Composite material wing mounting structure of aerospace craft

Abstract

The utility model discloses a composite material wing mounting structure of an aerospace craft, which belongs to the technical field of flying wings, symmetrical mounting grooves are formed in the bottom of a wing body, symmetrical reinforcing bosses are arranged on the outer walls of the two sides of the wing body, and the reinforcing bosses are positioned on the two sides of the mounting grooves; symmetrical screw holes are formed in the reinforcing bosses, and grooves matched with the screw holes are formed in one set of reinforcing bosses. A bolt is installed in the screw hole, a nut is installed on the bolt in a threaded mode, the nut comprises a convex ring, and the convex ring is located in the groove; a limiting ring coaxial with the screw hole is further mounted on the outer wall of the reinforcing boss, a plurality of sets of mounting cavities are formed in the outer wall of the reinforcing boss, and a plurality of sets of locking blocks movably arranged in the mounting cavities are fixedly arranged at the bottom of the limiting ring. According to the composite material wing mounting structure for the aerospace craft, the wing body can be mounted at the tail part of a projectile body or an aircraft through the bolt and the nut, and the limiting ring can be quickly disassembled and assembled through the design of the mounting cavity and the locking block, so that the practicability of the composite material wing mounting structure for the aerospace craft is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of flight wings, in particular to a composite material wing mounting structure for aerospace vehicles. Background Art

[0002] The advent of spacecraft has expanded the scope of human activity from Earth's atmosphere into the vast expanse of outer space, ushering in a quantum leap in humanity's ability to understand and transform nature, and significantly impacting socioeconomic and social life. Spacecraft, operating beyond Earth's atmosphere, are free from atmospheric obstructions and can receive the full range of electromagnetic radiation from celestial bodies, opening up full-band astronomical observations. Spacecraft, traversing from near-Earth space to interplanetary space, have enabled direct detection of the space environment, as well as close-up observations and direct sampling of the Moon and major solar system planets. Artificial satellites, acting as space radio relay stations, have enabled global satellite communications and broadcasting, while serving as space reference points for global satellite navigation and geodetic surveying. Taking advantage of the unique environment of space, such as high vacuum, intense radiation, and weightlessness, spacecraft have enabled a variety of important scientific experiments and research.

[0003] Publication number CN117922816A discloses a flying wing structure and method for doubling lift, belonging to the technical field of flying wings for aircraft. The technical solution is: the upper wing channel and the lower wing duct are arranged vertically to form a duct box; the length of the upper wing channel is less than that of the lower wing duct, the upper wing channel and the lower wing duct are arranged flush with each other, the lower wing duct is provided with a lower air inlet at the head, and a closed structure at the tail, and the overall structure is a cylindrical structure; the upper wing channel is provided with an upper air inlet at the head, and an upper air outlet at the tail, forming an airflow channel. The beneficial effect of this invention is that an air flow channel is formed above the wing through the double-layer structure, which multiplies the air flow rate on the wing and generates negative pressure, thereby increasing the lift of the entire wing. The wing with this structure can be applied to all aerodynamic aircraft.

[0004] The flying wings in the above-mentioned comparative documents have average strength, a complicated installation process, and are time-consuming and labor-intensive. The degree of automation is average, and there is a lack of a quick locking structure. Therefore, a composite wing installation structure for a spacecraft is designed here to solve the above-mentioned problems. Utility Model Content

[0005] The purpose of the utility model is to provide a composite wing installation structure for aerospace vehicles in order to solve the problems of conventional flying wings, such as average strength, complicated installation process, time-consuming and labor-intensive installation, average degree of automation, and lack of a quick locking structure.

[0006] To achieve the above-mentioned purpose, the technical solution of the utility model is: a composite wing mounting structure for a spacecraft, including a wing body, a symmetrical mounting groove being provided at the bottom of the wing body, and symmetrical reinforcing bosses being provided on the outer walls on both sides of the wing body, and the reinforcing bosses are located on both sides of the mounting groove; symmetrical screw holes are provided on the reinforcing bosses, and one group of the reinforcing bosses is provided with grooves matching the screw holes; bolts are installed in the screw holes, and nuts are threadedly installed on the bolts, and the nuts include a convex ring, and the convex ring is located in the groove; a limiting ring coaxial with the screw hole is also installed on the outer wall of the reinforcing boss, and multiple groups of mounting cavities are provided on the outer wall of the reinforcing boss, and multiple groups of locking blocks movably arranged in the mounting cavity are fixedly provided on the bottom of the limiting ring.

[0007] As a further solution of the present invention: an extrusion cavity is opened on the inner walls of both sides of the installation groove, an extrusion block is movably arranged in the extrusion cavity, and the bottom of the extrusion block is connected to the inner wall of the extrusion cavity through multiple sets of reset springs.

[0008] As a further solution of the present invention: anti-slip grooves are provided on the outer wall of the extrusion block.

[0009] As a further solution of the present invention: the installation cavity includes a vertically arranged telescopic cavity, and a horizontally arranged locking cavity is opened on the side of the telescopic cavity; the locking block includes a vertical part and a horizontal part. When the limit ring is installed on the outer wall of the reinforcing boss, the horizontal part is locked in the locking cavity.

[0010] As a further solution of the present invention: the inner wall diameter of the limiting ring is smaller than that of the convex ring.

[0011] As a further solution of the present invention: the bolts and nuts are made of high-strength aviation metal materials.

[0012] As a further solution of the present invention: the wing body is streamlined as a whole, with the head being the widest and gradually shrinking to the tail, which is in a pointed shape.

[0013] The present invention provides an improved composite wing mounting structure for aerospace vehicles, which has the following improvements and advantages compared with the prior art:

[0014] The utility model can install the wing body to the tail of the projectile or aircraft through the bolts and nuts that cooperate with each other, and the limit ring can be quickly disassembled and assembled through the design of the installation cavity and the locking block, and the stability during locking can be improved through the design of the locking cavity and the horizontal part. The structure is simple and easy to maintain, which further improves the practicality of the composite wing installation structure of the aerospace vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be further explained below in conjunction with the accompanying drawings and Examples:

[0016] Figure 1 It is a three-dimensional structural diagram of the structure of the utility model;

[0017] Figure 2 This is a partial three-dimensional structural diagram of the wing body of the utility model;

[0018] Figure 3 It is a partial cross-sectional view of the wing body of the utility model;

[0019] Figure 4 yes Figure 3 A magnified view of the structure at point A;

[0020] Figure 5 It is a three-dimensional structural diagram of the bolt and nut in the utility model;

[0021] Figure 6 It is a three-dimensional structural diagram of the limiting ring in the utility model.

[0022] Description of reference numerals:

[0023] 1. Wing body; 2. Mounting groove; 3. Reinforcement boss; 4. Screw hole; 5. Groove; 6. Extrusion chamber; 7. Return spring; 8. Extrusion block; 9. Bolt; 10. Nut; 11. Raised ring; 12. Mounting chamber; 13. Telescopic chamber; 14. Locking chamber; 15. Limiting ring; 16. Locking block; 17. Vertical portion; 18. Horizontal portion; 19. Anti-slip groove. DETAILED DESCRIPTION

[0024] The following will be combined with the Figures 1 to 6 This utility model is described in detail, and the technical solutions in the embodiments of this utility model are clearly and completely described. Obviously, the embodiments described are only some of the embodiments of this utility model, not all of them. Based on the embodiments of this utility model, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this utility model.

[0025] The utility model provides an improved aerospace composite wing mounting structure, such as Figures 1-6As shown, the composite wing mounting structure of a spacecraft includes a wing body 1, a symmetrical mounting groove 2 is provided at the bottom of the wing body 1, and symmetrical reinforcing bosses 3 are provided on the outer walls on both sides of the wing body 1, and the reinforcing bosses 3 are located on both sides of the mounting groove 2; symmetrical screw holes 4 are provided on the reinforcing bosses 3, and one group of the reinforcing bosses 3 is provided with a groove 5 that cooperates with the screw hole 4; a bolt 9 is installed in the screw hole 4, and a nut 10 is threadedly installed on the bolt 9, and the nut 10 includes a convex ring 11, which is located in the groove 5; a limiting ring 15 coaxial with the screw hole 4 is also installed on the outer wall of the reinforcing boss 3, and multiple groups of mounting cavities 12 are provided on the outer wall of the reinforcing boss 3, and multiple groups of locking blocks 16 movably arranged in the mounting cavity 12 are fixedly provided on the bottom of the limiting ring 15; an extrusion cavity 6 is provided on the inner walls on both sides of the mounting groove 2, and an extrusion block 8 is movably provided in the extrusion cavity 6, and the bottom of the extrusion block 8 is connected to the inner wall of the extrusion cavity 6 through multiple groups of return springs 7.

[0026] The utility model can install the wing body 1 to the tail of the projectile or aircraft through the bolts 9 and nuts 10 that cooperate with each other, and the design of the installation cavity 12 and the locking block 16 can quickly disassemble and assemble the limit ring 15, and the design of the locking cavity 14 and the horizontal part 18 can improve the stability during locking. The structure is simple and easy to maintain, which further improves the practicality of the composite wing installation structure of the aerospace vehicle.

[0027] See attached Figure 2 , anti-slip grooves 19 are provided on the outer wall of the extrusion block 8.

[0028] In this embodiment, during installation, the plug plate at the tail of the aircraft or missile body is inserted into the installation slot 2. In order to further increase the friction during clamping and thus further improve stability, anti-slip grooves 19 are designed.

[0029] See attached Figure 3 -Attached Figure 6 The installation cavity 12 includes a vertically arranged telescopic cavity 13, and a horizontally arranged locking cavity 14 is opened on the side of the telescopic cavity 13; the locking block 16 includes a vertical portion 17 and a horizontal portion 18. When the limit ring 15 is installed on the outer wall of the reinforcing boss 3, the horizontal portion 18 is locked in the locking cavity 14.

[0030] In this embodiment, when disassembly is required, the limiting ring 15 is first rotated counterclockwise, and when the horizontal portion 18 is separated from the locking cavity 14 , the limiting ring 15 is pulled outward.

[0031] See attached Figure 1 and attached Figure 6 The inner wall diameter of the limiting ring 15 is smaller than that of the convex ring 11.

[0032] In this embodiment, in order to lock and limit the protruding ring 11 on the nut 10 through the limiting ring 15 to prevent the nut 10 from loosening, the inner wall diameter of the limiting ring 15 is smaller than that of the protruding ring 11.

[0033] See attached Figure 5 The bolt 9 and the nut 10 are made of high-strength aviation metal material.

[0034] In this embodiment, in order to further improve the strength and service life of the device, aviation metal materials are used.

[0035] The above description of the disclosed embodiments will enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A composite wing mounting structure for aerospace vehicle, characterized by: The invention comprises a wing body (1), wherein a symmetrical mounting groove (2) is provided at the bottom of the wing body (1), and symmetrical reinforcing bosses (3) are provided on the outer walls of both sides of the wing body (1), and the reinforcing bosses (3) are located on both sides of the mounting groove (2); symmetrical screw holes (4) are provided on the reinforcing bosses (3), wherein a group of the reinforcing bosses (3) is provided with grooves (5) matching with the screw holes (4); bolts (9) are installed in the screw holes (4), and the bolts (9) A nut (10) is threadedly mounted on the nut (10), the nut (10) including a convex ring (11), the convex ring (11) being located in the groove (5); a limiting ring (15) coaxial with the screw hole (4) is also mounted on the outer wall of the reinforcing boss (3), a plurality of mounting cavities (12) are provided on the outer wall of the reinforcing boss (3), and a plurality of locking blocks (16) movably arranged in the mounting cavities (12) are fixedly mounted on the bottom of the limiting ring (15).

2. The aerospace vehicle composite wing mounting structure according to claim 1, characterized in that: An extrusion cavity (6) is provided on the inner walls of both sides of the installation groove (2), an extrusion block (8) is movably provided in the extrusion cavity (6), and the bottom of the extrusion block (8) is connected to the inner wall of the extrusion cavity (6) through multiple groups of return springs (7).

3. The aerospace vehicle composite wing mounting structure according to claim 2, characterized in that: Anti-slip grooves (19) are provided on the outer wall of the extrusion block (8).

4. The aerospace vehicle composite wing mounting structure according to claim 1, characterized in that: The installation cavity (12) includes a vertically arranged telescopic cavity (13), and a horizontally arranged locking cavity (14) is opened on the side of the telescopic cavity (13); the locking block (16) includes a vertical portion (17) and a horizontal portion (18); when the limiting ring (15) is installed on the outer wall of the reinforcing boss (3), the horizontal portion (18) is locked in the locking cavity (14).

5. The aerospace vehicle composite wing mounting structure according to claim 1, characterized in that: The inner wall diameter of the limiting ring (15) is smaller than that of the convex ring (11).

6. The aerospace vehicle composite wing mounting structure according to claim 1, characterized in that: The bolt (9) and nut (10) are made of high-strength aviation metal material.

7. The aerospace vehicle composite wing mounting structure according to claim 1, characterized in that: The wing body (1) is streamlined as a whole, with the widest part at the head and gradually shrinking to the tail, which is in a pointed shape.

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