Missile wing folding and unfolding device and folding and unfolding method

Abstract

The invention provides a missile wing retracting and releasing device and method, the missile wing retracting and releasing device comprises a fixing ring suitable for being detachably mounted on a missile body, a plurality of restraining mechanisms are arranged on the fixing ring at intervals in the circumferential direction of the fixing ring, and each restraining mechanism is used for independently limiting and restraining the free end of each missile wing in a retracting state. The restraint mechanism is designed to independently restrain the single folded missile wing, it is guaranteed that the risk of automatic springback is avoided after the missile wings are folded, the single missile wing can be selectively and independently released, the risk that all the missile wings bounce off at the same time is avoided, and the function of folding or unfolding the wings one by one is achieved; and the adaptability to missile wing folding and unfolding in the missile production and manufacturing process is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of missile production and manufacturing, and particularly relates to a missile wing retracting and extending device and a retracting and extending method. Background Art

[0002] At present, in the fields of process equipment, precision machinery, automated machinery, missile manufacturing, aircraft manufacturing, non-standard machinery, etc., especially in the missile manufacturing process, when multiple wing panels need to be folded, retracted, bundled and installed simultaneously or one by one, they are often completed by manual operation or by automated means, such as computer vision, manipulators, and automated devices. However, manual operation often requires the cooperation of multiple people and consumes a lot of manpower, while the cost of automated means is relatively high. Summary of the invention

[0003] The purpose of the present invention is to provide a wing retracting and deploying device which can at least solve some of the defects existing in the prior art.

[0004] To achieve the above object, the present invention adopts the following technical solution:

[0005] A missile wing retracting and releasing device comprises a fixing ring suitable for being detachably mounted on a missile body, wherein the fixing ring is provided with a plurality of restraining mechanisms at intervals along its circumference, and each of the restraining mechanisms is used to independently limit and restrain the free end of each missile wing in a retracted state.

[0006] Furthermore, the above-mentioned wing retracting and extending device also includes a binding belt for binding the wings of each of the constraint mechanisms in the retracted state.

[0007] Furthermore, the restraining mechanism includes a baffle for restraining the bomb wing and a driving assembly, the driving assembly is fixedly mounted on the fixing ring, the baffle is connected to the driving assembly, and the driving assembly drives the baffle to move so that the baffle has a restraining position capable of limiting the corresponding bomb wing in the folded state and an avoidance position away from the corresponding bomb wing in the folded state.

[0008] Furthermore, the blocking piece includes a pressing portion and limiting portions arranged at two ends of the pressing portion, and the limiting portions are inclined structures that expand outward from the pressing portion toward the inner side of the fixing ring.

[0009] Furthermore, the driving assembly includes a pin shaft, a spring, a locking pin and a power member, the pin shaft passes through the two axial end surfaces of the fixing ring, the baffle and the power member are respectively connected to the two ends of the pin shaft, the spring is sleeved on one end of the pin shaft close to the baffle, and the end of the pin shaft close to the power member is provided with a plurality of pin holes for inserting the locking pin.

[0010] Further, a spring installation groove for installing the spring and a pin guide hole for guiding the movement of the pin are provided inside the fixed ring; a step surface for abutting against the spring is provided on the pin.

[0011] Further, the fixed ring includes an upper ring and a lower ring. A storage through groove for accommodating the elastic body is formed between the inner sides of the upper ring and the lower ring. One end of the upper ring and the lower ring is rotatably connected, and the other end of the upper ring and the lower ring is detachably connected through a locking member.

[0012] Further, limiting bosses are provided at both ends of the upper ring and the lower ring, and the locking member is installed on the limiting bosses.

[0013] In addition, the present invention also provides a method for retracting and deploying the fin. Using the above-mentioned fin retracting and deploying device, it includes the following processes:

[0014] When retracting the fin, install the fixed ring at the set position of the elastic body, then fold the fin onto the elastic body, and at the same time, the constraint mechanism corresponding to the position of the fin on the fixed ring limits the free end of the fin. Repeat this process to sequentially complete all the fins that need to be retracted one by one;

[0015] When deploying the fin, release the limit constraint of the constraint mechanism on the fin of the specified fin one by one. The fin automatically pops open under the action of its own structure to complete the release of some specified fins or all fins.

[0016] Further, the above-mentioned fin retracting and deploying method further includes the following process:

[0017] When retracting the fin, after sequentially completing the limit constraint of the constraint mechanism on all the fins that need to be retracted, use a bundling band to tie up all the fins with the limit constraint completed, and then separate the fixed ring from the elastic body;

[0018] When deploying the fin, first install the fixed ring at the corresponding position of the elastic body and make the constraint mechanism limit and constrain each fin, then loosen the bundling band, and then release the limit constraint of the constraint mechanism on the fin of the specified fin one by one to complete the release of some specified fins or all fins.

[0019] Compared with the prior art, the beneficial effects of the present invention:

[0020] (1) The fin retracting and deploying device provided by the present invention independently constrains a single retracted fin through the design of the constraint mechanism, ensuring that the fin avoids the risk of automatic rebound after being retracted, and can selectively release a single fin independently, avoiding the risk of all fins popping open at the same time, realizing the function of retracting or releasing each fin one by one, and improving the adaptability of the fin retracting and deploying during the missile manufacturing process.

[0021] (2) In the wing retraction and extension device provided by the present invention, the restraint mechanism adopts a spring telescopic structure design, enabling the restraint mechanism to pop out and retract. In the two states of popping out and retracting, it can respectively achieve the restraint and release of the wing, with a simple structure and convenient operation.

[0022] The following will further elaborate on the present invention in conjunction with the accompanying drawings. Description of the Drawings

[0023] Figure 1 is an assembly schematic diagram of the wing retraction and extension device of the present invention and the projectile body;

[0024] Figure 2 is a schematic diagram of the open state of the wing retraction and extension device in an embodiment of the present invention;

[0025] Figure 3 is a schematic diagram of the closed-loop state of the wing retraction and extension device in an embodiment of the present invention;

[0026] Figure 4 is a cross-sectional view of the wing retraction and extension device in an embodiment of the present invention.

[0027] Description of the reference numerals: 1, fixed ring; 2, restraint mechanism; 3, binding band; 4, wing; 5, projectile body; 6, upper ring; 7, lower ring; 8, limit boss; 9, handle; 10, retaining piece; 11, locking member; 12, pin hole; 13, pin shaft; 14, pin shaft guide hole; 15, spring installation groove; 16, spring; 17, step surface. Detailed Embodiment

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0029] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is 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 should not be construed as a limitation to the present invention.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or a contact connection or an integral connection. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meanings of "a plurality" and "several" are two or more.

[0032] As Figures 1 to 4 shown, this embodiment provides a wing retraction device, which includes a fixing ring 1 adapted to be detachably installed on a missile body 5. A plurality of restraint mechanisms 2 are arranged at intervals along the circumference of the fixing ring 1. Each of the restraint mechanisms 2 is used to independently limit and restrain the free ends of the wings 4 in the retracted state respectively. Specifically, the number of the restraint mechanisms 2 is not less than the number of the wings 4 on the missile body 5. At the same time, for the design of the interval distance between the restraint mechanisms 2, it is necessary to ensure that when the fixing ring 1 is installed on the missile body 5, each of the wings 4 in the retracted state on the missile body 5 has a corresponding restraint mechanism 2 for limiting.

[0033] When it is necessary to retract the wings 4 of the missile, first install the fixing ring 1 at the designated position on the missile body 5. The designated position is at the position where the free end of the wing 4 is folded to the missile body 5. Then fold one of the wings 4 to the missile body 5, and then open the restraint mechanism 2 corresponding to this wing 4 on the fixing ring 1, so that the restraint mechanism 2 limits and fixes the free end of the wing 4 on the missile body 5. After that, after folding the wings 4 that need to be retracted one by one to the missile body 5 according to the above operations, use the corresponding restraint mechanisms 2 to limit and fix the folded wings 4 one by one. When it is necessary to release the wings 4, just release the restraint of the restraint mechanism 2 on the wings 4, and the wings 4 can automatically bounce open under the action of their own structures, so as to realize the release of some designated wings 4 or all the wings 4. The wing retraction device provided by this embodiment independently restrains a single retracted wing 4 by designing the restraint mechanism 2, which ensures that the risk of automatic rebound of the wings 4 after retraction is avoided, and the single wing 4 can be selectively released independently, avoiding the risk of all the wings 4 bouncing open at the same time, realizing the function of retracting or releasing the wings 4 one by one, improving the adaptability of the wing retraction and release during the missile manufacturing process, and the retraction and release operations of the wings 4 can be completed independently by one person, reducing the labor cost.

[0034] Further optimize the above technical solution, as Figure 1As shown, the wing retracting and releasing device of this embodiment also includes a binding belt 3, which is used to bind the wings 4 constrained by each of the constraint mechanisms 2. After the constraint mechanism 2 has limited and fixed all the folded wings 4, the binding belt 3 is used to bind and fix the constrained wings 4 individually or in a whole circle. After that, the fixing of the wings 4 by the constraint mechanism 2 can be released, the fixing ring 1 can be removed from the projectile body 5, and the retracted wings 4 can be fixed to the projectile body 5 using the binding belt 3, so as to avoid the installation of the fixing ring 1 on the projectile body 5 affecting the production process of the projectile body. When it is necessary to loosen the wings 4 one by one, the fixing ring 1 can be installed on the projectile body 5, and the constraint mechanism 2 can be used to fix the corresponding wings 4, and then the binding belt 3 can be loosened, and the constraints of the wings 4 by the constraint mechanism 2 can be released one by one.

[0035] As a specific implementation method, Figure 2 and Figure 3 As shown, the restraint mechanism 2 includes a baffle 10 for restraining the elastic wing 4 and a driving assembly, the driving assembly is fixedly mounted on the fixing ring 1, the baffle 10 is connected to the driving assembly, and the driving assembly drives the baffle 10 to move so that the baffle 10 has a restraining position capable of limiting the corresponding elastic wing 4 in the folded state and an avoidance position away from the corresponding elastic wing 4 in the folded state. In some embodiments, a driving assembly can be designed to drive the baffle 10 to perform axial telescopic movement along the fixing ring 1; when the fixing ring 1 is installed on the projectile body 5, the fixing ring 1 is coaxially arranged with the projectile body 5, and the baffle 10 is located on the side of the fixing ring 1 close to the projectile wing 4; when the projectile wing 4 is folded, the driving assembly drives the baffle 10 to retract toward the end away from the projectile wing 4, so that the baffle 10 does not block the folding of the projectile wing 4. After folding the projectile wing 4 onto the projectile body 5, the driving assembly drives the baffle 10 to move in the direction of the projectile wing 4 to press the projectile wing 4, so that the free end of the projectile wing 4 is limited and fixed between the baffle 10 and the projectile body 5; when the projectile wing 4 is released, the driving assembly drives the baffle 10 to retract toward the end away from the projectile wing 4.

[0036] In some embodiments, Figure 2 and Figure 4As shown, the driving component includes a pin shaft 13, a spring 16, a locking pin and a power component. Among them, the power component can be, but is not limited to, a handle 9. The pin shaft 13 penetrates through both end faces of the fixing ring 1 in the width direction. The retaining plate 10 and the handle 9 are respectively connected to both ends of the pin shaft 13. The spring 16 is sleeved on one end of the pin shaft 9 close to the retaining plate 10. A plurality of pin holes 12 for inserting the locking pin are provided at one end of the pin shaft 9 close to the handle 9. When folding the wing 4, first fold the wing 4 to the middle position, pull up the handle 9, drive the retaining plate 10 to contract through the pin shaft 13, and at the same time the spring 16 is compressed. Then fold the wing 4 to the final position, release the handle 9, and the retaining plate 10 pops out under the elastic force of the spring 16 and presses on the wing 4, thereby completing the limiting constraint on the wing 4. Then use the locking pin to lock the pin shaft 12 to prevent the pin shaft 12 from moving along the axial direction of the projectile body 5. When releasing the wing 4, pull out the locking pin and pull up the handle 9 again to make the retaining plate 10 contract. In this embodiment, the constraint mechanism 2 is designed as a spring telescopic structure, so that the retaining plate 10 can pop out and retract. In its two states of popping out and retracting, the constraint and release of the wing 4 are respectively realized, and the structure is simple and the operation is convenient.

[0037] Preferably, a spring installation groove 15 and a pin shaft guiding hole 14 are provided in the fixing ring 1. The pin shaft 13 is arranged through the fixing ring 1 along the pin shaft guiding hole 14, and the pin shaft guiding hole 14 plays a guiding role in the movement of the pin shaft 13. The spring 16 is sleeved on the pin shaft 13, and the spring 16 is placed in the spring installation groove 15. A step surface 17 for abutting against the spring 16 is provided at one end of the pin shaft 13 close to the retaining plate 10. One end of the spring 16 contacts the fixing ring 1, and the other end contacts the step surface 17 of the pin shaft 13. When pulling up the handle 9, the step surface 17 of the pin shaft 13 will compress the spring 16 to obtain the acting force for popping out the retaining plate 10.

[0038] Preferably, the retaining plate 10 is designed to include a pressing part and limiting parts provided at both ends of the pressing part. The limiting parts are inclined structures that expand outward from the pressing part towards the inner side of the fixing ring 1. The pressing part and the limiting parts form a clamping groove. When constraining the wing 4, the pressing part of the retaining plate 10 presses on the surface of the wing 4, and the two limiting parts are respectively located on both sides of the wing 4, thereby clamping the wing 4 on the projectile body 5.

[0039] As a specific implementation manner, such as Figure 2 and Figure 3As shown, the fixed ring 1 includes an upper ring 6 and a lower ring 7. A storage through groove for accommodating the elastic body 5 is formed between the inner sides of the upper ring 6 and the lower ring 7. One end of the upper ring 6 and the lower ring 7 is rotatably connected, and the other end of the upper ring 6 and the lower ring 7 is detachably connected by a locking member 11. By designing the fixed ring 1 in the structural form of the upper ring 6 and the lower ring 7, the fixed ring 1 can be quickly installed on the elastic body 5 and can also be quickly separated from the elastic body 5. Among them, the locking member 11 can adopt, but is not limited to, structural forms such as buckles and snap fasteners.

[0040] Optimally, limiting bosses 8 are provided at the ends of both the upper ring 6 and the lower ring 7, and the locking member 11 is installed on the limiting bosses 8. Through the design of the limiting bosses 8, it is convenient for the accurate alignment when the upper ring 6 and the lower ring 7 are closed.

[0041] The operation process of retracting and deploying the wing using the wing retracting and deploying device of this embodiment is as follows:

[0042] When it is necessary to retract the wing 4, first install the fixed ring 1 at the designated position on the elastic body 5, fold the wing 4 to the middle position, lift the handle 9, the restraint mechanism 2 shrinks as a whole, gradually fold the wing 4 to the final position, release the handle 9, the retaining piece 10 pops out to block the wing 4. When all the wings 4 are folded in sequence, tie the bundled belt 3 around the wings 4, and then release the buckle (i.e., the locking member 11) on the fixed ring 1, and the fixed ring 1 can be separated from the elastic body 5, and the operation of retracting the wing 4 is completed; when it is necessary to deploy the wing 4, first install the fixed ring 1 at the corresponding position on the elastic body 5, release the bundled belt 3, and then gradually lift the handle to no longer restrain the wing 4. The wing 4 automatically pops open under the action of its own structure, and the designated wing 4 or all the wings 4 can be released. When the action of releasing the wing 4 is completed, finally release the buckle on the fixed ring 1, and the fixed ring 1 can be separated from the elastic body 5 again, and the operation of deploying the wing is completed.

[0043] The above examples are only illustrative of the present invention and do not constitute a limitation on the protection scope of the present invention. Any design identical or similar to the present invention falls within the protection scope of the present invention.

Claims

1. A wing retraction device, characterized in that: It comprises a fixing ring suitable for being detachably mounted on the projectile body, on which a plurality of restraining mechanisms are arranged at intervals along its circumference, and each of the restraining mechanisms is used to independently limit and restrain the free end of each projectile wing in the folded state.

2. The wing retraction device according to claim 1, wherein: It also includes a binding belt for binding the elastic wings of each of the restraint mechanisms in the folded state.

3. The wing retraction and extension device according to claim 1 or 2, characterized in that: The restraining mechanism includes a baffle for restraining the bomb wing and a driving assembly, the driving assembly is fixedly mounted on the fixing ring, the baffle is connected to the driving assembly, and the driving assembly drives the baffle to move so that the baffle has a restraining position capable of limiting the corresponding bomb wing in the folded state and an avoidance position away from the corresponding bomb wing in the folded state.

4. The wing retraction and extension device according to claim 3, characterized in that: The blocking piece includes a pressing portion and limiting portions arranged at two ends of the pressing portion, and the limiting portions are inclined structures that expand outward from the pressing portion toward the inner side of the fixing ring.

5. The wing retraction device according to claim 3, characterized in that: The driving assembly includes a pin shaft, a spring, a locking pin and a power member. The pin shaft passes through the two axial end surfaces of the fixing ring. The baffle and the power member are respectively connected to the two ends of the pin shaft. The spring is sleeved on one end of the pin shaft close to the baffle. The end of the pin shaft close to the power member is provided with a plurality of pin holes for inserting the locking pin.

6. The wing retraction device according to claim 5, characterized in that: The fixing ring is provided with a spring installation groove for installing the spring and a pin guide hole for guiding the movement of the pin; the pin has a step surface abutting against the spring.

7. The wing retraction device according to claim 1 or 2, characterized in that: The fixing ring comprises an upper ring and a lower ring, wherein a storage groove for accommodating the elastic body is formed between the inner sides of the upper ring and the lower ring, one end of the upper ring and the lower ring are rotatably connected, and the other end of the upper ring and the lower ring are detachably connected via a locking piece.

8. The wing retraction device according to claim 7, characterized in that: The ends of the upper circle and the lower circle are both provided with limiting bosses, and the locking member is installed on the limiting bosses.

9. A method for wing retraction and extension, characterized in that, The wing retracting and releasing device according to any one of claims 1 to 8 comprises the following process: When folding the wing, the fixing ring is installed to the set position of the missile body, and then the wing is folded onto the missile body, and at the same time, the constraint mechanism corresponding to the position of the wing on the fixing ring limits the free end of the wing, and this process is repeated to complete all the wings that need to be folded one by one; When releasing the wings, the limit constraints of the constraint mechanisms on the wings are released one by one, and the wings automatically pop open under the action of their own structure, completing the release of some or all of the designated wings.

10. The wing retraction and extension method according to claim 9, characterized in that, It also includes the following processes: When folding the wings, after the restraint mechanism has completed the position restraint of all the wings that need to be folded one by one, the restraint belt is used to tie up the wings that have completed the position restraint, and then the fixing ring is separated from the missile body; When releasing the wings, first install the fixing ring to the corresponding position of the missile body, and make the constraint mechanism limit and constrain each wing, then loosen the binding belt, and then release the limit constraints of the constraint mechanism on the specified wing one by one to complete the release of some of the specified wings or all of the wings.

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