Shape-preserving protective plate for grating wing of aircraft

Abstract

The invention provides a shape-preserving protection plate for a grating wing of an aircraft. The shape-preserving protection plate comprises a cabin body, a protection plate body, the grating wing, fastening countersunk head screws and a pin puller. The protection plate is a high-temperature-resistant high-strength arc plate with an L-shaped section, the short edge of the protection plate is inserted into an axis gap between the grating wing and the cabin body, the long edge of the protection plate is attached to the exposed pneumatic face of the grating wing to form a shape-preserving face of the grating wing, and the section of the root is a quarter of a concave arc. The short edge of the arc plate and the grating wing share a pin puller, the root of the long edge is embedded into a quarter arc groove in the surface of the cabin body, a fastening sunk screw is installed on the rear section of the long edge, and the guard plate is connected with the grating wing. The shape-preserving protective plate for the grating wing of the aircraft has the advantages that the outer wall of the aircraft can be subjected to shape preserving when the grating wing is folded, the aerodynamic resistance is reduced, and the range is increased; and after the grating wings are unfolded, the shape-preserving protection plates are synchronously unfolded and are far away from the cabin body under the action of aerodynamic force. Meanwhile, the protective plate is simple in structure, light, high in strength and resistant to high temperature.

Description

Technical Field

[0001] This invention belongs to the field of aircraft component design, specifically, it relates to an aircraft grille wing conformal guard. Background Technology

[0002] Grid wings, also known as lattice wings, are an important component of aircraft. Serving as both lifting and control surfaces, grid wings improve the aircraft's lift characteristics and increase its stability and controllability. Grid wings are typically folded within the aircraft's cabin and deployed under specific conditions.

[0003] The typical design of a grid wing is a honeycomb structure with slanted walls at a 45° angle to the frame. The advantages of grid wings include high lift and strong control torque, making them suitable for aerodynamic control at hypersonic speeds. However, these advantages also introduce increased drag. When folded, the honeycomb-shaped outer edge of the grid wing forms the aerodynamic surface of the aircraft's outer wall, requiring more fuel to overcome this drag during flight, thus shortening the range.

[0004] Therefore, the industry needs a conformal protective plate for aircraft grille wings that can maintain the shape of the aircraft's outer wall when the grille wings are folded, reducing aerodynamic drag and increasing range. When the grille wings are deployed, the conformal protective plate should also deploy simultaneously and move away from the outer wall of the cabin under aerodynamic forces. At the same time, the protective plate should be simple in structure, lightweight, highly rigid, and resistant to high temperatures.

[0005] Chinese patent CN114087930B discloses a conformal folding structure for a grid wing, including a pivot, a torsion spring, a mounting base, a conformal cover, a grid wing, and a cabin, with the cabin mounted on an aircraft. The conformal cover is detachably connected to the top of the cabin, forming a sealed space between the cover and the cabin. The mounting base is located at the bottom of the cabin, and the grid wing is connected to the mounting base via a pivot with a torsion spring mounted on it. The axis of the pivot is perpendicular to the direction of movement of the aircraft. The grid wing has a retracted state and an operational state. When the grid wing is in the retracted state, the conformal cover is fixed to the top of the cabin, and the grid wing is retracted into the sealed space. When the grid wing is in the operational state, the conformal cover separates from the cabin, and the grid wing pops out under the action of the torsion spring. However, the conformal cover of this patent has high requirements for rigidity and strength, the structure is relatively complex and heavy, and it cannot achieve a deceleration and buffering effect during the deployment of the grid wing.

[0006] Currently, the industry typically uses specialized pin pullers to constrain the grille wing conformal guards, and the grille wings are then limited by the guards. This places high demands on the rigidity and strength of the guards, indirectly increasing their weight. Furthermore, there is no pivot structure at the base of the guards, and no deceleration or buffering design is observed during grille wing deployment, requiring further design optimization.

[0007] The conformal guard plate of this invention has an L-shaped longitudinal section, which enhances its rigidity. The structure is relatively simple and lightweight. This invention utilizes the impact of the countersunk screws on the limiting block and breakage separation during the deployment process to achieve the deceleration and buffering effect of the grid wing in place. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the present invention aims to provide an aircraft grille wing conformal protective plate, comprising: a cabin, a protective plate, a grille wing, countersunk screws for fastening, and a pin puller;

[0009] The protective plate has an L-shaped cross section. The short side of the protective plate is inserted into the axial gap between the grille wing and the cabin, and the long side is in contact with the exposed aerodynamic surface of the grille wing to form the conformal surface of the grille wing. The short side of the protective plate and the grille wing share a pull pin to be fastened to the cabin.

[0010] Near the root of the long side of the guard plate, the guard plate is fastened to the grille wing by tightening countersunk screws.

[0011] Preferably, the root section of the protective plate is a quarter-circular concave arc, and during installation, the root of the protective plate is embedded in a matching quarter-circular arc groove on the surface of the cabin.

[0012] Preferably, the size of the guard plate should match the size of the grille wing and be able to just cover the grille wing.

[0013] Preferably, the longitudinal section at the root of the protective plate is a quarter-circular concave arc.

[0014] Preferably, the surface of the cabin is provided with a quarter-circular groove that fits the root of the protective plate.

[0015] Preferably, the outer arc surface of the guard plate is connected to the grille wing by a countersunk screw.

[0016] Preferably, the number of the pin puller and the number of the countersunk screws are both one or more.

[0017] Preferably, during the deployment of the grille wing, the countersunk screw impacts the cabin limiting block, causing it to bend, break, and separate.

[0018] Preferably, when the grille wing reaches the deployment condition, the pin puller is activated, the constraints on the front of the grille wing and the guard plate are released, and the grille wing begins to deploy under the root torque.

[0019] Preferably, when the grille wing is in the folded state, the protective plate is fixed to the cabin; when the grille wing is fully unfolded, the protective plate separates from the cabin.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. The conformal protective plate designed in this invention can maintain the shape of the outer wall of the aircraft when the grid wings are folded, thereby reducing aerodynamic drag and increasing the range of the aircraft.

[0022] 2. This invention utilizes the impact and breakage of the countersunk screws during the deployment process to achieve the synchronous deployment of the conformal protective plate after the grid wing is deployed and it moves away from the cabin under the action of aerodynamic force.

[0023] 3. The present invention has a simple structure, is easy to operate, and is also lightweight, high-strength, and heat-resistant. Attached Figure Description

[0024] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0025] Figure 1 This is a cross-sectional view of the initial state of the conformal protective plate for the aircraft grille wing of the present invention.

[0026] Figure 2 This is a cross-sectional view of the unfolded state of the conformal protective plate of the aircraft grille wing of the present invention.

[0027] Figure 3 This is a cross-sectional view of the separated state of the aircraft grille conformal guard plate of the present invention.

[0028] The diagram shows: hull 1

[0029] Protective plate 2

[0030] Grille Wing 3

[0031] 4 countersunk screws

[0032] Pin puller 5 Detailed Implementation

[0033] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0034] The present invention provides an aircraft grille wing conformal guard, comprising: a cabin 1, a guard 2, a grille wing, countersunk screws 4, and a pin puller 5.

[0035] like Figure 1As shown, the grille wing folds inside the cabin 1, and is folded and limited by a puller 5. The protective plate 2 is a high-temperature resistant, high-strength arc plate with an L-shaped cross section and a U-shaped transverse section. The short side of the protective plate 2 is inserted into the axial gap between the grille wing and the cabin 1, and the long side fits against the exposed aerodynamic surface of the grille wing to form a conformal surface of the grille wing. The short side of the protective plate 2 and the grille wing are fastened to the cabin 1 by sharing the puller 5. Near the root of the long side of the protective plate 2, the protective plate 2 is fastened to the grille wing by a countersunk screw 4. The root section of the protective plate 2 is a quarter-circular concave arc. The surface of the cabin 1 has a quarter-circular arc groove that matches the root of the protective plate 2. During installation, the root of the protective plate 2 is embedded in the matching quarter-circular arc groove on the surface of the cabin 1.

[0036] like Figure 2 , Figure 3 As shown, when the grid wing reaches the deployment condition, the puller 5 is activated, releasing the constraints on the front of the grid wing and the protective plate 2. The grid wing begins to deploy under the torque at its root. This causes the protective plate 2 to flip outward, pulling out the countersunk screw 4, and the protective plate 2 rotates around the quarter-circle arc at its root. During the deployment of the grid wing, the countersunk screw 4 impacts the limiting block of the cabin 1, bending and breaking off, achieving buffer deceleration. The protective plate 2 gradually detaches from the quarter-circle arc of the projectile and moves away from the projectile under aerodynamic force, achieving separation. The outer arc surface of the protective plate 2 is connected to the grid wing by the countersunk screw 4, which is used to buffer and decelerate the grid wing. During installation, the number of countersunk screws 4 and pullers 5 can be one or more depending on the actual situation. Furthermore, the countersunk screw 4 is designed for easy wear.

[0037] When the grille wing is folded, the protective plate 2 is fixed to the cabin 1. After the grille wing is fully deployed, the protective plate 2 separates from the cabin 1. The size of the protective plate 2 should match the size of the grille wing and be able to perfectly cover the grille wing, so as to maintain the shape of the aircraft's outer wall when the grille wing is folded, reduce aerodynamic drag, and increase the aircraft's range. At the same time, the protective plate 2 has the advantages of simple structure, lightweight, high rigidity, and high temperature resistance.

[0038] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0039] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A conformal protective plate for an aircraft grille wing, characterized in that, include: The cabin (1), the protective plate (2), the grid wing (3), the countersunk screws (4), and the puller (5); The protective plate (2) has an L-shaped cross section. The short side of the protective plate (2) is inserted into the axial gap between the grille wing (3) and the cabin (1), and the long side is in contact with the exposed aerodynamic surface of the grille wing (3) to form the conformal surface of the grille wing (3). The short side of the protective plate (2) and the grille wing (3) share a pull pin (5) to be fastened to the cabin (1). The long side of the guard plate (2) is fastened to the grid wing (3) near the root by a countersunk screw (4).

2. The aircraft grille conformal guard plate according to claim 1, characterized in that, The root section of the protective plate (2) is a quarter-circular concave arc. During installation, the root of the protective plate (2) is embedded in the matching quarter-circular arc groove on the surface of the cabin (1).

3. The aircraft grille conformal guard (2) according to claim 1, characterized in that, The size of the guard plate (2) matches the size of the grille wing (3) and can just cover the grille wing (3).

4. The aircraft grille conformal guard (2) according to claim 1, characterized in that, The longitudinal section at the root of the guard plate (2) is a quarter-circular concave arc.

5. The aircraft grille conformal guard plate according to claim 1, characterized in that, The surface of the cabin (1) is provided with a quarter-circle groove that fits the root of the protective plate (2).

6. The aircraft grille conformal guard according to claim 1, characterized in that, The outer arc surface of the guard plate (2) is connected to the grille wing (3) by a countersunk screw (4).

7. The aircraft grille conformal guard (2) according to claim 1, characterized in that, The number of each of the pin puller (5) and the fastening countersunk screw (4) is one or more.

8. The aircraft grille conformal guard (2) according to claim 1, characterized in that, During the deployment of the grid wing (3), the countersunk screw (4) impacts the limiting block of the cabin (1), causing it to bend, break, and separate.

9. The aircraft grille conformal guard (2) according to claim 1, characterized in that, When the grille wing (3) reaches the deployment condition, the pin puller (5) is activated, the front constraints of the grille wing (3) and the guard plate (2) are released, and the grille wing (3) begins to deploy under the root torque.

10. The aircraft grille conformal guard (2) according to claim 1, characterized in that, When the grille wing (3) is folded, the protective plate (2) is fixed to the cabin (1); after the grille wing (3) is fully unfolded, the protective plate (2) separates from the cabin (1).

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