Shear screw type fairing separating mechanism, assembling method and separating method

Abstract

The invention provides a shear screw type fairing separating mechanism, an assembling method and a separating method.The shear screw type fairing separating mechanism comprises at least two cover bodies, and the cover bodies are spliced in the radial direction and provided with connecting and separating structures which are fixedly connected with each other; the connecting and separating structures are arranged at intervals along the splicing positions between the cover bodies, and the connecting and separating structures form weakening positions and are fractured in the splicing direction between the cover bodies. Hinges connected to the aircraft are arranged at the rear ends of the cover bodies respectively, guide grooves with openings facing the outer side are formed in the aircraft, and the hinges are rotatably and slidably connected into the guide grooves; an ignition actuating cylinder for driving the connecting and separating structure to break is arranged between the cover bodies in the splicing direction, the opposite cover bodies rotate reversely along the hinges, and the hinges slide along the guide grooves respectively and are separated from the aircraft. The structure has good manufacturability and easy assembly, and the whole structure has the effects of good strength and rigidity while the requirements of small-size space application and structure light weight are met.

Description

Technical Field

[0001] The present invention belongs to the technical field of fairing separation mechanisms, and in particular relates to a shear screw type fairing separation mechanism, an assembly method, and a separation method. Background Art

[0002] The fairing is a device used to protect the payload from harmful environmental influences such as aerodynamic force, aerodynamic heat, and acoustic vibration during the launch of the aircraft. It is located on the top of the aircraft. However, after the aircraft enters the predetermined orbit, the fairing has completed its function of maintaining the aerodynamic shape of the aircraft and protecting the payload, and it needs to be unlocked and separated in time to reduce weight and provide a suitable working space for the payload.

[0003] For high-speed aircraft, the fairing separation process is crucial, requiring careful consideration of separation speed, precision, and impact on flight stability. Existing fairings suffer from complex separation mechanisms, high weight, low separation efficiency, and the generation of harmful waste, failing to meet the urgent need for lightweight and miniaturized designs for split-flap fairings.

[0004] Patent document CN111661313B discloses a quick-release mechanism for an aircraft fairing and an aircraft. The quick-release mechanism includes: a first fixing member for fixing the lower hood; a second fixing member for fixing the upper hood; at least one unlocking assembly including a connector, a first socket, and a second socket, the first socket being connected to the first fixing member, the second socket being connected to the second fixing member, the connector being movably inserted into the first socket and the second socket; and at least one driving mechanism being transmission-connected to the corresponding connector to drive the connector to insert or disengage between the first socket and the second socket to form a quick-release mechanism and a quick-connect system. The driving mechanism drives the connector to insert or disengage between the first socket and the second socket, thereby achieving assembly or separation between the lower hood and the upper hood.

[0005] However, the driving link of the quick separation mechanism of patent document CN111661313B is complex and lacks reliability.

[0006] To this end, a fairing separation mechanism is needed that achieves rapid, reliable, low-impulse separation under harsh aerodynamic and thermal conditions and high dynamic pressure without generating harmful waste, while also addressing the extreme demands for easy assembly of fairing components and lightweight structure. To this end, the present invention designs a shear screw-type fairing separation mechanism that addresses these existing issues. Summary of the Invention

[0007] In view of the defects in the prior art, the purpose of the present invention is to provide a shear screw type fairing separation mechanism, an assembly method, and a separation method.

[0008] According to the present invention, a shear screw type fairing separation mechanism is provided, which includes at least two cover bodies, which are radially spliced ​​between the cover bodies and are fixedly connected to each other with a connecting and separating structure; the connecting and separating structures are arranged at intervals along the splicing between the cover bodies, and the connecting and separating structures form a weakened part and break along the splicing direction between the cover bodies; the rear ends of the cover bodies are respectively provided with hinges connected to the aircraft, the aircraft is provided with a guide groove opening toward the outside, and the hinge can be rotatably and slidably connected in the guide groove; a fire-actuated cylinder for driving the connecting and separating structure to break is provided between the cover bodies along the splicing direction, the relative cover bodies rotate in opposite directions along the hinges, and the hinges slide along the guide grooves and separate from the aircraft.

[0009] By adopting the above technical solution, the fairing is easy to assemble and has a lightweight structure, and it meets the requirements of good strength and rigidity while meeting the requirements of small-size space applications.

[0010] Preferably, the connection and separation structure includes an outer locking block, an inner locking block and a shear screw, the outer locking block is fixedly connected to one side of the cover; the inner locking block is passed through the outer locking block and fixed to the cover on the opposite side of the outer locking block; the shear screw is threaded and fixed to the outer locking block and the inner locking block, and the shear screw is provided with a weakened part corresponding to the connection between the inner locking block and the outer locking block, and the shear screw breaks along the weakened part.

[0011] By adopting the above technical solution, the fire working cylinder pushes the fairing to be separated along the weakened surface during separation. At the same time, the screws at both ends of the shear are separated together with the outer locking blocks and inner locking blocks in the fairing on both sides, without generating harmful excess materials and ensuring the normal operation of the payload.

[0012] Preferably, the threads at both ends of the shear screw are arranged in opposite directions along the weakened portion, and the opposite threads at both ends can be screwed to the outer locking block and the inner locking block at the same time.

[0013] By adopting the above technical solution, the threads at both ends of the shear screw are left-handed and right-handed respectively, so the simultaneous assembly of external locking and internal locking can be achieved.

[0014] Preferably, the end of the shear screw is provided with a groove for a screwdriver to pass through. The screwdriver can pass through the outer locking block or the inner locking block, be inserted into the groove and drive the shear screw to rotate.

[0015] Preferably, the fire operating cylinder has a hard outer shell, and both ends are respectively arranged at the outer wall of the cover, and the two ends of the fire operating cylinder are respectively screwed and fixed to the corresponding cover.

[0016] Preferably, the fire operating cylinder is arranged at the front end of the cover body.

[0017] According to the present invention, a method for assembling a shear screw type fairing separation mechanism comprises the following steps:

[0018] Step S1: Assemble the outer locking block, the inner locking block and the shear screw to form a connection and separation structure.

[0019] Step S2: Screw the fire operating cylinder and several connecting and separating structures onto one side of the cover.

[0020] Step S3: Splice the cover body on the other side to form a joint cover, and screw the ignition actuator and several connecting and separating structures to fix them.

[0021] Step S4: Screw the hinge onto the corresponding cover to engage with the guide groove on the aircraft, so that the cover is stably connected to the aircraft.

[0022] Preferably, in step S1:

[0023] The shear screws are set in opposite directions along the threads at both ends of the weakened part. The shear screws are placed between the outer locking block and the inner locking block. The groove at either end of the shear screws is rotated. The outer locking block and the inner locking block are tightened toward the center surface at the same time until they are locked, and assembled into a connection and separation structure.

[0024] A method for separating the shear screw type fairing separation mechanism, comprising the steps of:

[0025] The fire working cylinder receives the working signal, cuts off the main body and pushes the two side covers to separate to the preset length. While the covers are separated, the shear screws on both sides are cut off, and the fairing is quickly and symmetrically rotated and separated around the hinge distribution mating surface. After the two side covers are separated, the hinge moves along the guide groove, causing the fairing to rotate and separate around the root of the hinge.

[0026] An aircraft provided by the present invention adopts the shear screw type fairing separation mechanism.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] The split-flap fairing has good manufacturability and easy assembly. While meeting the requirements of small-size space applications and lightweight structure, the overall structure has good strength and rigidity. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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:

[0030] Figure 1 It is a main sectional view of the shear screw type fairing separation mechanism of the present invention.

[0031] Figure 2 It is a schematic diagram of the assembly of the connecting and separating structure (including the outer locking block, the inner locking block and the shear screw) of the present invention.

[0032] Figure 3 This is a schematic diagram of the assembly of the cover body on the front side of the cover of the present invention.

[0033] Figure 4 It is a schematic diagram of the fire working cylinder connecting the cover bodies on both sides of the present invention.

[0034] Figure 5 It is a schematic diagram of the assembly of the present invention after the cover is closed.

[0035] The figure shows:

[0036] DETAILED DESCRIPTION

[0037] 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.

[0038] like Figure 1 As shown, a shear screw type fairing separation mechanism includes at least two cover bodies 1. In this embodiment, the cover bodies 1 are two symmetrically arranged cover bodies 1. The petal structure can maximize the use of the internal space, which is beneficial to the assembly and lightweight of the fairing, as well as the requirement of symmetrical separation. The cover bodies 1 are spliced ​​radially and are fixedly connected to each other with a connecting separation structure 3.

[0039] like Figure 1 As shown, the connection and separation structures 3 are arranged at intervals along the joints between the cover bodies 1. The present invention uses 6 groups (3 groups on each side) of longitudinal locks to connect the cover bodies 1 on both sides into a whole, thereby achieving the cover fixing of the cover body 1.

[0040] like Figure 1 、 2 As shown, the connection and separation structure 3 includes an outer locking block 6, an inner locking block 7 and a shear screw 8. The outer locking block 6 is screwed and fixed to one side of the cover body 1; the inner locking block 7 is passed through the outer locking block 6 and is screwed and fixed to the cover body 1 on the opposite side of the outer locking block 6; the shear screw 8 is screwed and fixed to the outer locking block 6 and the inner locking block 7, and the shear screw 8 is provided with a weakened part corresponding to the connection between the inner locking block 7 and the outer locking block 6. The shear screw 8 can be broken along the weakened part under axial tension, and the cut screws at both ends are separated together with the outer locking block 6 and the inner locking block 7 of the cover body 1 on both sides, without generating harmful redundant materials, thereby ensuring the normal operation of the payload.

[0041] like Figure 2 、 3As shown, the shear screw 8 has opposite threads at both ends along the weakened portion, and the opposite threads at both ends can be simultaneously screwed to the outer locking block 6 and the inner locking block 7. The threads of the outer locking block 6 are left-handed, while the threads of the inner locking block 7 are right-handed. The threads at both ends of the shear screw 8 are left-handed and right-handed, respectively, allowing for simultaneous assembly of both external and internal locking. In one variation, the threads of the outer locking block 6 are right-handed, while the threads of the inner locking block 7 are left-handed.

[0042] Preferably, the end of the shear screw 8 is provided with a groove for the screwdriver to pass through. The screwdriver can be passed through the outer locking block 6 or the inner locking block 7, inserted into the groove and drive the shear screw 8 to rotate. By rotating the shear screw 8 at either end, the outer locking block 6 and the inner locking block 7 are tightened toward the center surface at the same time until they are locked.

[0043] like Figure 3 、 4 As shown, a fire-operated cylinder 4 for driving the connection separation structure 3 to break is provided between the cover bodies 1 along the splicing direction. The fire-operated cylinder 4 can be arranged at the front end of the cover body 1 so that the space inside the cover body 1 is adjacent to the aircraft, thereby increasing space utilization. When the fire-operated cylinder 4 is actuated, the main body will be cut off and pushed to a preset length. The fire-operated cylinder 4 will push the cover bodies 1 on both sides to separate while cutting off the shear screws 8 on both sides, so that the cover bodies 1 on both sides can be separated smoothly. The thrust of the fire-operated cylinder 4 and the shear force of the shear screws 8 can be optimized according to the actual aerodynamic load to achieve the extreme demand for fast and reliable separation with low impulse under harsh aerodynamic thermal environment and high dynamic pressure conditions.

[0044] like Figure 3 、 4 As shown, preferably, the fire operating cylinder 4 has a hard outer shell, and the two ends are respectively arranged at the outer walls of the cover body 1. The two ends of the fire operating cylinder 4 are respectively screwed and fixed to the corresponding cover body 1, which can enhance the connection strength and rigidity between the cover bodies 1 before the fire is operated.

[0045] like Figure 3 、 5 As shown, in order to make the separation trajectory of the cover body 1 more stable and controllable, the rear end of the cover body 1 is respectively provided with a hinge 5 connected to the aircraft, and the aircraft is provided with a guide groove opening toward the outside, and the hinge 5 can be rotatably and slidably connected to the guide groove; before the cover bodies 1 on both sides are separated, the hinges 5 installed on both sides of the cover body 1 are engaged with the guide grooves on both sides of the aircraft to realize a non-fastened connection between the fairing and the rear end structure; after the cover body 1 is unlocked, the relative cover body 1 rotates in the opposite direction along the hinge 5, the single-sided hinge 5 loses its inward limit, and moves along the outside of the guide groove, thereby realizing the rotational separation of the fairing around the root of the hinge 5.

[0046] This embodiment can achieve the coupling adjustment of the longitudinal separation resistance and the longitudinal locking force by optimizing the shear surface diameter of the shear screw 8, and optimize the design of shear screws 8 of different diameters for separation conditions of different sizes and different conditions to achieve the best fairing separation solution.

[0047] This embodiment also provides an assembly method for a shear screw type fairing separation mechanism, which is used to assemble the above-mentioned shear screw type fairing separation mechanism, and the steps include: S1: assembling the outer locking block 6, the inner locking block 7 and the shear screw 8 to form a connection and separation structure 3.

[0048] Preferably, the shear screw 8 is set in reverse along the threads at both ends of the weakened part, and the shear screw 8 is placed between the outer locking block 6 and the inner locking block 7. The groove at either end of the shear screw 8 is rotated, and the outer locking block 6 and the inner locking block 7 are tightened toward the center surface at the same time until they are locked, and assembled into a connection and separation structure 3.

[0049] S2: Screw the fire operating cylinder 4 and several connecting and separating structures 3 onto one side of the cover 1.

[0050] S3: Splice the cover body 1 on the other side to form a joint cover, and screw the fire operating cylinder 4 and several connecting and separating structures 3 to fix them.

[0051] S4: The hinge 5 is screwed and installed on the corresponding cover 1 to form an engagement with the guide groove on the aircraft, so that the cover 1 is stably connected to the aircraft.

[0052] This embodiment also provides a separation method of a shear screw type fairing separation mechanism, which is used to separate the fairing from the aircraft, and the steps include: the fire working cylinder 4 receives a working signal, cuts off the main body and pushes the two side cover bodies 1 to separate to a preset length, and while the cover body 1 is separated, the shear screws 8 on both sides are cut off, and the fairing is allowed to rotate and separate quickly and symmetrically around the distribution matching surfaces of the hinge 5. After the two side cover bodies 1 are separated, the hinge 5 moves along the guide groove, so that the fairing is separated by rotation around the root of the hinge 5.

[0053] 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.

[0054] 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 shear screw type fairing separation mechanism, characterized in that: include: At least two covers (1) are provided, the covers (1) are spliced ​​radially and provided with connecting and separating structures (3) to be fixedly connected to each other; the connecting and separating structures (3) are arranged at intervals along the splicing portion between the covers (1), and the connecting and separating structures (3) form a weakened portion and break along the splicing direction between the covers (1); the rear ends of the covers (1) are respectively provided with hinges (5) connected to the aircraft, the aircraft is provided with a guide groove opening toward the outside, and the hinges (5) are rotatable and slidably connected in the guide groove; a fire-operated cylinder (4) for driving the connecting and separating structures (3) to break is provided between the covers (1) along the splicing direction, the opposite covers (1) rotate in opposite directions along the hinges (5), and the hinges (5) respectively slide along the guide grooves and separate from the aircraft.

2. The shear screw type fairing separation mechanism according to claim 1, characterized in that: The connection and separation structure (3) comprises an outer locking block (6), an inner locking block (7) and a shear screw (8); the outer locking block (6) is fixedly connected to one side of the cover body (1); the inner locking block (7) is passed through the outer locking block (6) and fixed to the cover body (1) on the side opposite to the outer locking block (6); the shear screw (8) is screwed and fixed to the outer locking block (6) and the inner locking block (7); and the shear screw (8) is provided with a weakened portion corresponding to the connection between the inner locking block (7) and the outer locking block (6), and the shear screw (8) breaks along the weakened portion.

3. The shear screw type fairing separation mechanism according to claim 2, characterized in that: The shear screw (8) is provided with threads at both ends of the weakened portion in opposite directions, and the threads at both ends can be screwed to the outer locking block (6) and the inner locking block (7) at the same time.

4. The shear screw type fairing separation mechanism according to claim 3, characterized in that: The end of the shear screw (8) is provided with a groove for a screwdriver to pass through. The screwdriver can pass through the outer locking block (6) or the inner locking block (7), be inserted into the groove and drive the shear screw (8) to rotate.

5. The shear screw type fairing separation mechanism according to claim 1, characterized in that: The fire operating cylinder (4) has a hard outer shell, and its two ends are respectively arranged at the outer wall of the cover body (1). The two ends of the fire operating cylinder (4) are respectively screwed and fixed at the corresponding cover body (1).

6. The shear screw type fairing separation mechanism according to claim 1, characterized in that: The fire-operated cylinder (4) is arranged at the front end of the cover body (1).

7. A method for assembling a shear screw type fairing separation mechanism according to any one of claims 1 to 6, characterized in that the steps include: Step S1: Assembling the outer locking block (6), the inner locking block (7) and the shear screw (8) to form a connection and separation structure (3); Step S2: screwing the fire-operated cylinder (4) and the plurality of connecting and separating structures (3) onto one side of the cover (1); Step S3: Splice the cover body (1) on the other side to form a joint cover, and screw the fire-actuating cylinder (4) and the plurality of connecting and separating structures (3) together; Step S4: The hinge (5) is screwed and installed on the corresponding cover (1) to form an engagement with the guide groove on the aircraft, so that the cover (1) is stably connected to the aircraft.

8. The method for assembling the shear screw type fairing separation mechanism according to claim 7, characterized in that: In step S1: The shear screw (8) is set along the threads at both ends of the weakened part in opposite directions, and the shear screw (8) is placed between the outer locking block (6) and the inner locking block (7). The groove at either end of the shear screw (8) is rotated, and the outer locking block (6) and the inner locking block (7) are tightened toward the center surface at the same time until they are locked, and the connection and separation structure (3) is assembled.

9. A method for separating a shear screw type fairing separation mechanism according to any one of claims 1 to 6, characterized in that the steps include: The fire working cylinder (4) receives the working signal, cuts off the main body and pushes the two side covers (1) to separate to a preset length. When the covers (1) are separated, the shear screws (8) on both sides are cut off, and the fairing is symmetrically rotated and separated around the distribution matching surface of the hinge (5). After the two side covers (1) are separated, the hinge (5) moves along the guide groove, so that the fairing is rotated and separated around the root of the hinge (5).

10. An aircraft, characterized in that: A shear screw type fairing separation mechanism is adopted as described in any one of claims 1 to 6.

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