Built-in fairing pre-tightening and rotating separation hinge mechanism

Abstract

The invention discloses a built-in fairing pre-tightening and rotary separation hinge mechanism, relates to the technical field of carrier rockets, and solves the problems that a fairing separation mode is complex in structure, an exposed separation mechanism affects the aerodynamic configuration of an aircraft, and an axial pre-tightening function does not exist. An upper fairing is movably connected with a cabin body; a hinge structure is arranged on the upper fairing, and a cabin body groove structure is arranged on the cabin body; one end of the hinge structure is inserted into an insertion groove in the cabin groove structure, the other end of the hinge structure is provided with a pre-tightening structure, the pre-tightening structure abuts against the inner wall of the cabin groove structure, and the hinge structure, the pre-tightening structure and the cabin groove are matched to achieve circumferential positioning and axial pre-tightening of the upper fairing; the cabin body is provided with a step structure, and the upper fairing is buckled on the step structure. According to the device, the circumferential positioning and axial pre-tightening functions of the fairing can be achieved, the hinge is used as a turnover fulcrum to ensure that the turnover track is controllable, and the situation of collision or dead locking is avoided; and meanwhile, the influence of the separation mechanism on the aerodynamic configuration of the aircraft is reduced.

Description

Technical Field

[0001] The 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 prevent the satellite from being affected by harmful environments such as aerodynamic forces, aerodynamic heating, and acoustic vibration. It is an important part of the launch vehicle. When the rocket flies to a certain altitude, the fairing must be separated and discarded in time to allow the payload to work normally and reduce the subsequent mass of the aircraft, so that the aircraft can play its role effectively. At present, the rocket fairing separation methods at home and abroad include overall fairing separation, two-petal rotation separation, two-petal horizontal push separation, multi-petal rotation separation, and multi-petal horizontal push separation. However, the existing fairing separation methods have the problems of complex structure, no axial pre-tightening function, and exposed separation mechanism affecting the aerodynamic shape of the aircraft. Summary of the invention

[0003] In order to solve the problems mentioned above in the existing fairing separation method, such as complex structure, external separation mechanism affecting the aerodynamic shape of the aircraft, and no axial pre-tightening function, the present invention proposes a built-in fairing pre-tightening and rotating separation hinge mechanism. The present invention can realize the circumferential positioning and axial pre-tightening functions of the fairing on the cabin, and use the hinge as the flipping fulcrum to ensure that the flipping trajectory is controllable to avoid collision or locking; at the same time, the built-in fairing pre-tightening and rotating separation hinge mechanism is simple and reliable, reducing the impact of the separation mechanism on the aerodynamic shape of the aircraft.

[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 body, wherein the upper fairing and the cabin body are movably connected; a hinge structure is provided on the upper fairing, and a cabin body slot structure is provided on the cabin body, and the hinge structure and the cabin body slot structure are movably connected; one end of the hinge structure is inserted into a slot in the cabin body 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 body slot structure; a step structure is provided on the cabin body, and the upper fairing is buckled on the step structure.

[0005] Furthermore, the hinge structure includes an upper inner block and a plurality of upper fairing screws, and the upper fairing is connected to the upper inner block via the plurality of 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 sliding blocks are arranged on the inner side of the upper outer block, and a sliding groove is arranged on the two side edges of the upper inner block respectively, and the sliding blocks are slidably arranged in the sliding grooves.

[0010] Furthermore, the upper surface of the upper inner block is provided with a plurality of grooves, and the upper fairing is provided with a plurality of bosses, which 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 internal fairing pre-tightening and rotation separation hinge mechanism of the present invention overcomes the problems of the existing fairing separation method, such as complex structure, no axial pre-tightening function, and exposed separation mechanism affecting the aerodynamic shape of the aircraft. The hinge connection structure is an insertion 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 the upper fairing and the aircraft from colliding or locking.

[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 picture:

[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, which 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, which 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 an 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 an upper inner block of a built-in fairing pre-tightening and rotation separation hinge mechanism according to the present invention;

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

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

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

[0029] Fig.11 It is a top view of an upper pressing block of a built-in fairing pre-tightening and rotation separation hinge mechanism 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 technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part 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 creative work are 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", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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 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.

[0033] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" 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 it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to 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 Figure 1-Figure 11The embodiment is described in detail. The built-in fairing pre-tightening and rotation separation hinge mechanism described in the embodiment 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 cover 1 is connected to the hinge structure, and the hinge structure contacts the wall surface of the tank body groove through the pre-tightening structure to realize the circumferential positioning function of the upper fairing 1; the tank body 2 is provided with a step structure 2.3, and the upper fairing 1 is provided with a protruding structure, and the protruding structure of the upper fairing 1 is buckled on the step structure 2.3. Under the action of the pre-tightening structure, the upper fairing 1 moves in the opposite direction of the moving direction of the pre-tightening structure, so that the protruding structure is close to the step structure 2.3, and the pre-tightening function of the upper fairing 1 is realized. The step structure 2.3 is provided with a chamfer structure to prevent the upper fairing 1 from interfering with the step structure 2.3 when turning 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 arranged at one end of the upper inner block 3, and a pre-tightening structure is arranged at the other end. The hinge 3.3 is inserted into a slot 9 in the tank body slot structure. The hinge 3.3 is a wedge-shaped structure. 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 from the lower surface of the main part of the upper inner block 3 by a certain distance, such as Figure 6 shown.

[0037] The pre-tightening structure includes 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 thereof are in contact with the upper outer block 7. The upper outer block 7 is pressed against the inner wall of the cabin groove structure by rotating the top screws 8.

[0038] The upper outer block 7 is a U-shaped structure, including a top block and two slide bars, the two slide bars are symmetrically arranged at the two ends of the top block, and two sliders 7.1 are arranged on the opposite inner sides of the two slide bars. The cross section of the slider 7.1 is trapezoidal; the top width of the slider 7.1 is smaller than the bottom width. 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 a trapezoidal, such as Figure 6 As shown; the slider 7.1 is slidably disposed in the slide groove 3.4, and under the cooperation of the top screw 8 and the internal threaded hole 3.1, the upper outer block 7 is pushed to slide along the slide groove 3.4 and abut 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 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 a role in sharing the shear force of the upper fairing screws 6.

[0040] 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 is connected to the deep cabin groove 2.2. The depth of the deep cabin groove 2.2 is greater than that 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 pressing block 4 is arranged in the deep cabin groove 2.2. Two slots 9 are arranged on the upper pressing block 4. The cross section of the slots 9 is triangular. Fig. 9 and Fig.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 in the shape of waist-shaped holes. 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 screw 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, the raised structure on the inner side of the upper fairing 1 rests on the stepped structure 2.3 of the cabin 2, and the upper inner block 3 and the upper outer block 7 are installed in the shallow cabin groove 2.1; screw The top screw 8 is turned to push the upper outer block 7 forward and 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; the upper pressure block 4 is installed in the deep cabin groove 2.2 and fastened by the pressure block screw 5, and the slot 9 set on the upper pressure block 4 is buckled above the hinge 3.3.

[0044] When receiving the separation command, the actuator cylinder at the front of the upper fairing 1 works, pushing the upper fairing 1 to flip with the hinge 3.3 as the rotation fulcrum, and driving the upper inner block 3 and the upper outer block 7 to flip out from the shallow cabin groove 2.1. After the separation is completed, the upper pressure block 4 will remain in the deep cabin groove 2.2, and the rest of the structure will be flipped and discarded. The rotating separation hinge mechanism can ensure that the movement trajectory of the fairing during separation is controllable without collision / locking.

[0045] Summarizing the above implementation cases, the built-in fairing pre-tightening and rotation separation hinge mechanism described in the present invention overcomes the problems of the existing fairing separation method, such as complex structure, no axial pre-tightening function, and the exposed separation mechanism affecting the aerodynamic shape of the aircraft. The hinge connection structure is an inserted design, and the hinge 3.3 is wedge-shaped. The upper fairing 1 is flipped with the hinge 3.3 as the flip fulcrum, and separated according to a predetermined motion trajectory, so as to avoid the upper fairing 1 and the aircraft from colliding or locking. The built-in fairing pre-tightening and rotation separation hinge mechanism described in the present invention, the upper fairing 1 is buckled at the step structure 2.3 of the cabin 2, the upper outer block 7 and the upper inner block 3 are slidably matched, and the upper outer block 7 is pushed against the inner wall of the cabin groove under the action of the top screw 8, so as to apply a pre-tightening force to the upper fairing 1 to realize 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, so as to realize the circumferential positioning function of the upper fairing 1.

[0046] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the invention. It can also be a reasonable combination of the features recorded in the above implementation methods. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A built-in fairing pre-tightening and rotation separation hinge mechanism, characterized in that: 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); 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).

2. The built-in fairing pre-tightening and rotation separation hinge mechanism according to claim 1 is characterized in that: The hinge structure comprises an upper inner block (3) and a plurality of upper fairing screws (6), and 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 hinge (3.3) is inserted into a slot (9) in the cabin slot structure.

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

4. The internal fairing pre-tightening and rotation separation hinge mechanism according to claim 3 is characterized in that: The head of the hinge (3.3) protrudes beyond the lower surface of the upper inner block (3).

5. The internal fairing pre-tightening and rotation separation hinge mechanism according to claim 2 is characterized in that: 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) so that the upper outer block (7) is pressed against the inner wall of the cabin body groove structure.

6. The internal fairing pre-tightening and rotation separation hinge mechanism according to claim 5, characterized in that: The upper outer block (7) is a U-shaped structure. Two sliding blocks (7.1) are arranged on the inner side of the upper outer block (7). A sliding groove (3.4) is arranged on the two side edges of the upper inner block (3). The sliding blocks (7.1) are slidably arranged in the sliding grooves (3.4).

7. The internal fairing pre-tightening and rotation separation hinge mechanism according to claim 2 is characterized in that: 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).

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

9. The internal fairing pre-tightening and rotation separation hinge mechanism according to claim 8, characterized in that: The upper pressing block (4) is provided with three through holes, and the through holes are waist-shaped holes.

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

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