A rotatable outboard door retraction structure in a fixed-wing aircraft landing gear

Abstract

The utility model discloses a fixed wing aircraft landing gear rotatable outer cabin door retraction structure, including aircraft main part, the aircraft main part bottom end is provided with the symmetrical setting storage groove, one side of storage groove is equipped with rotatable inner cabin door, rotatable inner cabin door is connected with aircraft main part through rotatable inner cabin door fixed part, be equipped with the retractable landing gear in storage groove, retractable landing gear bottom end is equipped with the damping wheel axle. Advantageous effects: through landing gear, rotatable inner cabin door, rotatable outer cabin door, spring, adjusting steel wire, rotatable inner cabin door fixed part and rotatable outer cabin door spare etc. constitute a whole set of landing gear / rotatable outer cabin door retraction structure, convenient to assemble, and the structure cost is low, when the rotatable inner cabin door, rotatable outer cabin door and linkage mechanism are carried out to the collection of the gyro wheel, rotatable inner cabin door and rotatable outer cabin door can drive the rotation of rotatable inner cabin door and rotatable outer cabin door simultaneously and enclose the storage groove to the gyro wheel and carry out better shielding.

Description

Technical Field

[0001] This utility model relates to the field of fixed-wing aircraft technology, specifically to a retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft. Background Technology

[0002] In fixed-wing aircraft design, the reliable retraction and effective shielding of landing gear doors are crucial. Existing conventional landing gear door retraction structures generally suffer from the following significant drawbacks:

[0003] 1. Incomplete shielding: After the landing gear and tires are fully retracted into the fuselage, conventional door structures often cannot provide complete and tight coverage, leaving some structures (such as landing gear struts or tire sides) exposed to external airflow. This increases flight drag and affects aerodynamic efficiency.

[0004] 2. High cost and complexity: To achieve more complex door movement trajectories (such as the coordinated movement of inner and outer doors to achieve complete shielding), the industry typically relies on independent servo drive systems. While this solution achieves the functionality, it significantly increases the system's manufacturing cost, structural weight, control complexity, and maintenance difficulty.

[0005] 3. Adaptability limitations: Existing servo-driven solutions or single-structure designs for cabin doors have relatively fixed geometric configurations and motion trajectories, making it difficult to flexibly adapt to the different airframe space layouts and landing gear retraction angle requirements of different fixed-wing aircraft models, resulting in insufficient versatility and scalability.

[0006] Therefore, there is an urgent need to develop a new landing gear door retraction structure that can effectively solve the problem of complete door obstruction in a simpler, more reliable and lower cost way, while having good compatibility and scalability to meet the needs of diverse flight platforms.

[0007] No effective solutions have yet been proposed to address the problems in the relevant technologies. Utility Model Content

[0008] In view of the problems in the related technologies, this utility model proposes a retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft, so as to overcome the above-mentioned technical problems existing in the existing related technologies.

[0009] Therefore, the specific technical solution adopted by this utility model is as follows:

[0010] A retractable outer door structure for a fixed-wing aircraft landing gear includes an aircraft body. Symmetrically arranged storage slots are provided at the bottom of the aircraft body. A rotatable inner door is provided on one side of each storage slot. The rotatable inner door is connected to the aircraft body via a rotatable inner door fastener. A retractable landing gear is provided in the storage slot. A shock-absorbing wheel axle is provided at the bottom of the retractable landing gear, and a roller is provided at the bottom of the shock-absorbing wheel axle. A rotatable outer door is provided on the side of the storage slot away from the rotatable inner door. The rotatable outer door is connected to the aircraft body via a rotatable outer door fastener. A linkage rotation mechanism matching the rotatable outer door is provided in the storage slot.

[0011] Preferably, the shock-absorbing wheel axle is connected to the rotatable inner door via a spring.

[0012] Preferably, the linkage rotation mechanism includes an adjustable gear set provided in the storage slot, a rotating pressure rod provided on one side of the shaft end of the adjustable gear set, and a rotating pull rod provided at the end of the adjustable gear set away from the rotating pressure rod. The rotating pull rod is connected to the rotatable outer hatch through an adjusting steel wire.

[0013] Preferably, the rotatable outer hatch is connected to the rotating pull rod via a second spring.

[0014] Preferably, a main wing cover is provided in the storage slot on the side near the rotatable outer hatch. The advantages of this invention are: by assembling the landing gear, rotatable inner hatch, rotatable outer hatch, spring, adjusting wire, rotatable inner hatch internal fixing components, and rotatable outer hatch fasteners into a complete landing gear inner / rotatable outer hatch retraction structure, assembly is convenient and the structural cost is low. When the rollers are retracted, the rotatable inner hatch, rotatable outer hatch, and linkage mechanism simultaneously rotate the rotatable inner hatch and rotatable outer hatch, sealing the storage slot and providing good shielding for the rollers. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the overall structure of a retractable external hatch structure inside the landing gear of a fixed-wing aircraft according to an embodiment of the present utility model.

[0017] Figure 2 yes Figure 1A magnified view of a portion of point A in the middle;

[0018] Figure 3 This is a diagram illustrating the retraction and extension process of a rotatable outer hatch retraction and extension structure for the landing gear of a fixed-wing aircraft according to an embodiment of the present invention.

[0019] In the picture:

[0020] 1. Aircraft body; 2. Storage compartment; 3. Rotatable inner door; 4. Landing gear retraction and extension; 5. Shock-absorbing wheel axle; 6. Rotatable outer door; 7. Roller; 8. Rotatable inner door fastener; 9. Rotatable outer door fastener; 10. Adjustable gear set; 11. Rotating pressure rod; 12. Rotating pull rod; 13. Adjusting wire; 14. Main wing cover. Detailed Implementation

[0021] To further illustrate the various embodiments, the present invention provides accompanying drawings, which are part of the disclosure of the present invention. These drawings are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.

[0022] According to an embodiment of the present invention, a retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft is provided.

[0023] Example 1;

[0024] like Figure 1-3 As shown, the fixed-wing aircraft landing gear retraction structure according to an embodiment of the present invention includes an aircraft body 1. The aircraft body 1 has symmetrically arranged storage slots 2 at its bottom end. A rotatable inner door 3 is provided on one side of the storage slot 2. The rotatable inner door 3 is connected to the aircraft body 1 through a rotatable inner door fixing member 8. A retraction landing gear 4 is provided in the storage slot 2. A shock-absorbing wheel axle 5 is provided at the bottom end of the retraction landing gear 4. A roller 7 is provided at the bottom end of the shock-absorbing wheel axle 5. A rotatable outer door 6 is provided on the side of the storage slot 2 away from the rotatable inner door 3. The rotatable outer door 6 is connected to the aircraft body 1 through a rotatable outer door fixing member 9. A linkage rotation mechanism matching the rotatable outer door 6 is provided in the storage slot 2.

[0025] Example 2;

[0026] like Figure 1-3As shown, the aircraft includes a main body 1. Symmetrically arranged storage slots 2 are located at the bottom of the main body 1. A rotatable inner door 3 is located on one side of each storage slot 2. The rotatable inner door 3 is connected to the main body 1 via a rotatable inner door fastener 8. A retractable landing gear 4 is located within the storage slot 2. A shock-absorbing wheel axle 5 is located at the bottom of the retractable landing gear 4, and a roller 7 is located at the bottom of the shock-absorbing wheel axle 5. A rotatable outer door 6 is located on the side of the storage slot 2 away from the rotatable inner door 3. The rotatable outer door 6 is connected to the main body 1 via a rotatable outer door fastener 9. A linkage rotation mechanism matching the rotatable outer door 6 is located within the storage slot 2. The shock-absorbing wheel axle 5 is connected to the rotatable inner door 3 via a spring. The linkage rotation mechanism includes an adjustable gear set 10 disposed in the storage slot 2. A rotating pressure rod 11 is provided at one end of the shaft of the adjustable gear set 10, and a rotating pull rod 12 is provided at the end of the adjustable gear set 10 away from the rotating pressure rod 11. The rotating pull rod 12 is connected to the rotatable outer hatch 6 via an adjusting steel wire 13. The rotatable outer hatch 6 is connected to the rotating pull rod 12 via a spring. A main wing cover plate 14 is provided in the storage slot 2 on the side closest to the rotatable outer hatch 6.

[0027] In practical application, when the landing gear 4 retracts into the main wing: First, the landing gear 4 drives the shock absorber axle 5 to rotate, and the shock absorber axle 5 pulls the rotatable inner door 3 downwards via a spring; Second, during the retraction process, the landing gear 4 drives the roller 7 to rotate into the storage slot 2 via the shock absorber axle 5, at which time the roller 7 presses against the rotating pressure rod 11; Third, the rotating pressure rod 11, under pressure, drives the rotating pull rod 12 to rotate via the adjustable gear set 10; Fourth, when the rotating pull rod 12 rotates, it pulls the rotatable outer door 6 back into the storage slot 2 via the adjusting steel cable 13. The landing gear, rotating inner hatch, rotating outer hatch, spring, adjusting wire, rotating inner hatch fastener, and rotating outer hatch fastener are assembled into a complete landing gear inner / rotating outer hatch retraction structure. It is easy to assemble and has a low structural cost. When the rollers are retracted, the rotating inner hatch, rotating outer hatch, and linkage mechanism can simultaneously drive the rotating inner hatch and rotating outer hatch to rotate, sealing the storage slot and providing good protection for the rollers. In summary, by utilizing the above-mentioned technical solution of this utility model, a complete landing gear inner / rotatable outer door retraction structure is formed by assembling the landing gear, rotatable inner door, rotatable outer door, spring, adjusting steel wire, rotatable inner door fixing parts, and rotatable outer door fasteners. This structure is easy to assemble and has low structural cost. When the rollers are retracted, the rotatable inner door, rotatable outer door, and linkage mechanism can simultaneously drive the rotatable inner door and rotatable outer door to rotate, sealing the storage slot and providing good shielding for the rollers.

[0028] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft, characterized in that, The aircraft includes a main body (1), and a symmetrically arranged storage slot (2) is provided at the bottom of the main body (1). A rotatable inner door (3) is provided on one side of the storage slot (2). The rotatable inner door (3) is connected to the main body (1) through a rotatable inner door fastener (8). A retractable landing gear (4) is provided in the storage slot (2). A shock-absorbing wheel axle (5) is provided at the bottom of the retractable landing gear (4). A roller (7) is provided at the bottom of the shock-absorbing wheel axle (5). A rotatable outer door (6) is provided on the side of the storage slot (2) away from the rotatable inner door (3). The rotatable outer door (6) is connected to the main body (1) through a rotatable outer door fastener (9). A linkage rotation mechanism matching the rotatable outer door (6) is provided in the storage slot (2).

2. The retractable structure for a rotatable outer hatch inside the landing gear of a fixed-wing aircraft according to claim 1, characterized in that, The shock-absorbing wheel axle (5) is connected to the rotatable inner door (3) via a spring.

3. The retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft according to claim 2, characterized in that, The linkage rotation mechanism includes an adjustable gear set (10) provided in the storage slot (2). A rotating pressure rod (11) is provided on one side of the shaft end of the adjustable gear set (10). A rotating pull rod (12) is provided at the end of the adjustable gear set (10) away from the rotating pressure rod (11). The rotating pull rod (12) is connected to the rotatable outer hatch (6) through an adjusting steel wire (13).

4. The retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft according to claim 3, characterized in that, The rotatable outer hatch (6) is connected to the rotating pull rod (12) via spring 2.

5. The retractable structure for a rotatable external hatch inside the landing gear of a fixed-wing aircraft according to claim 4, characterized in that, The main wing cover plate (14) is provided in the storage slot (2) and on the side near the rotatable outer hatch (6).

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