Main landing gear fairing of general-purpose aircraft

Abstract

The utility model discloses a main landing gear fairing of a general-purpose aircraft, and relates to the technical field of aviation engineering. Comprising a main undercarriage body, a fairing front part, a fairing rear part, a plurality of groups of connecting mechanisms and a sealing mechanism, wherein the fairing front part is mounted on one side of the outer wall of the main undercarriage body, each group of connecting mechanism is arranged between the fairing front part and the fairing rear part, and the sealing mechanism is arranged between the fairing front part and the fairing rear part. The sealing mechanism comprises a first sealing strip, a second sealing strip, a mounting part and a fixing part, and the first sealing strip is fixedly embedded in one side of the outer wall of the front portion of the fairing. According to the main landing gear fairing of the general-purpose aircraft, the fairing front part and the fairing rear part can be quickly connected together through the connecting mechanism, and the connecting part between the fairing front part and the fairing rear part is sealed through the sealing mechanism, so that the situation that the aerodynamic performance of the aircraft is influenced due to the fact that airflow nonuniformly flows through the fuselage due to the fact that a gap exists in the connecting part is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engineering, in particular to a main landing gear fairing of a general aircraft. Background Art

[0002] In order to reduce weight and simplify structure, aircraft often use fixed landing gear. Since the landing gear struts and tires are blunt bodies and have greater resistance during flight, it is often necessary to install fairings to reduce resistance.

[0003] The installation between the front part and the rear part of the aircraft landing gear fairing is usually installed together by bolts to form a complete fairing structure. After the front part and the rear part of the aircraft landing gear fairing are installed by bolts, there will be a gap at the connection between the front part and the rear part of the aircraft landing gear fairing, causing the airflow to flow unevenly through the fuselage, thereby affecting the aerodynamic performance of the aircraft. Utility Model Content

[0004] The utility model provides a main landing gear fairing for a general aircraft. The front part and the rear part of the fairing can be quickly connected together through a connecting mechanism, and the connection between the front part and the rear part of the fairing is sealed through a sealing mechanism to avoid gaps at the connection, which causes uneven airflow through the fuselage and affects the aerodynamic performance of the aircraft.

[0005] To achieve the above objectives, the utility model is implemented through the following technical solutions: A main landing gear fairing for a general aircraft, comprising:

[0006] Main landing gear body;

[0007] The front part of the fairing is installed on one side of the outer wall of the main landing gear body;

[0008] The rear part of the fairing is installed on one side of the outer wall of the main landing gear body;

[0009] A plurality of connecting mechanisms are provided, each of which is provided between the front portion and the rear portion of the fairing; and

[0010] A sealing mechanism is arranged between the front part and the rear part of the fairing, and the sealing mechanism includes a first sealing strip, a second sealing strip, an installation component and a fixing component. The first sealing strip is fixedly embedded in one side of the outer wall of the front part of the fairing, the second sealing strip is arranged on the installation component, the fixing component is arranged on the first sealing strip, and the installation component is arranged between the front part and the rear part of the fairing.

[0011] Furthermore, each group of the connecting mechanism includes an L-shaped rod and a mounting frame, the L-shaped rod is fixedly arranged on one side of the inner wall of the rear part of the fairing, the mounting frame is fixedly arranged on one side of the inner wall of the front part of the fairing, and the L-shaped rod is slidably embedded in the inner wall of the mounting frame.

[0012] Furthermore, the mounting component includes a mounting groove and a connecting groove, the mounting groove is opened on one side of the outer wall of the front part of the fairing, and the connecting groove is opened on one side of the outer wall of the rear part of the fairing.

[0013] Furthermore, the first sealing strip is fixedly embedded in the inner wall of the installation groove, the second sealing strip is fixedly embedded in the inner wall of the connection groove, and the second sealing strip is wrapped around the outer wall of the first sealing strip.

[0014] Furthermore, the fixing component includes an installation cavity, a mounting frame and multiple groups of elastic components. The installation cavity is opened on the inner wall of the first sealing strip, and the mounting frame is fixedly arranged on the inner wall of the installation cavity. Each group of elastic components is symmetrically arranged on both sides of the outer wall of the mounting frame.

[0015] Furthermore, each group of the elastic components includes a fixed tube, a movable rod and a spring, the fixed tube is fixedly arranged on one side of the outer wall of the mounting frame, the movable rod is slidably embedded in the inner wall of the fixed tube, and the movable rod is fixedly arranged on one side of the inner wall of the mounting cavity, and the spring is fixedly arranged between the mounting frame and the mounting cavity.

[0016] The utility model provides a main landing gear fairing for a general aircraft, which has the following beneficial effects: the main landing gear fairing for the general aircraft can quickly connect the front part of the fairing and the rear part of the fairing together through a connecting mechanism, and seal the connection between the front part of the fairing and the rear part of the fairing through a sealing mechanism to avoid gaps at the connection, which causes uneven airflow through the fuselage, thereby affecting the aerodynamic performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional diagram of the utility model;

[0018] Figure 2 It is a partial cross-sectional view of the utility model;

[0019] Figure 3 For this utility model Figure 1 The enlarged schematic diagram of point A in the middle;

[0020] Figure 4 For this utility model Figure 2 A magnified schematic diagram of point B in the middle.

[0021] In the figure: 1. main landing gear body; 2. front part of fairing; 3. rear part of fairing; 4. connecting mechanism; 401. L-shaped rod; 402. mounting frame; 5. sealing mechanism; 501. first sealing strip; 502. second sealing strip; 503. mounting groove; 504. connecting groove; 505. mounting cavity; 506. mounting frame; 507. fixing cylinder; 508. moving rod; 509. spring. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the utility model in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] See also Figure 1-4 The utility model provides a technical solution: a main landing gear fairing of a general aircraft, comprising:

[0024] Main landing gear body 1;

[0025] The front part 2 of the fairing is installed on one side of the outer wall of the main landing gear body 1;

[0026] The rear fairing portion 3 is mounted on one side of the outer wall of the main landing gear body 1;

[0027] A plurality of connecting mechanisms 4 are provided, and each connecting mechanism 4 is provided between the front fairing portion 2 and the rear fairing portion 3; and

[0028] The sealing mechanism 5 is arranged between the front part 2 of the fairing and the rear part 3 of the fairing. The sealing mechanism 5 includes a first sealing strip 501, a second sealing strip 502, an installation component and a fixing component. The first sealing strip 501 is fixedly embedded in one side of the outer wall of the front part 2 of the fairing, the second sealing strip 502 is arranged on the installation component, the fixing component is arranged on the first sealing strip 501, and the installation component is arranged between the front part 2 of the fairing and the rear part 3 of the fairing.

[0029] In this embodiment: a complete fairing structure is formed by the front fairing part 2 and the rear fairing part 3 on the main landing gear body 1 to reduce resistance. The front fairing part 2 and the rear fairing part 3 can be quickly connected together through the connecting mechanism 4. The connection between the front fairing part 2 and the rear fairing 3 is sealed through the sealing mechanism 5 to avoid gaps in the connection, which causes uneven airflow through the fuselage and affects the aerodynamic performance of the aircraft. The first sealing strip 501 cooperates with the second sealing strip 502 to seal the connection between the front fairing part 2 and the rear fairing 3. The first sealing strip 501 and the second sealing strip 502 are installed and placed through the installation component. The stability of the seal is increased through the fixing component.

[0030] Specifically, each set of connecting mechanisms 4 includes an L-shaped rod 401 and a mounting frame 402. The L-shaped rod 401 is fixedly arranged on one side of the inner wall of the rear part 3 of the fairing, and the mounting frame 402 is fixedly arranged on one side of the inner wall of the front part 2 of the fairing. The L-shaped rod 401 is slidably embedded in the inner wall of the mounting frame 402.

[0031] In this embodiment: through the sliding fit between the L-shaped rod 401 and the installation frame 402, the front part 2 of the fairing and the rear part 3 of the fairing can be quickly aligned, thereby improving the convenience of installing the front part 2 of the fairing and the rear part 3 of the fairing to avoid misalignment between the front part 2 of the fairing and the rear part 3 of the fairing. The L-shaped rod 401 and the installation frame 402 are connected by bolts, so that the front part 2 of the fairing and the rear part 3 of the fairing can be installed and fixed together.

[0032] Specifically, the mounting component includes a mounting groove 503 and a connecting groove 504 . The mounting groove 503 is provided on one side of the outer wall of the front part 2 of the fairing, and the connecting groove 504 is provided on one side of the outer wall of the rear part 3 of the fairing.

[0033] In this embodiment: the installation groove 503 is used for installing and placing the first sealing strip 501 , and the connection groove 504 is used for installing and placing the second sealing strip 502 .

[0034] Specifically, the first sealing strip 501 is fixedly embedded in the inner wall of the installation groove 503 , the second sealing strip 502 is fixedly embedded in the inner wall of the connection groove 504 , and the second sealing strip 502 is wrapped around the outer wall of the first sealing strip 501 .

[0035] In this embodiment, the first sealing strip 501 enters the inner wall of the second sealing strip 502, and the first sealing strip 501 is in contact with the second sealing strip 502, thereby increasing the sealing effect.

[0036] Specifically, the fixing component includes an installation cavity 505, a mounting frame 506 and multiple groups of elastic components. The installation cavity 505 is opened on the inner wall of the first sealing strip 501, and the mounting frame 506 is fixedly arranged on the inner wall of the installation cavity 505. Each group of elastic components is symmetrically arranged on both sides of the outer wall of the mounting frame 506.

[0037] In this embodiment: the installation cavity 505 in the first sealing strip 501 is used for installing and placing the installation frame 506. The installation frame 506 facilitates the first sealing strip 501 to fit with the second sealing strip 502 and is used for installing and placing the elastic component.

[0038] Specifically, each group of elastic components includes a fixed cylinder 507, a movable rod 508 and a spring 509. The fixed cylinder 507 is fixedly arranged on one side of the outer wall of the mounting frame 506, the movable rod 508 is slidably embedded in the inner wall of the fixed cylinder 507, and the movable rod 508 is fixedly arranged on one side of the inner wall of the mounting cavity 505, and the spring 509 is fixedly arranged between the mounting frame 506 and the mounting cavity 505.

[0039] In this embodiment: through the sliding cooperation between the fixed cylinder 507 and the movable rod 508, a guiding and supporting role is played, and through the spring 509, the first sealing strip 501 can be driven to squeeze the second sealing strip 502, so that the first sealing strip 501 and the second sealing strip 502 can fit tightly, which can increase the sealing effect and avoid the presence of a gap at the connection between the front part 2 of the fairing and the rear part 3 of the fairing.

[0040] When in use, first install the L-shaped rod 401 on the rear part 3 of the fairing inside the installation frame 402 of the front part 2 of the fairing, and install the L-shaped rod 401 and the installation frame 402 together by bolts, so that the front part 2 of the fairing and the rear part 3 of the fairing are combined together to form a complete fairing, and at the same time, the first sealing strip 501 enters the interior of the second sealing strip 502, and cooperates with the spring 509 to drive the first sealing strip 501 to squeeze the second sealing strip 502, so that the first sealing strip 501 and the second sealing strip 502 can fit tightly, thereby achieving the sealing of the connection between the front part 2 of the fairing and the rear part 3 of the fairing, so as to avoid a gap at the connection between the front part 2 of the fairing and the rear part 3 of the fairing.

[0041] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A main landing gear fairing for a general aircraft, characterized in that: include: Main landing gear body (1); A fairing front portion (2) is mounted on one side of an outer wall of the main landing gear body (1); The rear fairing (3) is mounted on one side of the outer wall of the main landing gear body (1); A plurality of connecting mechanisms (4) are provided, each of which is arranged between the front portion (2) and the rear portion (3) of the fairing; and A sealing mechanism (5) is arranged between a front portion (2) of a fairing and a rear portion (3) of the fairing, and the sealing mechanism (5) comprises a first sealing strip (501), a second sealing strip (502), a mounting component and a fixing component, wherein the first sealing strip (501) is fixedly embedded in one side of an outer wall of the front portion (2) of the fairing, the second sealing strip (502) is arranged on the mounting component, the fixing component is arranged on the first sealing strip (501), and the mounting component is arranged between the front portion (2) of the fairing and the rear portion (3) of the fairing.

2. The main landing gear fairing of a general aircraft according to claim 1, characterized in that: Each group of the connecting mechanisms (4) comprises an L-shaped rod (401) and a mounting frame (402), wherein the L-shaped rod (401) is fixedly arranged on one side of the inner wall of the rear part (3) of the fairing, and the mounting frame (402) is fixedly arranged on one side of the inner wall of the front part (2) of the fairing, and the L-shaped rod (401) is slidably embedded in the inner wall of the mounting frame (402).

3. The main landing gear fairing of a general aircraft according to claim 2, characterized in that: The mounting component comprises a mounting groove (503) and a connecting groove (504), wherein the mounting groove (503) is provided on one side of the outer wall of the front part (2) of the fairing, and the connecting groove (504) is provided on one side of the outer wall of the rear part (3) of the fairing.

4. The main landing gear fairing of a general aircraft according to claim 3, characterized in that: The first sealing strip (501) is fixedly embedded in the inner wall of the installation groove (503), the second sealing strip (502) is fixedly embedded in the inner wall of the connection groove (504), and the second sealing strip (502) is wrapped around the outer wall of the first sealing strip (501).

5. The main landing gear fairing of a general aircraft according to claim 4, characterized in that: The fixing component comprises an installation cavity (505), a mounting frame (506) and a plurality of groups of elastic components. The installation cavity (505) is opened on the inner wall of the first sealing strip (501), the mounting frame (506) is fixedly arranged on the inner wall of the installation cavity (505), and each group of elastic components is symmetrically arranged on both sides of the outer wall of the mounting frame (506).

6. The main landing gear fairing of a general aircraft according to claim 5, characterized in that: Each group of the elastic components comprises a fixed tube (507), a movable rod (508) and a spring (509); the fixed tube (507) is fixedly arranged on one side of the outer wall of the mounting frame (506); the movable rod (508) is slidably embedded in the inner wall of the fixed tube (507); the movable rod (508) is fixedly arranged on one side of the inner wall of the mounting cavity (505); and the spring (509) is fixedly arranged between the mounting frame (506) and the mounting cavity (505).

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