Self-locking folding missile wing unfolding mechanism

Abstract

The invention belongs to the technical field of guided ammunition folding ammunition wings, and particularly relates to a self-locking folding ammunition wing unfolding mechanism which comprises a high-pressure gas cylinder, an air supply control valve, a self-locking device and a self-locking device, and the outlet of the high-pressure gas cylinder is provided with an air supply control valve; the oval push rod comprises a push rod body and a push rod inner cavity formed in the push rod body, and the outer wall of the push rod body is provided with an oval contact surface; one end of the gas supply pipeline is connected with an outlet of the high-pressure gas cylinder, the other end of the gas supply pipeline is provided with a sealed gas supply nozzle, and the sealed gas supply nozzle is communicated with the inner cavity of the push rod; the end of the missile wing assembly is provided with a missile wing eccentric rotating shaft, and the missile wing eccentric rotating shaft abuts against the oval contact face of the push rod. According to the self-locking folding missile wing unfolding mechanism, rapid and synchronous unfolding of the folding missile wings can be achieved, self-locking can be achieved while the folding missile wings are unfolded in place, and the self-locking folding missile wing unfolding mechanism is simple in structure, high in environment adaptability, convenient to use repeatedly, safe, reliable and beneficial to engineering implementation.

Description

Technical Field

[0001] The present application belongs to the technical field of folding wings of guided ammunition, and specifically relates to a self-locking folding wing deployment mechanism, and in particular to a folding wing deployment mechanism with a self-locking function driven by high-pressure gas. Background Art

[0002] The folding wing assembly can effectively reduce the size envelope of guided munitions, making them easier to transport, mount and launch. During the flight of the guided munition, the wing assembly unfolds to form a large aspect ratio aerodynamic configuration, improving the lift-to-drag characteristics of the guided munition. It is especially suitable for subsonic cruise missiles that have requirements for ceiling and range.

[0003] In order to achieve the rapid deployment of the folding wing assembly under specific flight conditions, it must be equipped with corresponding driving mechanisms and positioning locking devices. Currently, the commonly used ones include electric mechanisms, spring release mechanisms and pyrotechnic actuators. Among them, the electric mechanism requires the use of a complex transmission mechanism, which occupies a large space, has relatively poor transmission synchronization, consumes a lot of energy for positioning locking, and has high requirements for the use environment. It is easy to fail in a high-altitude and low-temperature environment; the spring release mechanism needs to be equipped with an independent locking mechanism before it works. Due to the stress release of the spring, it is not suitable for the rapid use of guided ammunition after long-term storage; the pyrotechnic actuator mainly uses the high-temperature and high-pressure gas generated by the explosive to drive the mechanism to move, which has high requirements for the sealing of the internal cavity of the actuator, and is prone to large vibration shock.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a self-locking folding wing deployment mechanism to solve at least one of the problems of the existing folding wing deployment mechanism, namely, complex structure, one-time use, poor deployment synchronization, and unreliable locking.

[0006] The technical solution of this application is:

[0007] A self-locking folding wing deployment mechanism, comprising:

[0008] A high-pressure gas cylinder, wherein a gas supply control valve is provided at the outlet of the high-pressure gas cylinder;

[0009] An oval push rod, the oval push rod comprising a push rod and a push rod inner cavity opened inside the push rod, and the outer wall of the push rod has an oval contact surface;

[0010] An air supply pipeline, one end of which is connected to the outlet of the high-pressure gas cylinder, and the other end of which is provided with a sealed air supply nozzle, which is communicated with the inner cavity of the push rod;

[0011] The elastic wing assembly has an eccentric rotating shaft for the elastic wing at the end thereof, and the eccentric rotating shaft for the elastic wing abuts against the oval contact surface of the push rod.

[0012] In at least one embodiment of the present application, the high-pressure gas cylinder, the gas supply pipeline, and the sealed gas supply nozzle are all fixedly installed inside the guided ammunition.

[0013] In at least one embodiment of the present application, the air supply control valve is controlled by instructions from a guided munitions control system.

[0014] In at least one embodiment of the present application, the sealed air supply nozzle comprises:

[0015] A connecting straight pipe, one end of which is connected to the gas supply pipeline;

[0016] An air supply nozzle, the air supply nozzle is nested inside the push rod, the air supply nozzle is connected to the other end of the connecting straight pipe, and the air supply nozzle is provided with a mounting groove along the circumferential direction;

[0017] A graphite rubber sealing ring is installed in the installation groove.

[0018] In at least one embodiment of the present application, the eccentric rotating shafts of the elastic wings are symmetrically arranged in a group along the circumference of the oval push rod.

[0019] In at least one embodiment of the present application, the eccentric rotating shafts of the wing are symmetrically arranged in multiple groups along the circumference of the oval push rod.

[0020] In at least one embodiment of the present application, the wing eccentric shaft includes:

[0021] A wing shaft, the wing shaft being fixedly connected to an end of the wing assembly;

[0022] An eccentric rotating wheel is connected to the elastic wing rotating shaft through a key, and the eccentric rotating wheel and the elastic wing rotating shaft are eccentrically arranged, and the eccentric rotating wheel abuts against the oval contact surface of the push rod.

[0023] In at least one embodiment of the present application, when the wing is deployed in place, the edges of the eccentric rotating wheels of the two eccentric rotating shafts of the wing symmetrically arranged in the same group reach the maximum spacing.

[0024] The invention has at least the following beneficial technical effects:

[0025] The self-locking folding wing deployment mechanism of the present application can realize the rapid and synchronous deployment of the folding wings, and can realize self-locking when deployed in place. It has a simple structure, strong environmental adaptability, is easy to reuse, safe and reliable, and is conducive to engineering implementation. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic diagram of a folded state of a self-locking folding wing deployment mechanism according to an embodiment of the present application;

[0027] Figure 2 This is a schematic diagram of a self-locking folding wing deployment mechanism in an embodiment of the present application;

[0028] Figure 3 is a schematic diagram of a sealed air supply nozzle according to an embodiment of the present application;

[0029] Figure 4 is a schematic diagram of an oval push rod according to an embodiment of the present application;

[0030] Figure 5 It is a schematic diagram of an eccentric rotating shaft of a wing of an embodiment of the present application;

[0031] Figure 6 It is a schematic diagram of the deployment process of a self-locking folding wing deployment mechanism according to an embodiment of the present application.

[0032] in:

[0033] 1-high pressure gas cylinder; 2-gas supply control valve; 3-gas supply pipeline; 4-sealed gas supply nozzle; 41-gas supply nozzle; 42-graphite rubber sealing ring; 43-connecting straight pipe; 5-ovate push rod; 51-push rod; 52-push rod inner cavity; 6-eccentric shaft of the wing; 61-wing shaft; 62-eccentric rotor; 7-wing assembly. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0035] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present 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 should not be understood as limiting the scope of protection of the present application.

[0036] The following is combined with Figures 1 to 6 This application is described in further detail.

[0037] The present application provides a self-locking folding wing deployment mechanism, comprising: a high-pressure gas cylinder 1, an air supply control valve 2, an air supply pipeline 3, a sealed air supply nozzle 4, an oval push rod 5, an eccentric rotating shaft of the wing 6 and a wing assembly 7.

[0038] Specifically, Figure 1-2 As shown, the high-pressure gas cylinder 1 adopts a small gas cylinder, and a gas supply control valve 2 is arranged at the outlet of the high-pressure gas cylinder 1, and the gas supply control valve 2 can control the on-off of the gas supply and adjust the gas supply flow. The oval push rod 5 includes a push rod 51 and a push rod inner cavity 52 opened inside the push rod 51. The outer wall of the push rod 51 has an oval contact surface, and the push rod inner cavity 52 can be used as a gas collecting container for high-pressure gas; one end of the gas supply pipeline 3 is connected to the outlet of the high-pressure gas cylinder 1, and the other end is provided with a sealed gas supply nozzle 4, which is connected to the push rod inner cavity 52, and the high-pressure gas is supplied to the push rod inner cavity 52 inside the push rod 51 through the sealed gas supply nozzle 4; the wing assembly 7 includes a wing body and a shaft mounting seat installed at the end of the wing body, and the wing eccentric shaft 6 is fixedly installed on the shaft mounting seat, and the wing eccentric shaft 6 abuts against the oval contact surface of the push rod 52.

[0039] In a preferred embodiment of the present application, the self-locking folding wing deployment mechanism can be applied to guided ammunition. In this embodiment, the high-pressure gas cylinder 1, the gas supply pipeline 3 and the sealed gas supply nozzle 4 are all fixedly installed inside the guided ammunition, wherein the high-pressure gas cylinder 1 and the sealed gas supply nozzle 4 are fixed at corresponding positions inside the guided ammunition, the gas supply pipeline 3 is sealed, and the switch state and opening degree of the gas supply control valve 2 are controlled by the command of the guided ammunition control system.

[0040] In a preferred embodiment of the present application, Figure 3As shown, the sealed air supply nozzle 4 includes: an air supply nozzle 41, a graphite rubber sealing ring 42 and a connecting straight pipe 43, wherein one end of the connecting straight pipe 43 is connected to the air supply pipeline 3, and the connecting straight pipe 43 can be used as a positioning structure of the sealed air supply nozzle 4, and is fixedly connected to the structural parts inside the guided ammunition to fix the sealed air supply nozzle 4 at the front of the wing assembly 7; the outer shape of the air supply nozzle 41 is a cylindrical structure, and the air supply nozzle 41 is nested inside the push rod 51. The air supply nozzle 41 is connected to the other end of the connecting straight pipe 43, and the high-pressure gas in the air supply pipeline 3 is supplied into the cylindrical push rod inner cavity 52 inside the push rod 51 through the air supply nozzle 41. The air supply nozzle 41 is provided with an installation groove along the circumferential direction; the graphite rubber sealing ring 42 is installed in the installation groove, and the graphite rubber sealing ring 42 is squeezed by the inner wall of the push rod 51 to achieve the sealing of the push rod inner cavity 52.

[0041] In the self-locking folding wing deployment mechanism of the present application, the wing eccentric shafts 6 are arranged symmetrically along the circumference of the oval push rod 5 in one or more groups, and each group includes two wing eccentric shafts 6. Figure 4-5 As shown, the wing eccentric shaft 6 includes: a wing shaft 61 and an eccentric wheel 62. The wing shaft 61 is fixedly connected to the shaft mounting seat at the end of the wing assembly 7. The eccentric wheel 62 is connected to the wing shaft 61 through a key, and the eccentric wheel 62 is eccentrically arranged with the wing shaft 61. The edge of the eccentric wheel 62 abuts against the oval contact surface of the push rod 52. Advantageously, by designing the oval contact surface of the push rod 52, when the wing is deployed in place, the edges of the eccentric wheels 62 of the two symmetrically arranged wing eccentric shafts 6 in the same group reach the maximum spacing.

[0042] The self-locking folding wing deployment mechanism of the present application, when the wing needs to be changed from a folded state to an deployed state, the guided ammunition control system sends a command to the guided ammunition control system to control the air supply control valve 2 to open, and the high-pressure gas inside the high-pressure gas cylinder 1 is supplied to the push rod inner cavity 52 of the oval push rod 5 through the air supply pipeline 3 and the sealed air supply nozzle 4 fixed on the front of the wing assembly 7. The high-pressure gas pushes the push rod 51 to move, and the symmetrically arranged wing eccentric shaft 6 is squeezed and rotated by the movement of the oval push rod 5, driving the wing assembly 7 to rotate and deploy around the wing eccentric shaft 6. The deployed position of the wing assembly 7 is the position with the maximum distance between the edges of the two symmetrically arranged wing eccentric shafts 6 in the same group, and the oval push rod 5 can no longer squeeze and push the wing eccentric shaft 6 to rotate, thereby realizing the self-locking system when the wing is deployed. Figure 6 As shown in FIG. 1 , state I is the wing folded state, and state II is the wing unfolded state. The wing folding process is opposite to the above unfolding process, which will not be described here.

[0043] The self-locking folding wing deployment mechanism of the present application can realize the rapid and synchronous deployment of the folding wing, and can realize the self-locking system when it is deployed in place. Compared with the prior art, the present application has the following significant advantages:

[0044] a. Using high-pressure gas source as the driving power source simplifies the system structure, improves working reliability, and effectively reduces the impact on the projectile during the driving process;

[0045] b. The sealed gas collecting cavity is used to drive the push rod to drive the eccentric shaft of the missile wing to rotate. The transmission efficiency is high, the push rod stroke is short, and the required high-pressure gas volume is small, which effectively controls the volume of the high-pressure gas cylinder and reduces the demand for the internal space of the guided ammunition;

[0046] c. An oval push rod is used to push the eccentric shaft to rotate to realize the unfolding transmission of the folding wings. When the wings are fully unfolded, the edges of the symmetrically arranged eccentric shafts reach the maximum spacing, and the oval push rod cannot continue to push the shaft to rotate. The push rod is fixed under the action of the high-pressure gas in the push rod cavity, and the self-locking system of the wings fully unfolded is automatically realized without adding an independent locking mechanism.

[0047] d. There are no disposable consumables during the working process, which is convenient for repeated verification and use, and can effectively reduce the development cost.

[0048] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A self-locking folding wing deployment mechanism, characterized in that: include: A high-pressure gas cylinder (1), wherein a gas supply control valve (2) is provided at the outlet of the high-pressure gas cylinder (1); An oval push rod (5), the oval push rod (5) comprising a push rod (51) and a push rod inner cavity (52) opened inside the push rod (51), and the outer wall of the push rod (51) has an oval contact surface; An air supply pipeline (3), one end of which is connected to the outlet of the high-pressure gas cylinder (1), and the other end of which is provided with a sealed air supply nozzle (4), and the sealed air supply nozzle (4) is in communication with the push rod inner cavity (52); A wing assembly (7), wherein an eccentric wing shaft (6) is provided at the end of the wing assembly (7), and the eccentric wing shaft (6) abuts against the oval contact surface of the push rod (52).

2. The self-locking folding wing deployment mechanism according to claim 1, characterized in that: The high-pressure gas cylinder (1), the gas supply pipeline (3) and the sealed gas supply nozzle (4) are all fixedly installed inside the guided ammunition.

3. The self-locking folding wing deployment mechanism according to claim 2, characterized in that: The air supply control valve (2) is controlled by instructions from a guided ammunition control system.

4. The self-locking folding wing deployment mechanism according to claim 3, characterized in that: The sealed air supply nozzle (4) comprises: A connecting straight pipe (43), one end of which is connected to the air supply pipeline (3); An air supply nozzle (41), wherein the air supply nozzle (41) is nested inside the push rod (51), the air supply nozzle (41) is connected to the other end of the connecting straight pipe (43), and the air supply nozzle (41) is provided with a mounting groove along the circumferential direction; A graphite rubber sealing ring (42), wherein the graphite rubber sealing ring (42) is installed in the installation groove.

5. The self-locking folding wing deployment mechanism according to claim 1, characterized in that: The eccentric rotating shafts (6) of the elastic wings are symmetrically arranged in a group along the circumference of the oval push rod (5).

6. The self-locking folding wing deployment mechanism according to claim 1, characterized in that: The eccentric rotating shafts (6) of the elastic wings are symmetrically arranged in multiple groups along the circumference of the oval push rod (5).

7. The self-locking folding wing deployment mechanism according to claim 5 or 6, characterized in that: The wing eccentric shaft (6) comprises: A wing shaft (61), the wing shaft (61) being fixedly connected to an end of the wing assembly (7); An eccentric rotating wheel (62), wherein the eccentric rotating wheel (62) is connected to the elastic wing rotating shaft (61) via a key, and the eccentric rotating wheel (62) and the elastic wing rotating shaft (61) are eccentrically arranged, and the eccentric rotating wheel (62) abuts against the oval contact surface of the push rod (52).

8. The self-locking folding wing deployment mechanism according to claim 7, characterized in that: When the wing is fully deployed, the edges of the eccentric rotating wheels (62) of the two eccentric rotating shafts (6) of the wing arranged symmetrically in the same group reach the maximum spacing.

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