A type of lateral double-opening landing gear follow-up door

Abstract

This invention pertains to aircraft structural design and relates to a lateral, opposing landing gear follow-up door. It includes the door, front suspension bracket, front support, bolt assembly A, control bracket, bolt assembly B, linkage assembly, bolt assembly C, triangular rocker arm, bolt assembly D, landing gear folding strut, bolt assembly E, rocker arm, bolt assembly F, rear suspension bracket, bolt assembly G, and rear support. Through the connection of the triangular rocker arm, linkage, and control bracket with the opposing door, the linkage between the opposing door and the landing gear is achieved, simplifying the complexity of the landing gear retraction system. Compared to traditional door arrangements, this structural form reduces the number of parts, lowers manufacturing difficulty, saves manufacturing time and costs, and improves production efficiency. The simplified mechanism also reduces material consumption for this component, making assembly easier and facilitating component transportation and installation.

Description

Technical Field

[0001] This invention pertains to aircraft structural design and relates to a lateral double-opening landing gear follow-up door. Background Technology

[0002] To ensure a good aerodynamic shape, aircraft landing gear is typically retracted into the fuselage, enclosed by operable landing gear doors. There are two common methods for operating these doors: active and passive. Active control directly opens and closes the doors as the landing gear is extended or retracted. Both methods are widely used on various aircraft models. Active control is typically used if some doors need to close after the landing gear is extended; passive control is typically used if some doors cannot be closed or have a minimal aerodynamic impact.

[0003] Active door retraction requires a separate servo actuation system and position locking mechanism from the landing gear retraction. Compared to passive door retraction, active door operation is more complex and heavier. Furthermore, in emergency landing gear deployment situations, the landing gear may fail to deploy due to a malfunction in the active door operation system, resulting in lower reliability. Summary of the Invention

[0004] Purpose of the invention

[0005] This invention provides a passive opposed-opening landing gear door design that transforms the landing gear's retraction and extension motion in the aircraft's longitudinal plane into the door's retraction and extension motion in the transverse plane, achieving coordination and consistency between the door and landing gear's retraction and extension motions, and reducing the door's aerodynamic drag in takeoff and landing configurations.

[0006] Technical solution

[0007] A transversely opening landing gear follow-up door includes a door, a front suspension bracket, a front support, a bolt assembly A, a control bracket, a bolt assembly B, a tie rod assembly, a bolt assembly C, a triangular rocker arm, a bolt assembly D, a landing gear folding strut, a bolt assembly E, a rocker arm, a bolt assembly F, a rear suspension bracket, a bolt assembly G, and a rear support.

[0008] The tie rod assembly consists of an ear bolt, an inner threaded rod, and an adjusting bolt.

[0009] The front section of the hatch is riveted to the front suspension bracket; the other end of the front suspension bracket is hinged to the front support via bolt assembly A, forming a kinematic pair in which the hatch rotates around bolt assembly A; the front support is fixed to the wheel well sidewall by riveting.

[0010] The middle section of the cabin door is riveted to the control bracket; the other end of the control bracket is connected to the lug bolt of the pull rod assembly via bolt assembly B; the pull rod assembly consists of lug bolts, an inner threaded rod, and an adjusting bolt connected by screws; the lug bolts and adjusting bolts are arranged orthogonally, and both lug bolts and adjusting bolts are equipped with spherical bearings, and the length of the pull rod is adjusted according to installation requirements; the adjusting bolt of the pull rod assembly is connected to one end of the triangular rocker arm via bolt assembly C; the other two intersections of the triangular rocker arm form a rotating pair with bolt assembly F and the rocker arm, and bolt assembly D and the landing gear folding strut, respectively; the landing gear folding strut is the landing gear retraction component and the driving component for the cabin door movement; the rocker arm is connected to the fuselage via bolt assembly E, forming a rotating pair that rotates around bolt assembly E.

[0011] The rear section of the hatch is riveted to the rear suspension bracket; the other end of the rear suspension bracket is hinged to the rear support via bolt assembly G, forming a kinematic pair that rotates around the longitudinal axis. The rear support is fixed to the fuselage by riveting, and the hinge points of the rear support and the front support should be arranged coaxially.

[0012] Furthermore, the hatch is made of riveted metal materials, or it can be supported by carbon fiber composite materials;

[0013] Furthermore, the front suspension bracket is made of metal.

[0014] Furthermore, the control bracket is made of metal.

[0015] Furthermore, the rear suspension bracket is made of metal.

[0016] Furthermore, the pull rod assembly is made of metal.

[0017] Furthermore, the landing gear folding struts are made of metal.

[0018] Furthermore, the opening degree of the hatch is controlled by the length of the lever assembly;

[0019] Furthermore, the front suspension bracket has a J-shaped structure to ensure that the front suspension bracket does not interfere with the fuselage skin during the movement of the cabin door.

[0020] Furthermore, the control bracket has a J-shaped structure, which ensures that the control bracket and the fuselage skin will not interfere with each other during the movement of the hatch.

[0021] Furthermore, the rear suspension bracket has a J-shaped structure to ensure that the rear suspension bracket does not interfere with the fuselage skin during the movement of the cabin door.

[0022] The beneficial effects of this application are as follows:

[0023] This invention achieves linkage between the double-opening hatch and the landing gear by connecting the triangular rocker arm, connecting rod and control bracket to the hatch, thus simplifying the complexity of the landing gear retraction system.

[0024] This structural design reduces the number of parts, simplifies manufacturing, saves time and costs, and improves production efficiency compared to traditional door arrangements. The simplified mechanism also reduces material consumption, simplifies assembly, and facilitates transportation and installation. Furthermore, it reduces component weight, lightens the overall aircraft load, and improves fuel efficiency. Simultaneously, the simplified mechanism enhances the reliability of landing gear and door deployment, reducing the probability of malfunctions and contributing to safe takeoff and landing. Maintenance and repair are also simpler than with traditional doors, shortening repair time and reducing labor costs. This arrangement also reduces aerodynamic drag during takeoff and landing, improving aerodynamic performance. Costs are reduced throughout the entire process, from design and manufacturing to transportation, maintenance, and use. Attached Figure Description

[0025] Figure 1 Diagram of the front suspension bracket (single side);

[0026] Figure 2a Installation diagram of the control bracket and rocker arm (single side);

[0027] Figure 2b Side view (single side) of the control bracket and rocker arm mounting;

[0028] Figure 3 This is a schematic diagram of the tie rod assembly (one side).

[0029] Figure 4 This is a diagram of the rear suspension bracket installation (single side).

[0030] Among them: cabin door (1), front suspension bracket (2), front support (3), bolt assembly A (4), control bracket (5), bolt assembly B (6), tie rod assembly (7), bolt assembly C (8), triangular rocker arm (9), bolt assembly D (10), landing gear folding strut (11), bolt assembly E (12), rocker arm (13), bolt assembly F (14), rear suspension bracket (15), bolt assembly G (16), rear support (17), fuselage skin (18), lug bolt (19), inner screw (20), adjusting bolt (21). Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this invention. The embodiments described below with reference to reference are exemplary and intended to explain this invention, and should not be construed as limiting the invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention. The embodiments of this invention will be described in detail below.

[0032] A transversely opening landing gear follow-up door includes a door (1), a front suspension bracket (2), a front support (3), a bolt assembly A (4), a control bracket (5), a bolt assembly B (6), a tie rod assembly (7), a bolt assembly C (8), a triangular rocker arm (9), a bolt assembly D (10), a landing gear folding strut (11), a bolt assembly E (12), a rocker arm (13), a bolt assembly F (14), a rear suspension bracket (15), a bolt assembly G (16), and a rear support (17). The tie rod assembly consists of an ear bolt (19), an inner threaded rod (20), and an adjusting bolt (21). The front section of the door (1) is riveted to the front suspension bracket (2); the other end of the front suspension bracket (2) is hinged to the front support (3) via bolt assembly A (4), forming a kinematic pair in which the door (1) rotates around bolt assembly A (4); the front support (3) is fixed to the wheel well sidewall (18) by riveting.

[0033] The middle section of the hatch (1) is riveted to the control bracket (5); the other end of the control bracket (5) is connected to the lug bolt (19) of the pull rod assembly (7) through bolt assembly B (6); the pull rod assembly (7) is composed of lug bolt (19), inner threaded rod (20) and adjusting bolt (21) connected by screws; the lug bolt (19) and adjusting bolt (21) are arranged orthogonally, and both lug bolt (19) and adjusting bolt (21) are equipped with spherical bearings, and the length of the pull rod (7) is adjusted according to the installation requirements; pull rod assembly (7) The adjusting bolt (21) is connected to one end of the triangular rocker arm (9) through bolt assembly C (8); the other two intersections of the triangular rocker arm (9) form a rotating pair with bolt assembly F (14) and rocker arm (13), as well as bolt assembly D (10) and landing gear folding strut (11); the landing gear folding strut (11) is the landing gear retraction component and the driving component for the movement of the cabin door (1); the rocker arm (13) is connected to the fuselage through bolt assembly E (12) to form a rotating pair that rotates around bolt assembly E (12).

[0034] The rear section of the hatch (1) is riveted to the rear suspension bracket (15); the other end of the rear suspension bracket (15) is hinged to the rear support (17) through bolt assembly G (16) to form a kinematic pair that rotates around the longitudinal axis. The rear support (17) is fixed to the fuselage by riveting. The hinge point of the rear support (17) and the front support (4) should be arranged coaxially.

[0035] In one embodiment of the present invention, the hatch (1) is made of metal material riveted together, or it can be supported by carbon fiber composite material;

[0036] In one embodiment of the present invention, the front suspension bracket (2) is made of metal.

[0037] In one embodiment of the present invention, the control bracket (5) is made of metal.

[0038] In one embodiment of the present invention, the rear suspension bracket (15) is made of metal.

[0039] In one embodiment of the present invention, the tie rod assembly (7) is made of metal.

[0040] In one embodiment of the present invention, the landing gear folding strut (11) is made of metal.

[0041] In one embodiment of the present invention, the opening degree of the hatch (1) is controlled by the length of the pull rod assembly (7);

[0042] In one embodiment of the present invention, the front suspension bracket (2) has a J-shaped structure to ensure that the front suspension bracket (2) and the fuselage skin (18) will not interfere during the movement of the cabin door (1);

[0043] In one embodiment of the present invention, the control bracket (5) has a J-shaped structure. The J-shaped structure can ensure that the control bracket (5) and the fuselage skin (18) will not interfere during the movement of the hatch (1).

[0044] In one embodiment of the present invention, the rear suspension bracket (15) has a J-shaped structure to ensure that the rear suspension bracket (15) and the fuselage skin (18) will not interfere during the movement of the cabin door (1).

[0045] The transverse split landing gear follow-up door consists of the door (1), front suspension bracket (2), front support (3), bolt assembly A (4), control bracket (5), bolt assembly B (6), tie rod (7), bolt assembly C (8), triangular rocker arm (9), bolt assembly D (10), landing gear folding strut (11), bolt assembly E (12), rocker arm (13), bolt assembly F (14), rear suspension bracket (15), bolt assembly G (16), rear support (17), fuselage skin (18), lug bolt (19), inner screw (20), adjusting bolt (21), etc. The front suspension bracket (2) is fixed at one end to the front end of the cabin door (1) and hinged at the other end to the front support (3). The front support (3) is fixed to the fuselage. The three components are arranged along the transverse direction of the aircraft. The control bracket (5) is fixed at one end to the cabin door (1) and connected to the linkage assembly (7). The other end of the linkage assembly (7) is connected to one end of the triangular rocker arm (9). One end of the triangular rocker arm (9) is connected to the landing gear folding strut (11), and the other end is connected to one end of the rocker arm (13). The other end of the rocker arm (13) is connected to the fuselage via bolt assembly E (12). The components are arranged along the longitudinal and transverse directions of the aircraft. The rear suspension bracket (15) is fixed at one end to the rear end of the cabin door (1) and hinged at the other end to the rear support (17). The rear support (17) is fixed to the fuselage skin (18). The three components are arranged along the transverse direction of the aircraft.

[0046] In this invention, the front suspension bracket (2) and the rear suspension bracket (15) are used to support the front and rear ends of the hatch (1) respectively, and play the role of fixing the shape of the hatch (1). The control bracket (5) is arranged between the front suspension bracket (2) and the rear suspension bracket (15). During the opening and closing of the hatch (1), the triangular rocker arm (9) and the rocker arm (13) move in the longitudinal plane, the tie rod assembly (7) moves in the longitudinal and transverse planes, and the front suspension bracket (2), the rear suspension bracket (15) and the control bracket (5) move in the transverse plane. The tie rod assembly (7) is provided with joint bearings at both ends and is orthogonally installed to convert the movement of the landing gear folding strut (11) in the longitudinal plane into the movement of the hatch (1) in the transverse plane, so as to realize the opening and closing of the hatch (1) in the transverse direction.

[0047] like Figure 1 As shown, the cabin door (1) is riveted to the bottom plate of the front suspension bracket (2). The front suspension bracket (2) is arranged longitudinally in front of the cabin door (1) and has a J-shaped structure to ensure that the front suspension bracket (2) and the fuselage skin (18) will not interfere during the movement of the cabin door (1). The other end of the front suspension bracket (2) is hinged to the front support (3) through bolt assembly A (4) to form a kinematic pair that rotates around the longitudinal axis. The front support (3) is fixed to the fuselage skin (18) by riveting.

[0048] like Figure 2aAs shown, the hatch (1) is riveted to one end of the bottom plate of the control bracket (5). The control bracket (5) is arranged longitudinally in the middle section of the hatch and has a J-shaped structure. It will not interfere with the fuselage skin (18) during movement. The other end of the control bracket (5) is connected to the lug bolt (19) of the pull rod assembly (7) through bolt assembly B (6). The pull rod assembly (7) is composed of lug bolt (19), inner screw (20) and adjusting bolt (21) connected by screws. The lug bolt (19) and adjusting bolt (21) are arranged orthogonally. Both lug bolt (19) and adjusting bolt (21) are equipped with spherical bearings. The length of the pull rod assembly (7) is adjusted according to the installation requirements, such as Figure 3 As shown, the adjusting bolt (21) of the tie rod assembly (7) is connected to the bolt assembly C (8) at one end of the triangular rocker arm (9); the other two intersections of the triangular rocker arm (9) form a rotating pair with the bolt assembly F (14) and the rocker arm (13), as well as the bolt assembly D (10) and the landing gear folding strut (11). The landing gear folding strut (11) is the landing gear retraction component and the driving component for the movement of the cabin door. The rocker arm (13) is connected to the fuselage through the bolt assembly E (12).

[0049] like Figure 4 As shown, the hatch (1) is riveted to the bottom plate of the rear suspension bracket (15). The rear suspension bracket is arranged longitudinally at the rear section of the hatch and has a J-shaped structure to ensure that the rear suspension bracket (15) and the fuselage skin (18) will not interfere during the movement of the hatch. The other end of the rear suspension bracket (15) is hinged to the rear support (17) through the bolt assembly G (16) to form a kinematic pair that rotates around the longitudinal axis. The rear support (17) is fixed to the fuselage by riveting. The hinge point of the rear support (17) and the front support (4) should be arranged coaxially.

[0050] Working principle: When the landing gear needs to be lowered, the landing gear folding strut (11) extends as the landing gear is lowered. When the landing gear folding strut (11) extends, it drives the triangular rocker arm (9) to rotate. Since the other end of the rocker arm (13) is fixed to the fuselage, the triangular rocker arm (9) rotates while moving due to the restriction of the rocker arm (13). When the triangular rocker arm (9) rotates, it drives the pull rod assembly (7) to move downward. The pull rod assembly (7) pushes the control bracket (5) and the door (1) to rotate along the rotation axis of the door (1) (i.e., the hinge point axis between the rear support (17) and the front support (4)), thereby realizing the coordinated lowering of the door (1) and the landing gear. The process of retracting the door (1) is the reverse process of the above process. This structure realizes the coordinated movement of the door (1) and the landing gear retraction and extension.

[0051] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Within the spirit and principles of the present invention, any person skilled in the art may use the disclosed technical content to make changes or modifications to create equivalent embodiments applicable to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention, any modifications, equivalent substitutions, improvements, etc., should be included within the protection scope of the present invention.

Claims

1. A transversely opening landing gear follow-up door, characterized in that, The system includes a hatch, a front suspension bracket, a front support, bolt assembly A, a control bracket, bolt assembly B, a tie rod assembly, bolt assembly C, a triangular rocker arm, bolt assembly D, a landing gear folding strut, bolt assembly E, a rocker arm, bolt assembly F, a rear suspension bracket, bolt assembly G, and a rear support. The tie rod assembly consists of an eyelet bolt, an inner threaded rod, and an adjusting bolt. The front section of the hatch is riveted to the front suspension bracket. The other end of the front suspension bracket is hinged to the front support via bolt assembly A, forming a kinematic pair for the hatch to rotate around bolt assembly A. The front support is riveted to the wheel well sidewall. The middle section of the hatch is riveted to the control bracket. The other end of the control bracket is connected to the eyelet bolt of the tie rod assembly via bolt assembly B. The tie rod assembly consists of an eyelet bolt, an inner threaded rod, and an adjusting bolt connected by screws. The lug bolts and adjusting bolts are arranged orthogonally, and both lug bolts and adjusting bolts are equipped with spherical bearings. The length of the tie rod is adjusted according to the installation requirements. The adjusting bolt of the tie rod assembly is connected to one end of the triangular rocker arm through bolt assembly C. The other two intersections of the triangular rocker arm form a rotating pair with bolt assembly F and the rocker arm, as well as bolt assembly D and the landing gear folding strut, respectively. The landing gear folding strut is the landing gear retraction component and the driving component for the movement of the cabin door. The rocker arm is connected to the fuselage through bolt assembly E, forming a rotating pair that rotates around bolt assembly E. The rear section of the cabin door is riveted to the rear suspension bracket. The other end of the rear suspension bracket is hinged to the rear support through bolt assembly G, forming a kinematic pair that rotates around the longitudinal axis. The rear support is fixed to the fuselage by riveting, and the hinge points of the rear support and the front support are arranged coaxially.

2. The follow-up hatch as described in claim 1, characterized in that, The hatches are made of riveted metal or carbon fiber composite materials.

3. The follow-up hatch as described in claim 1, characterized in that, The front suspension bracket is made of metal.

4. The follow-up hatch as described in claim 3, characterized in that, The control bracket is made of metal.

5. The follow-up hatch as described in claim 4, characterized in that, The rear suspension bracket is made of metal.

6. The follow-up hatch as described in claim 5, characterized in that, The tie rod assembly is made of metal.

7. The follow-up hatch as described in claim 6, characterized in that, The landing gear folding struts are made of metal.

8. The follow-up hatch as described in claim 7, characterized in that, The opening degree of the hatch is controlled by the length of the lever assembly.

9. The follow-up hatch as described in claim 8, characterized in that, The front suspension bracket has a J-shaped structure to ensure that the front suspension bracket does not interfere with the fuselage skin during the movement of the cabin door.

10. The follow-up hatch as described in claim 1, characterized in that, The control bracket has a J-shaped structure, which ensures that the control bracket and the fuselage skin will not interfere during the movement of the cabin door; the rear suspension bracket has a J-shaped structure to ensure that the rear suspension bracket and the fuselage skin will not interfere during the movement of the cabin door.

Images