CN112985190A

CN112985190A - Volute spiral spring type folding missile wing unfolding mechanism

Info

Publication number: CN112985190A
Application number: CN202110410580.1A
Authority: CN
Inventors: 吴俊全; 卢山; 张晓旻; 胥磊; 李心元; 孙俊峰; 张菲; 齐红亮; 吴敏
Original assignee: Xian Aerospace Propulsion Institute
Current assignee: Xian Aerospace Propulsion Institute
Priority date: 2021-04-13
Filing date: 2021-04-13
Publication date: 2021-06-18

Abstract

The invention relates to the technical field of small tactical missiles, in particular to a folding missile wing. A wrap spring type folding missile wing deployment mechanism comprising: the wing surface and the wing seat are movably connected, and a volute spiral spring is arranged in the wing surface; when the missile leaves the box in a launching mode, the wing surface is in a folded state, and the spiral spring elastically deforms along with the wing surface to generate torque in the unfolding direction of the wing surface; when the missile leaves the launching box, the wing surfaces are unfolded outwards to a set angle under the torque action of the spiral spring. The invention adopts the volute spiral spring as a power source, does not need to eject control instructions and initiating explosive devices, has simple and reliable structure, lower cost, good synchronism in the unfolding process and small interference on the full-ejection attitude. The volute spiral spring is installed inside the wing surface, and the installation of the folding missile wing unfolding mechanism does not occupy the space of a missile body.

Description

Volute spiral spring type folding missile wing unfolding mechanism

Technical Field

The invention relates to the technical field of small tactical missiles, in particular to a folding missile wing.

Background

In order to miniaturize and store the launching device simply and conveniently, a large number of small tactical missiles are launched in a box (barrel) mode, and the missile wings are of a folding missile wing structure. When the missile is in the box (barrel), the wing surface is in a folded state by using the inner wall of the box (barrel) as constraint. After the missile is launched from the box (barrel), the wing surface is unfolded under the action of the unfolding mechanism.

The design of the modern missile structure (national defense industry publishing agency, 5 months 2014, 1 st edition) divides the folding missile wing into a longitudinal folding wing surface and a transverse folding wing surface, and details are provided on a common longitudinal folding wing surface mechanism and a common transverse folding wing surface mechanism. The power sources of the existing folding missile wing mechanism comprise a torsion spring, a compression spring, gas pressure, a fire actuating cylinder and the like. However, none of the prior art documents relates to the unfolding of a foldable wing springing mechanism by using a spiral spring as a power source.

Disclosure of Invention

The purpose of the invention is: provides a volute spiral spring type folding missile wing unfolding mechanism which does not need the actuation of initiating explosive devices.

The technical scheme of the invention is as follows: a wrap spring type folding missile wing deployment mechanism comprising: the wing surface is movably connected with the wing seat through a rotating shaft and can rotate around the rotating shaft;

a volute spring is arranged in the wing surface, and two ends of the volute spring are respectively fixed on the wing surface and the rotating shaft; when the missile leaves the box during launching, the wing surface is in a folded state, the spiral spring elastically deforms along with the wing surface, the spiral spring is in a deformation energy storage state and generates torque in the unfolding direction to the wing surface, and the torque generated by the spiral spring is increased along with the increase of the folding angle of the wing surface.

When the missile leaves the launching box, the wing surface is not restrained and is unfolded outwards under the torque action of the spiral spring.

On the basis of the scheme, furthermore, a limiting shaft is arranged on the wing seat and used for limiting the unfolding angle of the wing surface.

In the above scheme, specifically, the rotating shaft is axially limited through the fixing screw.

Furthermore, one end of the rotating shaft is provided with a notch; one end of the spiral spring is fixed in the mounting groove in the wing surface, and the other end is fixed in the notch of the rotating shaft.

In the above scheme, specifically, the rotating shaft and the limiting shaft are installed on the same horizontal height of the wing seat.

Has the advantages that:

(1) the invention adopts the volute spiral spring as a power source, does not need to eject control instructions and initiating explosive devices, has simple and reliable structure, lower cost, good synchronism in the unfolding process and small interference on the full-ejection attitude.

(2) The volute spiral spring is installed inside the wing surface, and the installation of the folding missile wing unfolding mechanism does not occupy the space of a missile body.

Drawings

FIG. 1 is a schematic view of the present invention in an expanded state;

FIG. 2 is a cross-sectional view of FIG. 1;

FIG. 3 is a sectional view taken along line A-A of FIG. 1;

FIG. 4 is a schematic view of the present invention in a folded state;

FIG. 5 is a schematic view of the spiral spring of the present invention;

FIG. 6 is a schematic structural view of a rotating shaft according to the present invention;

FIG. 7 is a schematic view of the structure of the wing seat of the present invention;

wherein: 1-wing surface, 2-wing seat, 3-rotating shaft, 4-limiting shaft, 5-fixing screw and 6-volute spiral spring.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples.

The embodiment provides a volute spiral spring type folding missile wing unfolding mechanism, and is simple and reliable in structure, low in cost, good in unfolding process synchronism and small in interference on a full missile posture.

Referring to fig. 1 and 2, the spiral spring type folding missile wing unfolding mechanism comprises: the wing surface 1, wing seat 2 and spiral spring 6, wing surface 1 and wing seat 2 swing joint are equipped with spiral spring 6 in wing surface 1.

Referring to fig. 3, the airfoil 1 is movably connected with the airfoil seat 2 through a rotating shaft 3, and the rotating shaft 3 is axially limited through a fixing screw 5.

Referring to fig. 5 and 6, a notch is formed at one end of the rotating shaft 3; one end (wing surface fixed end) of the volute spiral spring 6 is fixed in the installation groove in the wing surface 1, the other end (rotating shaft fixed end) is fixed in the groove of the rotating shaft 3, therefore, the two ends of the volute spiral spring 6 are respectively fixed on the wing surface 1 and the rotating shaft 3, and the wing surface 1 can finish the deformation energy storage of the volute spiral spring 6 when being folded.

Referring to fig. 4 and 7, the wing base 2 is provided with a limiting shaft 4, and the limiting shaft 4 is used for limiting the position of the wing surface 1 after being unfolded. The wing seat 2 is also provided with a rotating shaft mounting hole, and the rotating shaft 3 and the limiting shaft 4 are mounted on the same horizontal height of the wing seat 2.

When the missile leaves the box in the launching process, the missile is limited by the interior of the launching box, the airfoil surface 1 is in a folded state, the spiral spring 6 is elastically deformed along with the airfoil surface 1, the spiral spring 6 is in a deformed energy storage state and generates torque in the unfolding direction to the airfoil surface 1, and the torque generated by the spiral spring 6 is increased along with the increase of the folding angle of the airfoil surface 1.

Referring to figure 2, when the projectile leaves the launch box, the airfoil 1 is unrestrained and begins to rotate about the axis of rotation 3 under the torque of the volute spiral spring 6; when the wing surface 1 rotates to a set angle, the wing surface 1 is in contact with the limiting shaft 4, the wing surface 1 stops rotating, and therefore the work of the volute spiral spring type folding missile wing unfolding mechanism is completed.

Although the invention has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims

1. The utility model provides a scroll spring formula is folded and is flicked wing deployment mechanism which characterized in that: the method comprises the following steps: a wing surface (1), a volute spiral spring (6) and a wing seat (2); the airfoil (1) is movably connected with the airfoil seat (2) through a rotating shaft (3), and the airfoil (1) can rotate around the rotating shaft (3);

a volute spring (6) is arranged in the wing surface (1); two ends of the volute spiral spring (6) are respectively fixed on the wing surface (1) and the rotating shaft (3), when the missile leaves the box in a launching mode, the wing surface (1) is in a folded state, and the volute spiral spring (6) deforms to store energy; when the missile leaves the launching box, the wing surfaces (1) are unfolded outwards under the torque action of the spiral spring (6).

2. The spiral spring type folding missile wing deployment mechanism of claim 1, characterized in that a limit shaft (4) is arranged on the wing seat (2), and the limit shaft (4) is used for limiting the deployment angle of the wing surface (1).

3. A spiral spring type accordion missile wing deployment mechanism as claimed in claim 1, characterized in that the rotation shaft (3) is axially limited by a fixing screw (5).

4. A volute spiral spring type folding missile wing deployment mechanism as claimed in claim 1, wherein one end of the rotating shaft (3) is provided with a notch; one end of the volute spiral spring (6) is fixed in the mounting groove in the airfoil (1), and the other end of the volute spiral spring is fixed in the groove of the rotating shaft (3).

5. A volute spiral spring type folding missile wing deployment mechanism as claimed in claim 2, characterized in that the rotation shaft (3) and the limit shaft (4) are mounted at the same level of the wing seat (2).