A single-wing folding and unfolding mechanism

Abstract

This utility model belongs to the field of guided bombs and discloses a single-wing folding and deployment mechanism, including a base with a central shaft in the middle. The base is also concave cylindrical, with a fixing frame installed inside. An electromagnetic pin is installed within the fixing frame. The central shaft has a stepped design, and a rotating assembly is rotatably mounted on the central shaft. A wing frame is mounted on the rotating assembly. The rotating assembly includes a rotating component with a pin hole bracket on its lower surface. A sleeve is mounted on the top of the central shaft, and a spiral spring is mounted on the sleeve. The inner end of the spiral spring is fixed to the central shaft, and the outer end is fixed to the rotating component. This single-wing folding and deployment mechanism of this utility model integrates the electromagnetic pin, spiral spring, and limiting mechanism within the base through radial insertion and removal of the electromagnetic pin. This reduces vertical dimensions, decreases the overall volume, increases integration, and makes it suitable for deployment in confined bomb spaces. It improves safety and reliability, enhances versatility, and reduces production costs.

Description

Technical Field

[0001] This utility model belongs to the field of guided bombs, and in particular relates to a folding and unfolding mechanism for a single-wing design. Background Technology

[0002] In warfare, the most effective way to destroy fixed enemy ground targets is through air strikes using aircraft or drones. Therefore, airborne weapons have become crucial for attacking ground targets, especially large, fixed targets. Guided bombs, compared to missiles, have a much larger mass and explosive charge, resulting in greater destructive power. However, compared to missiles, guided bombs experience greater gravity and drag, and generally lack propulsion, thus limiting their range. To address these issues and compensate for the shorter range of guided bombs, a folding and unfolding wing mechanism can be installed on traditional guided bombs. This allows the wings to unfold from folded to extended range, achieving a gliding range extension effect.

[0003] Comparing with Chinese Patent CN116499315A, a loitering munition wing folding and unfolding mechanism with electromagnet locking is disclosed, including a rotating unfolding element, a rotating base, an electromagnet locking element, and a wing box. The rotating unfolding element includes a rotating shaft, a left wing root rotating part, a left wing root connecting plate, a right wing root rotating part, and a right wing root connecting plate. The rotating shaft is used to connect and fix the wing and is equipped with a torsion spring to control the wing folding and unfolding. The left and right wing roots are provided with electromagnet locking holes for locking and unlocking the wing folding and unfolding. The rotating base is provided with bolt locking mating holes and base connecting screws. The electromagnet locking element includes an electromagnet, a left inner side plate, a left outer side plate, a right inner side plate, and a right outer side plate. The inner and outer side plates are provided with connecting screw holes for electromagnet connection. The wing box includes a wing box inner plate, a wing box outer shell, and a wing box top plate. The wing box inner plate is nested inside the wing box outer shell and is provided with a wing box connecting screw hole and a base locking threaded hole. It can control the locking and unlocking states when the loitering munition wing unfolds and folds.

[0004] However, the aforementioned patents have high vertical dimension requirements, occupy a large space, and require four-point sliding locking, which seriously affects the convenience and accuracy of unfolding and locking. Therefore, a new device needs to be designed. Utility Model Content

[0005] The purpose of this invention is to provide a folding and unfolding mechanism for a single wing to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A folding and unfolding mechanism for a single-wing aircraft includes a base with a central shaft in the center. The base is concave cylindrical with two limiting protrusions on its inner wall. A fixing frame is installed inside the base, and an electromagnetic pin is installed within the fixing frame. The central shaft has a stepped design, and a rotating assembly is rotatably mounted on the central shaft. A wing frame is mounted on the rotating assembly. The rotating assembly includes a rotating component with a stepped design. A pair of angular contact ball bearings are installed in the center of the rotating component, and retaining rings are provided on the end faces of the angular contact ball bearings. A pin hole bracket is installed on the lower surface of the rotating component, and a stop pin is provided on one side of the pin hole bracket. An outer end cap is installed on the upper end face of the rotating component. A sleeve is installed on the top of the central shaft, and an inner end cap is installed on the top of the central shaft. A spiral spring is provided on the sleeve. The inner end of the spiral spring is fixed to the central shaft, and the outer end of the spiral spring is fixed to the rotating component. The stop pin and the limiting protrusion limit the rotation angle of the rotating component from 0° to 90°. The electromagnetic pin is inserted into the pin hole bracket at the 0° and 90° positions, respectively, which are the locking positions for folding and unfolding the rotating component.

[0008] Furthermore: a front cable cover is provided at the front of the base, and a rear cable cover is provided at the rear of the base. The base, the front cable cover, and the rear cable cover are fixed to the projectile by metal straps.

[0009] Furthermore: a left wing assembly and a right wing assembly are respectively installed on both sides of the wing frame; a top cover is installed inside the concave end face of the wing frame; a long carbon rod is installed at the front end of the wing frame, and the long carbon rod passes through the front end of the left wing assembly and the right wing assembly.

[0010] Furthermore: the left wing assembly includes a left wing body, a left short carbon rod is installed at the rear end of the left wing body, and a left wing cap is installed at the outer end of the left wing body; the right wing assembly includes a right wing body, a right short carbon rod is installed at the rear end of the right wing body, and a right wing cap is installed at the outer end of the right wing body.

[0011] Furthermore, the left wing body and the right wing body are respectively adopted as roll-formed aluminum alloy structures, and are provided with reinforcing ribs at both ends.

[0012] Further: The parameters of the spiral spring are: 4 coils, inner diameter 36mm, outer diameter 70mm, thickness 2mm, width 10mm; and spring force range of 200-350N.

[0013] Furthermore, the electromagnetic pin parameters are: length 56.8mm, width 25mm, height 22mm, pin diameter 7.5mm, and telescopic length 12mm.

[0014] Compared with existing technologies, the beneficial effects are:

[0015] 1. By using the radial insertion and removal of the electromagnetic pin, the electromagnetic pin, spiral spring, and limiting mechanism are highly integrated into the base, reducing the vertical dimension, decreasing the overall volume, increasing the integration, making it suitable for deployment in confined projectile spaces, improving safety and reliability, while also enhancing versatility and reducing production costs.

[0016] 2. Except for the electromagnetic pin, all parts adopt a purely mechanical structure design, which is safer, more reliable and convenient. The electromagnetic pin and the pin hole frame are matched in two positions (0° and 90°) to ensure rigid locking in the folded / unfolded state and prevent accidental unlocking due to vibration during flight. The mechanical limit design of the stop pin and the limit protrusion precisely controls the rotation angle range (0°-90°) to prevent over-rotation and damage to the mechanism.

[0017] 3. The spiral spring (parameter optimization: 4 coils, spring force 200-350N) provides stable torque output, and the unfolding time from the folded state to the unfolded state is within 500ms, achieving rapid unfolding. At the same time, it reduces the external drive requirement by pre-compressing and storing energy.

[0018] 4. The metal straps secure the base and cable cover, which can withstand 20G impact vibration (compliant with GJB150A-2009 standard) and adapt to the high overload environment of missile launch; the split cable cover (front / rear cover) design facilitates maintenance and avoids cable entanglement affecting deployment; it can be applied to various types of guided bombs and has strong versatility. Attached Figure Description

[0019] Figure 1 This is a structural schematic diagram of a single-wing folding and unfolding mechanism according to the present invention;

[0020] Figure 2 This is a schematic diagram of the base of the folding and unfolding mechanism of the single-wing described in this utility model;

[0021] Figure 3 This is a bottom-view axonometric drawing of the rotating component of the folding and unfolding mechanism of the single-wing described in this utility model;

[0022] Figure 4 This is a schematic diagram of the unfolded state of the single-wing folding and unfolding mechanism described in this utility model;

[0023] Figure 5 This is a schematic diagram of the folded state of the single-wing folding and unfolding mechanism described in this utility model;

[0024] Figure 6 This is a schematic diagram of the left and right wing bodies of the one-wing folding and unfolding mechanism described in this utility model in their unfolded states;

[0025] Figure 7This is a schematic diagram of the installation of the long carbon rod of the folding and unfolding mechanism of the single-wing described in this utility model.

[0026] In the attached diagram, the following are the reference numerals: 01, base; 02, electromagnetic pin; 03, fixing frame; 04, rotating component; 05, stop pin; 06, pin hole frame; 07, angular contact ball bearing; 08, snap ring; 09, sleeve; 10, spiral spring; 11, inner end cover; 12, outer end cover; 13, wing frame; 14, top cover; 15, front cable cover; 16, rear cable cover; 17, metal band; 18, central shaft; 19, limiting protrusion; 100, left wing assembly; 101, left wing body; 102, left wing end cap; 103, left short carbon rod; 200, right wing assembly; 201, right wing body; 202, right wing end cap; 203, right short carbon rod; 301, long carbon rod; 900, projectile. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0028] Please see Figures 1-7 A folding and unfolding mechanism for a single-wing aircraft includes a base 01, a central shaft 18 in the middle of the base 01, and the base 01 being a concave cylindrical shape. Two limiting protrusions 19 are provided on the inner wall of the base 01. A fixing frame 03 is installed inside the base 01, and an electromagnetic pin 02 is installed inside the fixing frame 03. The central shaft 18 adopts a stepped design, and a rotating component is rotatably installed on the central shaft 18. An aircraft wing frame 13 is installed on the rotating component.

[0029] In this embodiment: the rotating assembly includes a rotating component 04, which adopts a stepped design. A pair of angular contact ball bearings 07 are installed in the middle of the rotating component 04. A retaining ring 08 is provided on the end face of the angular contact ball bearing 07. A pin hole bracket 06 is installed on the lower surface of the rotating component 04. A stop pin 05 is provided on one side of the pin hole bracket 06. An outer end cover 12 is installed on the upper end face of the rotating component 04. A sleeve 09 is installed on the top of the central shaft 18. An inner end cover 11 is installed on the top of the central shaft 18. A spiral spring 10 is provided on the sleeve 09. The inner end of the spiral spring 10 is fixed on the central shaft 18, and the outer end of the spiral spring 10 is fixed on the rotating component 04. The stop pin 05 and the limiting protrusion 19 limit the rotation angle of the rotating component 04 from 0° to 90°. The electromagnetic pin 02 is inserted into the pin hole bracket 06 at the 0° position and the 90° position, respectively, which are the locking positions for folding and unfolding the rotating component 04.

[0030] Furthermore: A front cable cover 15 is provided at the front of the base 01, and a rear cable cover 16 is provided at the rear of the base 01. The base 01, the front cable cover 15, and the rear cable cover 16 are fixed to the projectile body 900 by metal bands 17; a left wing assembly 100 and a right wing assembly 200 are respectively installed on both sides of the wing frame 13. A top cover 14 is installed in the concave end face of the wing frame 13. A long carbon rod 301 is installed at the front end of the wing frame 13, and the long carbon rod 301 passes through the front end of the left wing assembly 100 and the right wing assembly 200; the left wing assembly 100 includes a left wing body 101, a left short carbon rod 103 is installed at the rear end of the left wing body 101, and a left... Wing cap 102; Right wing assembly 200 includes right wing body 201, right short carbon rod 203 is installed at the rear end of right wing body 201, and right wing cap 202 is installed at the outer end of right wing body 201; Left wing body 101 and right wing body 201 are respectively adopted by roll forming aluminum alloy structure, and reinforcing ribs are provided at both ends; Parameters of spiral spring 10: number of coils is 4, inner diameter is 36mm, outer diameter is 70mm, thickness is 2mm, width is 10mm; elastic force range is 200-350N; Parameters of electromagnetic pin 02: length is 56.8mm, width is 25mm, height is 22mm, pin diameter is 7.5mm, telescopic length is 12mm.

[0031] During assembly: The wing frame 13 is bolted onto the upper stepped surface of the rotating component 04. The long carbon rod 301 is inserted into the carbon rod hole at the front end of the wing frame 13. The left short carbon rod 103 and the right short carbon rod 203 are respectively inserted into the left and right carbon rod holes at the rear end of the wing frame 13 and glued together with resin adhesive. The left wing body 101 and the right wing body 201 are then installed onto the left and right ends of the wing frame 13, and the connecting surfaces are glued together. Countersunk screws are used at the wing roots of the left wing body 101 and the right wing body 201. For connection and fixation, the long carbon rod 301, the left short carbon rod 103, and the right short carbon rod 203 need to be embedded into the carbon rod grooves of the left wing body 101 and the right wing body 201, and need to be glued together; the left wing cover 102 and the right wing cover 202 are glued to the wingtips of the left wing body 101 and the right wing body 201 respectively with resin glue; the top cover 14 is installed in the concave end face of the wing frame 13 with hexagonal bolts; the base 01, the front cable cover 15, and the rear cable cover 16 are fixed to the projectile body 900 by metal bands 17;

[0032] When folded, the wing frame 13, the left wing body 101 and the right wing body 201 are distributed along the length of the projectile 900. The rotating part 04 torsion compresses the spiral spring 10 supported by the central shaft 18 to store the elastic force. The fixed frame 03 supports the electromagnetic pin 02 to be inserted into the pin hole frame 06 for fixed limit.

[0033] When unfolded, the fixed frame 03 first supports the electromagnetic pin 02 to retract and disengage from the pin hole frame 06. The spiral spring 10 releases its elastic force, pushing the rotating part 04 to rotate under the support of a pair of angular contact ball bearings 07 on the central shaft 18. At the same time, it drives the wing frame 13 to rotate. The stop pin 05 on the bottom surface of the rotating part 04 cooperates with the limiting protrusion 19 on the base 01 to limit the rotation angle of the rotating part 04 from 0° to 90°. When the wing frame 13, the left wing body 101 and the right wing body 201 rotate to be perpendicular to the length direction of the projectile 900, the electromagnetic pin 02 extends and inserts into the pin hole frame 06, locking the unfolding.

[0034] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A folding and unfolding mechanism for a single-wing structure, comprising a base (01), wherein a central shaft (18) is disposed in the middle of the base (01), characterized in that: It also includes a base (01) which is concave cylindrical, with two limiting protrusions (19) on the inner wall of the base (01), a fixing frame (03) installed inside the base (01), an electromagnetic pin (02) installed inside the fixing frame (03), a stepped design for the central shaft (18), a rotating assembly rotatably mounted on the central shaft (18), and an wing frame (13) mounted on the rotating assembly; The rotating assembly includes a rotating component (04), which has a stepped design. A pair of angular contact ball bearings (07) are installed in the middle of the rotating component (04). A retaining ring (08) is provided on the end face of the angular contact ball bearing (07). A pin hole bracket (06) is installed on the lower surface of the rotating component (04). A stop pin (05) is provided on one side of the pin hole bracket (06). An outer end cap (12) is installed on the upper surface of the rotating component (04). A sleeve (09) is installed on the top of the central shaft (18), and an inner end cap (11) is installed on the top of the central shaft (18). A spiral spring (10) is provided on the sleeve (09), with the inner end of the spiral spring (10) fixed on the central shaft (18) and the outer end of the spiral spring (10) fixed on the rotating part (04). The stop pin (05) and the limiting protrusion (19) limit the rotation angle of the rotating part (04) from 0° to 90°; the electromagnetic pin (02) is inserted into the pin hole frame (06) at the 0° position and the 90° position respectively, which are the locking positions for the folding and unfolding of the rotating part (04).

2. The folding and unfolding mechanism for a single-wing design according to claim 1, characterized in that: A front cable cover (15) is provided in front of the base (01), and a rear cable cover (16) is provided behind the base (01). The base (01), the front cable cover (15) and the rear cable cover (16) are fixed to the projectile (900) by metal bands (17).

3. The folding and unfolding mechanism for a single-wing design according to claim 1, characterized in that: The left wing assembly (100) and the right wing assembly (200) are respectively installed on both sides of the wing frame (13). A top cover (14) is installed in the concave end face of the wing frame (13). A long carbon rod (301) is installed at the front end of the wing frame (13). The long carbon rod (301) passes through the front end of the left wing assembly (100) and the right wing assembly (200).

4. The folding and unfolding mechanism for a single-wing design according to claim 3, characterized in that: The left wing assembly (100) includes a left wing body (101), a left short carbon rod (103) is installed at the rear end of the left wing body (101), and a left wing cap (102) is installed at the outer end of the left wing body (101); the right wing assembly (200) includes a right wing body (201), a right short carbon rod (203) is installed at the rear end of the right wing body (201), and a right wing cap (202) is installed at the outer end of the right wing body (201).

5. The folding and unfolding mechanism for a single-wing design according to claim 4, characterized in that: The left wing body (101) and the right wing body (201) are respectively adopted as roll-formed aluminum alloy structures, and are provided with reinforcing ribs at both ends.

6. The folding and unfolding mechanism for a single-wing structure according to claim 1, characterized in that: The parameters of the spiral spring (10) are: 4 coils, 36mm inner diameter, 70mm outer diameter, 2mm thickness, and 10mm width; the elastic force range is 200-350N.

7. The folding and unfolding mechanism for a single-wing design according to claim 1, characterized in that: The electromagnetic pin (02) has the following parameters: length 56.8mm, width 25mm, height 22mm, pin diameter 7.5mm, and telescopic length 12mm.

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