Gliding air-drop box

Abstract

The utility model relates to a kind of gliding air-drop box, comprising: head component;Cargo box assembly, the front end of cargo box assembly is connected with head component;Main wing, main wing is foldablely connected to the upper portion of cargo box assembly;Tail component, including tail wing installation part and tail wing structure, tail wing installation part is connected to the rear end of cargo box assembly, tail wing structure is installed on tail wing installation part, tail wing structure has two vertically foldable vertical tail wings.Tail wing structure further includes horizontal tail and tail wing folding structure;The upper surface of tail wing installation part is provided with horizontal tail, the both sides of horizontal tail are foldably connected to vertical tail wing by tail wing folding structure, two vertical tail wings adopt left-right symmetrical layout, and after unfolding, it is V-shaped.Its beneficial effect is, the gliding air-drop box of the utility model, since tail component uses the above foldable structure, so that it can fold tail wing in hanging state, reduce the space occupied.

Description

Technical Field

[0001] This utility model relates to the field of gliding airdrop technology, and in particular to a gliding airdrop box. Background Technology

[0002] The gliding drop box is a special packaging box adapted to the gliding drop system. Its core function is to achieve safe protection, accurate positioning and stable landing of materials during unpowered gliding drop. It has the dual attributes of "gliding carrier adaptability" and "material protection", which is different from the single protective box of traditional vertical airdrop or parachute airdrop.

[0003] Chinese patent document CN219339735U discloses a gliding airdrop drone, including a head assembly, fuselage, wings, and tail. The head assembly is conical, the fuselage is cuboid, and the tail includes a conical shape and two vertical ailerons. The head assembly is connected to the fuselage, and the fuselage is connected to the tail. The fuselage includes an upper box and a lower box. The upper box contains two pairs of wings that can be folded inside. The wings are arranged in a tandem configuration, with the two pairs of wings staggered vertically when unfolded. The front wing has an upward dihedral. The lower box is a transport box lined with a honeycomb structure.

[0004] The gliding airdrop drone has the following defects and shortcomings: The tail fin of the gliding airdrop drone is an H-shaped tail fin, which is fixed and cannot be folded. Therefore, it will occupy more space when the carrier is mounted, transported and stored, which directly leads to a reduction in the number of items that the carrier can load at one time.

[0005] Therefore, there is an urgent need to provide a new type of gliding drop container with a more compact structure. Utility Model Content

[0006] (a) Technical problems to be solved

[0007] In view of the above-mentioned shortcomings and deficiencies of the prior art, this utility model provides a gliding airdrop box, which solves the technical problem of wasted space caused by the fixed and non-foldable H-shaped tail fin of the existing gliding airdrop drone.

[0008] (II) Technical Solution

[0009] To achieve the above objectives, the main technical solutions adopted by this utility model include:

[0010] This utility model embodiment provides a gliding airdrop box, comprising:

[0011] Header component;

[0012] Cargo box assembly, the front end of which is connected to the head assembly;

[0013] The main wing can be folded forward and backward and connected to the upper part of the cargo box assembly;

[0014] The rear assembly includes a tail wing mount and a tail wing structure. The tail wing mount is connected to the rear end of the cargo box assembly, and the tail wing structure is mounted on the tail wing mount. The tail wing structure has two vertically foldable tail fins.

[0015] Optionally, the tail fin structure further includes a horizontal tail fin and a tail fin folding structure;

[0016] The horizontal tail fin is provided on the upper surface of the tail fin mounting part. The two sides of the horizontal tail fin are foldably connected to the vertical tail fin through the tail fin folding structure. The two vertical tail fins are arranged symmetrically from left to right and form a V shape when unfolded.

[0017] Optionally, the tail fin folding mechanism includes a first pivot and a first torsion spring;

[0018] A main beam limiting step is provided on both sides of the horizontal tail fin, and a first ear plate is connected to the main beam limiting step;

[0019] A vertical tail limiting step is provided on the side of the vertical tail fin near the horizontal tail fin, and a second lug is connected to the vertical tail limiting step.

[0020] The first ear plate and the second ear plate are hinged together by the first pivot. The first torsion spring is sleeved around the first pivot. One end of the first torsion spring is connected to the main beam limiting step, and the other end is connected to the vertical tail limiting step. It is configured to drive the vertical tail wing to rotate from the folded position to the unfolded position.

[0021] Optionally, a main wing folding mechanism is provided between the main wing and the cargo box assembly, the main wing folding mechanism including a second pivot, a pivot cover and a second torsion spring;

[0022] One end of the second rotating shaft is fixedly mounted on the cargo box assembly, and the end of the main wing is provided with a wing support unit. The wing support unit has a through hole, through which the second rotating shaft passes. The other end of the second rotating shaft is detachably mounted with the rotating shaft cover.

[0023] The second torsion spring is provided between the inner wall of the through hole of the wing support unit and the second rotating shaft. One end of the second torsion spring is connected to the second rotating shaft, and the other end is connected to the wing support unit, configured to drive the main wing to rotate from the folded position to the unfolded position.

[0024] Optionally, it may also include a first electronic lock and a second electronic lock;

[0025] The tail fin mounting part is provided with the first electronic lock, the output end of the first electronic lock is connected to the first ball head locking pin, the vertical tail fin is provided with the first locking hole, and the first ball head locking pin cooperates with the first locking hole to lock the vertical tail fin in the folded position.

[0026] The cargo box assembly is provided with a second electronic lock, which is connected to a second ball-head locking pin. The main wing is provided with a second locking hole, and the second ball-head locking pin cooperates with the second locking hole to lock the main wing in the folded position.

[0027] Optionally, the main wing, the horizontal tail, and the vertical tail each include two main spars, multiple ribs, and skin;

[0028] The two main beams are arranged in parallel and a plurality of ribs are spaced apart along the axial direction, and the outer surface of the plurality of ribs is covered with the skin.

[0029] Optionally, it may also include airborne equipment;

[0030] The head assembly is integrally molded from composite material and is internally divided into at least three layers for housing the airborne equipment, which includes at least one of a radio beacon receiver, a barometer, and a photoelectric detection device.

[0031] Optionally, the cargo box assembly can be disassembled into a front compartment, a middle compartment, and a rear compartment, with reinforcing ribs spaced at intervals of 250-350 mm on each compartment.

[0032] Optionally, the upper surface of the cargo box assembly is provided with a pair of lifting lugs for mounting to the carrier aircraft.

[0033] (III) Beneficial Effects

[0034] The beneficial effects of this utility model are as follows: The gliding airdrop container of this utility model includes a head assembly, a cargo box assembly, a main wing, and a tail assembly. The front end of the cargo box assembly is connected to the head assembly; the main wing is foldable and connected to the upper part of the cargo box assembly; the tail assembly includes a tail wing mounting part and a tail wing structure. The tail wing mounting part is connected to the rear end of the cargo box assembly, and the tail wing structure is mounted on the tail wing mounting part, including two vertically foldable tail wing sections. Compared with existing gliding airdrop drones, the gliding airdrop container of this utility model, by adopting a foldable tail assembly structure (including two vertically foldable tail wing sections), allows the tail wing to be retracted during loading, transportation, and storage, significantly reducing the overall space occupied. This design effectively solves the space waste problem caused by the fixed and non-foldable H-shaped tail wing in the prior art, thereby increasing the number of items that can be loaded at one time and optimizing transportation and storage efficiency. Furthermore, this folding structure facilitates rapid deployment, further enhancing the practicality and adaptability of the gliding airdrop container. Attached Figure Description

[0035] Figure 1 This is a perspective view of Embodiment 1 of the gliding airdrop box of this utility model, wherein the wings of the gliding airdrop box are in a folded position;

[0036] Figure 2 This is another perspective view of Embodiment 1 of the gliding airdrop box of this utility model, wherein the wings of the gliding airdrop box are in the deployed position;

[0037] Figure 3 This is a schematic diagram of the internal structure of the head assembly of Embodiment 1 of the gliding airdrop box of this utility model;

[0038] Figure 4 This is a side view of Embodiment 1 of the gliding airdrop container of the present invention, showing the internal structure of the container assembly;

[0039] Figure 5 This is a three-dimensional schematic diagram of the tail fin structure of Embodiment 1 of the gliding airdrop box of this utility model;

[0040] Figure 6 for Figure 5 An enlarged schematic diagram of the connection between the horizontal tail and the vertical tail;

[0041] Figure 7 This is a cross-sectional view of the main wing folding mechanism in Embodiment 1 of the gliding airdrop box of this utility model;

[0042] Figure 8 This is a perspective view of the main wing of Embodiment 1 of the gliding airdrop container of this utility model;

[0043] Figure 9 This is a schematic diagram of the rotation limiting component of Embodiment 1 of the gliding airdrop box of this utility model.

[0044] [Explanation of Labels in the Attached Image]

[0045] 1: Head assembly; 2: Cargo box assembly; 3: Tail assembly; 4: Main wing; 5: Horizontal tail; 6: Vertical tail; 7: First pivot; 8: First torsion spring; 9: Main beam limiting step; 10: First lug; 11: Vertical tail limiting step; 12: Second lug; 13: Second pivot; 14: Pivot cover; 15: Second torsion spring; 16: Main beam; 17: Wing rib; 18: Skin; 19: Onboard equipment; 20: Reinforcing rib; 21: Lifting lug; 22: Tail wing mounting part; 23: Main wing folding mechanism; 24: Wing support unit; 25: Rotation limiting protrusion; 26: Abutment limiting component. Detailed Implementation

[0046] To better explain and facilitate understanding of this utility model, a detailed description of its specific embodiments is provided below with reference to the accompanying drawings. In this document, directional terms such as "upper," "lower," "left," "right," "front," and "rear" are used interchangeably with other directional terms. Figure 1 The orientation is used as a reference.

[0047] Example 1:

[0048] Reference Figures 1 to 8 This embodiment provides a gliding airdrop container, including a head assembly 1, a cargo container assembly 2, a main wing 4, and a tail assembly 3. The head assembly 1 is connected to the front end of the cargo container assembly 2, the main wing 4 is foldable to the upper part of the cargo container assembly 2 via a main wing folding mechanism 23, and the tail assembly 3 is connected to the rear end of the cargo container assembly 2.

[0049] like Figure 1 and Figure 3 As shown, the front end of the head assembly 1 is a streamlined head cone to optimize its aerodynamic shape, and a landing buffer device is provided at the bottom of the head assembly 1. Figure 1 (Not shown), the head assembly 1 houses the carrier device 19.

[0050] See Figure 4 In this embodiment, the cargo box assembly 2 can be disassembled into a front compartment, a middle compartment, and a rear compartment. Each compartment is provided with reinforcing ribs 20 at intervals to increase the structural strength of the cargo box assembly 2. Preferably, the interval between two adjacent reinforcing ribs 20 is 250-350 mm. In addition, a pair of lifting lugs 21 are provided on the upper surface of the cargo box assembly 2. The diameter of the lifting lugs 21 is 20-25 mm for mounting to the carrier aircraft.

[0051] Furthermore, the cargo box assembly 2 is equipped with two pairs of foldable front and rear main wings 4, and the two pairs of main wings 4 are arranged in an alternating vertical arrangement after being unfolded.

[0052] Combination Figure 4 , Figure 5 and Figure 6 As shown, the tail assembly 3 of this embodiment includes a tail wing mounting part 22 and a tail wing structure. The tail wing mounting part 22 is connected to the rear end of the cargo box assembly 2, and the tail wing structure is mounted on the tail wing mounting part 22.

[0053] Specifically, the tail fin structure of this embodiment includes a horizontal tail fin 5, two vertically foldable vertical tail fins 6, and a tail fin folding structure.

[0054] A horizontal tail fin 5 is provided on the upper surface of the tail fin mounting part 22. The two sides of the horizontal tail fin 5 are foldably connected to the vertical tail fin 6 through the tail fin folding structure. The two vertical tail fins 6 are arranged symmetrically from left to right and form a V shape when unfolded.

[0055] The tail fin folding mechanism includes a first pivot 7 and a first torsion spring 8. A main beam limiting step 9 is provided on both sides of the horizontal tail fin 5, and a first ear plate 10 is connected to the main beam limiting step 9. A vertical tail limiting step 11 is provided on the side of the vertical tail fin 6 near the horizontal tail fin 5, and a second ear plate 12 is connected to the vertical tail limiting step 11. The first ear plate 10 and the second ear plate 12 are hinged together by the first pivot 7. A first torsion spring 8 is sleeved around the first pivot 7. One end of the first torsion spring 8 is connected to the main beam limiting step 9, and the other end is connected to the vertical tail limiting step 11, configured to drive the vertical tail fin 6 to rotate from the folded position to the unfolded position.

[0056] Preferably, a retaining ring (not shown in the figure) is provided at the end of the first rotating shaft 7 to restrict the axial movement of the first rotating shaft 7.

[0057] It should be noted that the main beam limiting step 9 and the tail fin limiting step 11 work together to limit the rotation angle of the tail fin 6. Specifically, when the tail fin 6 rotates to the folded position, the end face of the tail fin limiting step 11 abuts against the lower surface of the main beam limiting step 9. When the tail fin 6 rotates to the unfolded position, the end face of the tail fin limiting step 11 abuts against the upper edge of the end face of the main beam limiting step 9.

[0058] Preferably, when the vertical tail fin 6 is rotated to the deployed position, the angle between the vertical tail fin 6 and the horizontal plane is 55-70 degrees.

[0059] See Figure 7 The main wing folding mechanism 23 of this embodiment includes a second rotating shaft 13, a rotating shaft cover 14, and a second torsion spring 15. One end of the second rotating shaft 13 is fixedly mounted on the cargo box assembly 2. A wing support unit 24 is provided at the end of the main wing 4. A through hole is provided on the wing support unit 24, through which the second rotating shaft 13 passes. The rotating shaft cover 14 is detachably mounted on the other end of the second rotating shaft 13. A second torsion spring 15 is provided between the inner wall of the through hole of the wing support unit 24 and the second rotating shaft 13. One end of the second torsion spring 15 is connected to the second rotating shaft 13, and the other end is connected to the wing support unit 24. It is configured to drive the main wing 4 to rotate from the folded position to the unfolded position.

[0060] Specifically, the second shaft 13 has a first shaft section and a second shaft section with a diameter larger than the first shaft section. The second shaft section can be fixedly connected to the cargo box assembly 2 by bolts. A second torsion spring 15 and a wing support unit 24 are sleeved around the first shaft section. The shaft cover 14 is a fixing bolt. A threaded hole is opened on the end face of the first shaft section. The shaft cover 14 is screwed into the threaded hole to restrict the axial movement of the wing support unit 24.

[0061] It should be noted that a rotation limiting component can be provided between the main wing folding mechanism 23 and the wing support unit 24. This rotation limiting component is used to limit the rotation angle of the main wing 4.

[0062] Combination Figure 9 As shown, the rotation limiting assembly of this embodiment includes a rotation limiting protrusion 25 and two abutting limiting components 26. Two abutting limiting components 26 are provided on the circumferential surface of the second shaft segment of the second rotating shaft 13, and a rotation limiting protrusion 25 is provided on the side of the wing support unit 24 facing the second shaft segment. The rotation limiting protrusion 25 cooperates with the two abutting limiting components 26 to limit the rotation angle of the main wing 4.

[0063] The working principle of the rotation limiting component is as follows: The rotation limiting protrusion 25 has two extreme positions: when the wing support unit 24 drives the rotation limiting protrusion 25 to rotate and contact one of the abutting limiting components 26, the rotation limiting protrusion 25 is at the first extreme position, at which time the main wing 4 is in the folded position; when the wing support unit 24 drives the rotation limiting protrusion 25 to rotate and contact the other abutting limiting component 26, the rotation limiting protrusion 25 is at the second extreme position, at which time the main wing 4 is in the unfolded position. This embodiment limits the rotation angle of the main wing 4 by setting two extreme positions when the rotation limiting protrusion 25 on the wing support unit 24 abuts against the edges of the two abutting limiting components 26.

[0064] The gliding drop container in this embodiment also includes a first electronic lock and a second electronic lock. The first electronic lock is mounted on the tail fin mounting portion 22, and its output end is connected to a first ball-head locking pin. A first locking hole is provided on the vertical tail fin 6, and the first ball-head locking pin engages with the first locking hole to lock the vertical tail fin 6 in the folded position. The second electronic lock is mounted on the cargo container assembly 2, and its second electronic lock is connected to a second ball-head locking pin. A second locking hole is provided on the main wing 4, and the second ball-head locking pin engages with the second locking hole to lock the main wing 4 in the folded position.

[0065] It should be noted that the electronic lock and ball-head locking pin are existing devices already circulating in the market. The working process of the electronic lock and ball-head locking pin is as follows:

[0066] 1. Vertical tail fin 6 locking: A first electronic lock is installed on the tail fin mounting part 22. The output end of the first electronic lock is connected to a first ball-head locking pin. The end of the first ball-head locking pin is provided with a radial spring and a retractable steel ball (standard part). When the vertical tail fin 6 is folded, the first ball-head locking pin is inserted into the preset locking hole, and the spring pushes the steel ball to extend and achieve fixation.

[0067] 2. Main Wing 4 Locking: The cargo box assembly 2 is equipped with a second electronic lock. The output end of the second electronic lock is connected to a second ball-head locking pin. The end of the second ball-head locking pin is equipped with a radial spring and a retractable steel ball (standard part). When the main wing 4 is folded, the second ball-head locking pin is inserted into the preset locking hole, and the spring pushes the steel ball out to achieve fixation.

[0068] 3. Unlocking process: The first electronic lock drives the first ball joint locking pin to retract, the second electronic lock drives the second ball joint locking pin to retract, and the torsion spring drives the main wing 4 / vertical tail wing 6 to deploy instantly.

[0069] Please see Figure 8 In this embodiment, the main wing 4 includes two main beams 16, multiple wing ribs 17, and a skin 18. The two main beams 16 are arranged in parallel, and multiple wing ribs 17 are spaced apart along the axial direction. The outer surface of the multiple wing ribs 17 is covered with a skin 18.

[0070] Preferably, the main beam 16 is a carbon fiber tube, the wing rib 17 is cut from an epoxy resin plate with a thickness of 4-6 mm, and the skin 18 is made of composite material pressed together under high temperature and pressure.

[0071] In addition, it should be noted that the specific structures of the horizontal tail 5 and the vertical tail 6 are the same as those of the main wing 4, and will not be described again here.

[0072] The working process of the gliding airdrop container in this embodiment is as follows: during mounting ( Figure 1 The main wing 4 folds inward toward the cargo box assembly 2, and the vertical tail wing 6 folds downward and is locked by an electronic lock, reducing the overall width by about 40%. After airdrop, the electronic lock is released, and the first torsion spring 8 and the second torsion spring 15 respectively drive the vertical tail wing 6 to flip upward and the main wing 4 to unfold outward. Figure 2 This allows for the formation of a stable gliding body.

[0073] Example 2:

[0074] This embodiment provides another gliding airdrop container. Unlike embodiment 1, the gliding airdrop container in this embodiment also includes a control device, which is electrically connected to the first electronic lock, the second electronic lock, and the onboard equipment 19.

[0075] Specifically, the airborne equipment 19 in this embodiment includes a radio beacon receiver, a barometer, and a photoelectric detection device. The head assembly 1 is integrally molded from a composite material, and its interior is divided into three independent chambers by partitions, each housing the radio beacon receiver, barometer, and photoelectric detection device. The radio beacon receiver is used to receive ground signals and perform positioning, the barometer is used to monitor flight altitude, and the photoelectric detection device is used for obstacle detection.

[0076] It should be noted that the innovation of this embodiment lies in the integrated innovation of the mechanical system. The supporting electrical circuit structure and control structure that enable its overall normal function are common knowledge. The control device, radio beacon receiving device, barometer and photoelectric detection device are also existing products that are already circulating in the market (that is, basic standard components widely used in this field). Their specific structure and working principle are also common knowledge in this field, so they will not be described in detail here.

[0077] The remaining parts that are the same as in Example 1 will not be repeated here.

[0078] In the description of this utility model, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0079] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0080] In this utility model, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "beneath" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0081] In the description of this specification, the terms "one embodiment," "some embodiments," "embodiment," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0082] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make modifications, alterations, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A gliding airdrop container, characterized in that: include: Header component (1); Cargo box assembly (2), the front end of which is connected to head assembly (1); Main wing (4), which can be folded forward and backward and connected to the upper part of the cargo box assembly (2); The tail assembly (3) includes a tail wing mounting part (22) and a tail wing structure. The tail wing mounting part (22) is connected to the rear end of the cargo box assembly (2). The tail wing structure is mounted on the tail wing mounting part (22) and has two vertically foldable tail wings (6).

2. The gliding drop container as described in claim 1, characterized in that: The tail fin structure also includes a horizontal tail fin (5) and a tail fin folding structure; The horizontal tail fin (5) is provided on the upper surface of the tail fin mounting part (22). The two sides of the horizontal tail fin (5) are foldably connected to the vertical tail fin (6) through the tail fin folding structure. The two vertical tail fins (6) are arranged symmetrically from left to right and form a V shape after unfolding.

3. The gliding drop container as described in claim 2, characterized in that: The tail wing folding mechanism includes a first pivot (7) and a first torsion spring (8). A main beam limiting step (9) is provided on both sides of the horizontal tail fin (5), and a first ear plate (10) is connected to the main beam limiting step (9). The vertical tail fin (6) is provided with a vertical tail limiting step (11) on the side near the horizontal tail fin (5), and a second ear plate (12) is connected to the vertical tail limiting step (11). The first ear plate (10) and the second ear plate (12) are hinged together by the first pivot (7). The first torsion spring (8) is sleeved around the first pivot (7). One end of the first torsion spring (8) is connected to the main beam limiting step (9), and the other end is connected to the tail limiting step (11). It is configured to drive the tail wing (6) to rotate from the folded position to the unfolded position.

4. The gliding drop container as described in claim 3, characterized in that: A main wing folding mechanism (23) is provided between the main wing (4) and the cargo box assembly (2). The main wing folding mechanism (23) includes a second pivot (13), a pivot cover (14), and a second torsion spring (15). One end of the second rotating shaft (13) is fixedly mounted on the cargo box assembly (2), and the end of the main wing (4) is provided with a wing support unit (24). The wing support unit (24) has a through hole, through which the second rotating shaft (13) passes. The other end of the second rotating shaft (13) is detachably mounted with the rotating shaft cover (14). The second torsion spring (15) is provided between the inner wall of the through hole of the wing support unit (24) and the second rotating shaft (13). One end of the second torsion spring (15) is connected to the second rotating shaft (13), and the other end is connected to the wing support unit (24), configured to drive the main wing (4) to rotate from the folded position to the unfolded position.

5. The gliding drop container as described in claim 3, characterized in that: It also includes a first electronic lock and a second electronic lock; The tail wing mounting part (22) is provided with the first electronic lock, the output end of the first electronic lock is connected to the first ball head locking pin, the vertical tail wing (6) is provided with the first locking hole, the first ball head locking pin cooperates with the first locking hole to lock the vertical tail wing (6) in the folded position; The cargo box assembly (2) is provided with a second electronic lock, which is connected to a second ball-head locking pin. The main wing (4) is provided with a second locking hole, and the second ball-head locking pin cooperates with the second locking hole to lock the main wing (4) in the folded position.

6. The gliding drop container as described in claim 3, characterized in that: The main wing (4), the horizontal tail (5) and the vertical tail (6) each include two main spars (16), multiple wing ribs (17) and skin (18). The two main beams (16) are arranged in parallel and a plurality of ribs (17) are spaced apart along the axial direction. The outer surface of the plurality of ribs (17) is covered with the skin (18).

7. The gliding drop container as described in any one of claims 1-6, characterized in that: It also includes airborne equipment (19); the head assembly (1) is integrally molded from composite material and is internally divided into at least three layers for housing the airborne equipment (19), the airborne equipment (19) including at least one of a radio beacon receiver, a barometer and a photoelectric detection device.

8. The gliding drop container as described in any one of claims 1-6, characterized in that: The cargo box assembly (2) can be disassembled into a front compartment, a middle compartment and a rear compartment, and each compartment is provided with reinforcing ribs (20) spaced apart, with the reinforcing ribs (20) spaced 250-350 mm apart.

9. The gliding drop container as described in any one of claims 1-6, characterized in that: The upper surface of the cargo box assembly (2) is provided with a pair of lifting lugs (21) for mounting to the carrier aircraft.

Images