and the ends are in contact with the upper outer block 7. By rotating the top screws 8, the upper outer block 7 is pressed against the inner wall of the cabin groove structure.

[0038] The upper outer block 7 is a U-shaped structure, comprising a top block and two slide bars, the two slide bars being symmetrically arranged at both ends of the top block, two sliders 7.1 being arranged on opposite inner sides of the two slide bars, the cross section of the sliders 7.1 being trapezoidal; the top width of the sliders 7.1 being smaller than the bottom width, as shown in FIG. Figure 8 The edges of both sides of the main body of the upper inner block 3 are respectively provided with a chute 3.4, the chute 3.4 cross-section is trapezoidal, as Figure 6 The slider 7.1 is slidingly disposed in the chute 3.4, and under the action of the top screw 8 and the internal threaded hole 3.1, the upper outer block 7 is pushed to slide along the chute 3.4 and against the inner wall of the cabin groove.

[0039] The upper surface of the upper inner block 3 is provided with a plurality of grooves 3.2, and the upper fairing 1 is provided with a plurality of bosses 1.1, which are embedded in the grooves 3.2; during the pre-tightening process of the upper fairing 1, the bosses 1.1 and the grooves 3.2 cooperate with the upper fairing screws 6 to drive the upper fairing 1 to move, and the bosses 1.1 and the grooves 3.2 play the role of sharing the shear force of the upper fairing screws 6.

[0040] The cabin groove structure includes a shallow cabin groove 2.1, a deep cabin groove 2.2 and an upper pressure block 4. The shallow cabin groove 2.1 and the deep cabin groove 2.2 are connected. The depth of the deep cabin groove 2.2 is greater than the depth of the shallow cabin groove 2.1. The hinge structure and the pre-tightening structure are arranged in the shallow cabin groove 2.1. The upper pressure block 4 is arranged in the deep cabin groove 2.2. Two slots 9 are provided on the upper pressure block 4. The cross section of the slot 9 is triangular, as shown in FIG. Figure 9 and Figure 10 As shown; the slot 9 and the bottom surface of the deep cabin groove 2.2 form a right-angled triangle cavity, the hinge 3.3 is inserted into the cavity, the upper surface of the hinge 3.3 is in contact with the upper inclined surface of the right-angled triangle cavity, the head and the lower surface of the hinge 3.3 do not contact the bottom surface of the deep cabin groove 2.2, and are in a suspended state, thereby reserving space for the flipping of the hinge 3.3 to avoid interference.

[0041] The upper pressing block 4 is provided with three through holes, which are waist-shaped. The upper pressing block 4 is fixed in the deep cabin groove 2.2 by the pressing block screws 5. The position of the upper pressing block 4 can be adjusted as needed.

[0042] The specific installation and working process of the built-in fairing pre-tightening and rotation separation hinge mechanism described in the present invention is as follows:

[0043] Install the upper inner block 3 on the inner side of the upper fairing 1 through the upper fairing screws 6, and embed the boss 1.1 into the groove 3.2; insert the slider 7.1 of the upper outer block 7 into the slide groove 3.4; screw the top screw 8 into the internal threaded hole 3.1; install the upper fairing 1, the upper inner block 3 and the upper outer block 7 on the cabin 2, with the raised structure on the inner side of the upper fairing 1 resting on the stepped structure 2.3 of the cabin 2, and install the upper inner block 3 and the upper outer block 7 into the shallow cabin groove 2.1; screw Turn the top screw 8, and push the upper outer block 7 forward through the top screw 8 and press it against the inner wall of the shallow cabin groove 2.1. Under the pushing action of the upper outer block 7, the upper fairing 1 moves in the opposite direction, so that the raised structure of the upper fairing 1 and the upper outer block 7 are relatively clamped on the cabin 2, thereby realizing the pre-tightening of the upper fairing 1; install the upper pressure block 4 in the deep cabin groove 2.2, and tighten it with the pressure block screw 5, and the slot 9 set on the upper pressure block 4 is buckled above the hinge 3.3.

[0044] Upon receiving the separation command, the actuator at the front of the upper fairing 1 activates, pushing it to flip around hinge 3.3, driving the upper inner block 3 and upper outer block 7 out of the shallow chamber slot 2.1. After separation, the upper pressure block 4 remains in the deep chamber slot 2.2, while the remaining components are discarded. The rotating separation hinge mechanism ensures a controllable trajectory during fairing separation, preventing collisions or locking.

[0045] Summarizing the above-mentioned implementation cases, the built-in fairing pre-tightening and rotational separation hinge mechanism described in the present invention overcomes the problems of the existing fairing separation method, such as complex structure, lack of axial pre-tightening function, and exposed separation mechanism affecting the aerodynamic shape of the aircraft. The hinge connection structure is an insert-type design, and the hinge 3.3 is wedge-shaped. The upper fairing 1 flips with the hinge 3.3 as the flip fulcrum and separates according to a predetermined motion trajectory, thereby avoiding collision or locking between the upper fairing 1 and the aircraft. The built-in fairing pre-tightening and rotational separation hinge mechanism described in the present invention, the upper fairing 1 is buckled into the stepped structure 2.3 of the cabin 2, the upper outer block 7 and the upper inner block 3 are slidably matched, and under the action of the top screw 8, the upper outer block 7 is pressed against the inner wall of the cabin groove, thereby applying a pre-tightening force to the upper fairing 1 to achieve the axial pre-tightening function; at the same time, by embedding the upper outer block 7 and the upper inner block 3 into the cabin groove, the upper inner block 3 and the upper fairing 1 are connected, thereby achieving the circumferential positioning function of the upper fairing 1.

[0046] The specific embodiments described above further illustrate the objectives, technical solutions, and beneficial effects of the present invention. It should be understood that the above description is merely a specific embodiment of the present invention and is not intended to limit the invention. Reasonable combinations of the features described in the above embodiments are also possible. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of protection of the present invention.

Claims

1. A hinge mechanism with built-in fairing pre-tightening and rotation separation, characterized by: The invention comprises an upper fairing (1) and a cabin (2), wherein the upper fairing (1) and the cabin (2) are movably connected; a hinge structure is provided on the upper fairing (1), and a cabin groove structure is provided on the cabin (2), and the hinge structure and the cabin groove structure are movably connected; One end of the hinge structure is inserted into a slot (9) in the cabin groove structure, and the other end of the hinge structure is provided with a pre-tightening structure, which rests against the inner wall of the cabin groove structure; a step structure (2.3) is provided on the cabin (2), and the upper fairing (1) is buckled on the step structure (2.3); The hinge structure comprises an upper inner block (3) and a plurality of upper fairing screws (6), wherein the upper fairing (1) is connected to the upper inner block (3) via the plurality of upper fairing screws (6); one end of the upper inner block (3) is provided with two hinges (3.3), and the other end is provided with a pre-tightening structure, and the hinges (3.3) are inserted into slots (9) in the cabin slot structure; The pre-tightening structure comprises an upper outer block (7) and two top screws (8); the upper inner block (3) is provided with two internal threaded holes (3.1); the top screws (8) are arranged in the internal threaded holes (3.1) and the ends of the top screws (8) are in contact with the upper outer block (7) to press the upper outer block (7) against the inner wall of the cabin groove structure; The upper outer block (7) is a U-shaped structure, two sliders (7.1) are provided on the inner side of the upper outer block (7), and a slide groove (3.4) is provided on both side edges of the upper inner block (3), and the sliders (7.1) are slidably provided in the slide grooves (3.4); The upper surface of the upper inner block (3) is provided with a plurality of grooves (3.2), the upper fairing (1) is provided with a plurality of bosses (1.1), and the bosses (1.1) are embedded in the grooves (3.2).

2. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 1, characterized in that: The hinge (3.3) is a wedge-shaped structure.

3. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 2, characterized in that: The head of the hinge (3.3) exceeds the lower surface of the upper inner block (3).

4. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 1, characterized in that: The cabin groove structure comprises a shallow cabin groove (2.1), a deep cabin groove (2.2) and an upper pressing block (4); the shallow cabin groove (2.1) and the deep cabin groove (2.2) are connected; the hinge structure and the pre-tightening structure are arranged in the shallow cabin groove (2.1); and the upper pressing block (4) is arranged in the deep cabin groove (2.2); two slots (9) are arranged on the upper pressing block (4); and the cross-section of the slots (9) is triangular.

5. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 4, characterized in that: The upper pressing block (4) is provided with three through holes, and the through holes are waist-shaped holes.

6. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 1, characterized in that: The stepped structure (2.3) is provided with a chamfered structure.

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