A main landing gear door mechanism, aircraft and stowage and deployment method

Abstract

The application provides a main landing gear cabin door mechanism, an aircraft and a folding and unfolding method. The main landing gear cabin door mechanism comprises a left cabin door and a right cabin door, one end of the left cabin door is provided with a first folding and unfolding driving mechanism, one end of the right cabin door is provided with a second folding and unfolding driving mechanism, a small cabin door is hinged to one side of the left cabin door close to the right cabin door, and the small cabin door and the left cabin door are provided with a third folding and unfolding driving mechanism capable of driving the small cabin door and the left cabin door to rotate respectively; in a first position, the left cabin door and the right cabin door are in a vertical state, and the small cabin door is folded and overlapped with the left cabin door; in a second position, the left cabin door, the small cabin door and the right cabin door are horizontally located on the same plane. The small cabin door can be independently folded and unfolded, the folded small cabin door can reduce the windward area of the cabin door in a lowered state and the aerodynamic load borne by the cabin door, and the design of the driving mechanism for folding and unfolding the cabin door is more convenient.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft landing gear technology, in particular to a main landing gear door mechanism, an aircraft and a stowing and deploying method. BACKGROUND

[0002] The landing gear of an aircraft is accommodated in the cabin of the fuselage and is provided with a door. The large landing gear makes the cabin larger, resulting in a larger door. Even if the door is designed as a two-leaf door, the weight of the door itself is relatively heavy. In addition, the large door also has a large aerodynamic load due to the large area in the lowered state, which in turn makes the mechanism for driving the door to rotate relatively heavy and the design cost relatively high. SUMMARY

[0003] The purpose of the present application is to provide a main landing gear door mechanism, an aircraft and a stowing and deploying method, which can reduce the windward area of the door in the lowered state and reduce the aerodynamic load on the door.

[0004] The technical solution of the present application is: a main landing gear door mechanism, comprising a left door and a right door which are arranged adjacent to each other and open to form a first position or close to form a second position, the left door is provided at one end away from the right door with a first stowing and deploying driving mechanism for driving the left door to rotate, the right door is provided at one end away from the left door with a second stowing and deploying driving mechanism for driving the right door to rotate, the left door is hinged at one side close to the right door with a small door, and the small door and the left door are provided with a third stowing and deploying driving mechanism for driving the small door and the left door to rotate, respectively; in the first position, the left door and the right door are in a vertical state, and the small door is folded and overlapped with the left door; in the second position, the left door, the small door and the right door are horizontally located on the same plane.

[0005] Preferably, the right door has an area a, the left door has an area b, and the small door has an area c, c+b>a.

[0006] Preferably, the first stowing and deploying driving mechanism and the second stowing and deploying driving mechanism each comprise a first connecting bracket and a first actuating cylinder, one end of the first connecting bracket is connected with the right door or the left door, the other end of the first connecting bracket is provided with a second hinge point, the first connecting bracket is further provided with a first hinge point, and one end of the first actuating cylinder is hinged to the first hinge point.

[0007] Preferably, the first connecting bracket is an arc-shaped bracket.

[0008] Preferably, the third retracting and releasing drive mechanism comprises a second connecting bracket, a second actuating cylinder and a third actuating cylinder, one end of the second connecting bracket is connected with the left hatch, the other end of the second connecting bracket is provided with a third hinge point, the second connecting bracket is further provided with a fourth hinge point and a fifth hinge point, one end of the second actuating cylinder is hinged to the fifth hinge point, the other end of the second actuating cylinder is hinged to the small hatch, and one end of the third actuating cylinder is hinged to the fourth hinge point.

[0009] Preferably, the second connecting bracket is an arc-shaped bracket.

[0010] Preferably, the left hatch and the right hatch are further provided with a rotating bracket, the second retracting and releasing drive mechanism and the rotating bracket are staggered on the right hatch, and the first retracting and releasing drive mechanism, the third retracting and releasing drive mechanism and the rotating bracket are staggered on the left hatch.

[0011] The application further provides an aircraft, comprising a fuselage, the fuselage having a cabin capable of accommodating a main landing gear, the fuselage being provided with the main landing gear hatch mechanism as described above on the side wall of the cabin, and the first retracting and releasing drive mechanism, the third retracting and releasing drive mechanism and the second retracting and releasing drive mechanism being hinged to the corresponding positions of the fuselage.

[0012] Preferably, the application further provides a method for retracting and releasing the main landing gear of the aircraft, comprising:

[0013] Step one, releasing the main landing gear:

[0014] Step 1.1, driving the hatch to open:

[0015] The first retracting and releasing drive mechanism and the third retracting and releasing drive mechanism are started to drive the left hatch to rotate outward until the first position, and the second retracting and releasing drive mechanism is started to drive the right hatch to rotate outward until the first position;

[0016] The third retracting and releasing drive mechanism is further started to drive the small hatch to rotate to the inner side of the left hatch, so that the small hatch and the left hatch are overlapped to form the first position;

[0017] Step 1.2, driving the main landing gear to release:

[0018] Step 1.3, driving the left hatch and the right hatch to close:

[0019] The first retracting and releasing drive mechanism is started to drive the left hatch to rotate inward until the second position, and the second retracting and releasing drive mechanism is started to drive the right hatch to rotate inward until the second position;

[0020] Step two, retracting the main landing gear:

[0021] Step 2.1, driving the left hatch and the right hatch to open:

[0022] The first retractable drive mechanism is started to drive the left door to rotate outward until it is in the first position; at the same time, the second retractable drive mechanism is started to drive the right door to rotate outward until it is in the first position;

[0023] Step 2.2, drive the main landing gear to retract;

[0024] Step 2.3, drive the door to close:

[0025] The third retractable drive mechanism is started to drive the small door to rotate to the outside of the left door until the small door is flush with the left door;

[0026] The first retractable drive mechanism is started to drive the left door to rotate inward until it is in the second position; at the same time, the second retractable drive mechanism is started to drive the right door to rotate inward until it is in the second position.

[0027] Compared with the related art, the present application has the following beneficial effects:

[0028] I. The main landing gear door mechanism designs one of the doors (the left door) as a foldable composite structure, and the small door can be independently retracted and folded. After the door is opened, the folded small door can reduce the windward area in the door down state and reduce the aerodynamic load on the door, so that the design of the door retracting and driving mechanism is more convenient;

[0029] II. The structure design of the small door can retract the left door and the right door when the main landing gear is in the down state, so as to protect the equipment in the landing gear cabin;

[0030] III. The right door area is greatly reduced, and the small door is driven to rotate by an independent driving mechanism, so that the design of each driving mechanism is more convenient, and the number of driving mechanism installations can be reduced. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 The present application provides a front structure schematic view of the main landing gear door mechanism in the first position;

[0032] Figure 2 is a side view of Figure 1

[0033] Figure 3 is a schematic view of the door being opened (wherein A is a schematic view of the left door, the right door, and the small door being unfolded; B is a schematic view of the small door being folded);

[0034] Figure 4 is a schematic view of the door when the main landing gear is down and the door is in the first position;

[0035] Figure 5 is a front view of Figure 4

[0036] ​​Figure 6 Fig. 2 is a schematic view of the left and right cabin doors in the second position after the main landing gear is extended.

[0037] Figure 7 Fig. 3 is a top view of the left and right cabin doors. Figure 6 Fig. 4 is a schematic view of the left and right cabin doors in the first position.

[0038] In the drawings: 1, left cabin door; 2, right cabin door; 3, first extension and retraction drive mechanism; 31, first connecting bracket; 32, first actuating cylinder; 33, first hinge point; 34, second hinge point; 4, second extension and retraction drive mechanism; 5, third extension and retraction drive mechanism; 51, second connecting bracket; 52, second actuating cylinder; 53, third hinge point; 54, fourth hinge point; 55, fifth hinge point; 56, third actuating cylinder; 6, small cabin door; 7, rotating bracket; 10, main landing gear. DETAILED DESCRIPTION

[0039] The present application will be described in detail below with reference to the drawings and embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. For the convenience of description, if the terms "upper", "lower", "left" and "right" appear in the following text, they only mean the upper, lower, left and right directions of the drawings themselves, and do not limit the structure.

[0040] As shown in Figs. 1-4, the cabin door mechanism of the main landing gear provided by the present embodiment comprises a left cabin door 1, a right cabin door 2, a first extension and retraction drive mechanism 3, a second extension and retraction drive mechanism 4, a third extension and retraction drive mechanism 5, a small cabin door 6 and a rotating bracket 7. Figure 1 Figure 2 The left cabin door 1 and the right cabin door 2 are arranged adjacent to each other and open to form a first position or close to form a second position. The end of the left cabin door 1 away from the right cabin door 2 is provided with the first extension and retraction drive mechanism 3 for driving the left cabin door 1 to rotate. The side of the left cabin door 1 close to the right cabin door 2 is hinged with the small cabin door 6 and is provided with the third extension and retraction drive mechanism 5 for driving the small cabin door 6 to rotate. The first extension and retraction drive mechanism 3, the third extension and retraction drive mechanism 5 and the rotating bracket 7 are staggered on the left cabin door 1.

[0041] The left cabin door 1 and the right cabin door 2 are arranged adjacent to each other and open to form a first position or close to form a second position. The end of the left cabin door 1 away from the right cabin door 2 is provided with the first extension and retraction drive mechanism 3 for driving the left cabin door 1 to rotate. The side of the left cabin door 1 close to the right cabin door 2 is hinged with the small cabin door 6 and is provided with the third extension and retraction drive mechanism 5 for driving the small cabin door 6 to rotate. The first extension and retraction drive mechanism 3, the third extension and retraction drive mechanism 5 and the rotating bracket 7 are staggered on the left cabin door 1.

[0042] ​The left hatch 1 is provided with a notch, the size of which is equal to that of the small hatch 6, so that the left hatch 1 and the small hatch 6 form a complete rectangle. The right hatch 2 has an area a, the left hatch 1 has an area b, and the small hatch 6 has an area c, c+b>a. The left hatch 1 and the right hatch 2 are asymmetric structures. In this embodiment, the right hatch 2 is only two-thirds of a conventional symmetric hatch, and only one second retracting and deploying drive mechanism 4 is needed to realize the retracting and deploying of the hatch. The left hatch 1 combines the first actuating cylinder 32 and the third actuating cylinder 56 on the second retracting and deploying drive mechanism 4, two actuating cylinders, which reduces the windward area of the left hatch 1 in the lowered state after the small hatch 6 is folded, thereby reducing the aerodynamic load on the hatch.

[0043] The first retracting and deploying drive mechanism 3 comprises a first connecting bracket 31 and a first actuating cylinder 32. The first connecting bracket 31 is a C-shaped arc bracket, and the arc curvature is arranged inward (as shown in the figure). Figure 4 The rotating bracket 7 has the same structure as the first connecting bracket 31. One end of the first connecting bracket 31 is connected with the left hatch 1, and the other end of the first connecting bracket 31 is provided with a second hinge point 34, which is hinged with the side wall of the cabin of the fuselage. The rotating bracket 7 has the same structure as the first connecting bracket 31, one end of the rotating bracket 7 is connected with the left hatch 1, and the other end is hinged with the fuselage.

[0044] The first connecting bracket 31 is further provided with a first hinge point 33, one end of the first actuating cylinder 32 is hinged on the first hinge point 33, and the other end of the first actuating cylinder 32 is hinged at a corresponding position of the fuselage.

[0045] The third retracting and deploying drive mechanism 5 comprises a second connecting bracket 51, a second actuating cylinder 52, and a third actuating cylinder 56. One end of the second connecting bracket 51 is connected with the left hatch 1, and the other end of the second connecting bracket 51 is provided with a third hinge point 53, which is hinged on the fuselage.

[0046] The second connecting bracket 51 is further provided with a fourth hinge point 54 and a fifth hinge point 55, one end of the second actuating cylinder 52 is hinged on the fifth hinge point 55, the other end of the second actuating cylinder 52 is hinged on the small hatch 6, one end of the third actuating cylinder 56 is hinged on the fourth hinge point 54, and the other end of the third actuating cylinder 56 is hinged on the fuselage.

[0047] The structure of the second retracting and deploying drive mechanism 4 is the same as that of the first retracting and deploying drive mechanism 3. The second retracting and deploying drive mechanism 4 and the rotating bracket 7 are staggered on the right hatch 2.

[0048] The second retracting and extending driving mechanism 4 and the rotating support 7 form the hinge of the right cabin door 2. The first retracting and extending driving mechanism 3 and the rotating support 7 form the hinge of the left cabin door 1. The second retracting and extending driving mechanism 4 drives the right cabin door 2 to rotate, the first retracting and extending driving mechanism 3 drives the left cabin door 1 to rotate, and the third retracting and extending driving mechanism 5 drives the small cabin door 6 to rotate to form the first position and the second position.

[0049] The first actuating cylinder 32, the second actuating cylinder 52 and the third actuating cylinder 56 each comprise an outer cylinder and a piston rod (such as a hydraulic cylinder) retracting in the outer cylinder.

[0050] In the first position, the left cabin door 1 and the right cabin door 2 are in a vertical state, and the small cabin door 6 is folded and overlapped with the left cabin door 1 (as shown in Figure 4 、 Figure 5 In the second position, the left cabin door 1, the small cabin door 6 and the right cabin door 2 are horizontally and located in the same plane.

[0051] As shown in Figure 4 The present application also provides an aircraft, comprising a fuselage, the fuselage having a cabin capable of accommodating a main landing gear, and the main landing gear cabin door mechanism, the first connecting support 31, the rotating support 7, the second connecting support 51, the first actuating cylinder 32 and the third actuating cylinder 56 are hinged to the corresponding positions of the fuselage.

[0052] As shown in Figure 5 The notch of the left cabin door 1 provided with the small cabin door 6 can avoid the position of the main landing gear 10. When the main landing gear 10 is lowered, the left cabin door 1 and the right cabin door 2 are in a closed state (as shown in Figure 6 、 Figure 7 , so as to protect the equipment in the cabin.

[0053] The present application also provides a retracting and extending method of the main landing gear of the above-mentioned aircraft, comprising:

[0054] Step one, the main landing gear is lowered:

[0055] Step 1.1, drive the cabin door to open:

[0056] As shown in Figure 3A , the first actuating cylinder 32 of the first retracting and extending driving mechanism 3 and the third actuating cylinder 56 of the third retracting and extending driving mechanism 5 are elongated to drive the left cabin door 1 to rotate outward until it is in the first position; at the same time, the first actuating cylinder 32 of the second retracting and extending driving mechanism 4 is elongated to drive the right cabin door 2 to rotate outward until it is in the first position;

[0057] As shown in Figure 3BAs shown, the second actuating cylinder 52 of the third retractable drive mechanism 5 is retracted to drive the small cabin door 6 to rotate to the inner side of the left cabin door 1, so that the small cabin door 6 and the left cabin door 1 are overlapped to form the first position (as shown in Figure 4 , Figure 5 As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0058] Step 1.2, drive the actuating cylinder on the main landing gear to lower the main landing gear 10 and make it contact with the ground.

[0059] Step 1.3, drive the left cabin door 1 and the right cabin door 2 to close:

[0060] As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position. Figure 6 Figure 7 Step 2, drive the actuating cylinder on the main landing gear to raise the main landing gear 10:

[0061] Step 2.1, drive the left cabin door 1 and the right cabin door 2 to open:

[0062] As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0063] Step 2.2, drive the main landing gear to be raised; Figure 3B Step 2.3, drive the cabin door to be closed:

[0064] As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0065] As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0066] Figure 3A As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0067] As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position. Figure 1 Figure 2 As shown, the first actuating cylinder 32 of the first retractable drive mechanism 3 and the third actuating cylinder 56 of the third retractable drive mechanism 5 are retracted to drive the left cabin door 1 to rotate inwardly until it is in the second position; at the same time, the first actuating cylinder 32 of the second retractable drive mechanism 4 is retracted to drive the right cabin door 2 to rotate inwardly until it is in the second position.

[0068] ​​​The above merely illustrates the embodiments of the present application, and is not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process conversion, or direct or indirect application in other related technical fields, which is made according to the content of the present application, shall be included in the patent protection scope of the present application.

Claims

1. A main landing gear door mechanism, characterized in that, The left hatch (1) and the right hatch (2) are adjacently arranged and opened to form a first position or closed to form a second position, the left hatch (1) is provided with a first stowing and driving mechanism (3) at one end away from the right hatch (2) for driving the left hatch (1) to rotate, the right hatch (2) is provided with a second stowing and driving mechanism (4) at one end away from the left hatch (1) for driving the right hatch (2) to rotate, the left hatch (1) is hinged with a small hatch (6) at one side close to the right hatch (2), the small hatch (6) and the left hatch (1) are provided with a third stowing and driving mechanism (5) for driving the small hatch (6) and the left hatch (1) to rotate respectively; in the first position, the left hatch (1) and the right hatch (2) are in vertical state, and the small hatch (6) is folded and overlapped with the left hatch (1); in the second position, the left hatch (1), the small hatch (6) and the right hatch (2) are horizontally arranged on the same plane; the first stowing and driving mechanism (3) and the second stowing and driving mechanism (4) each comprise a first connecting bracket (31) and a first actuating cylinder (32), one end of the first connecting bracket (31) is connected with the right hatch (2) or the left hatch (1), the other end of the first connecting bracket (31) is provided with a second hinge point (34), the first connecting bracket (31) is further provided with a first hinge point (33), and one end of the first actuating cylinder (32) is hinged to the first hinge point (33); the third stowing and driving mechanism (5) comprises a second connecting bracket (51), a second actuating cylinder (52) and a third actuating cylinder (56), one end of the second connecting bracket (51) is connected with the left hatch (1), the other end of the second connecting bracket (51) is provided with a third hinge point (53), the second connecting bracket (51) is further provided with a fourth hinge point (54) and a fifth hinge point (55), one end of the second actuating cylinder (52) is hinged to the fifth hinge point (55), the other end of the second actuating cylinder (52) is hinged to the small hatch (6), and one end of the third actuating cylinder (56) is hinged to the fourth hinge point (54).

2. A main landing gear bay door mechanism according to claim 1, characterised in that, The right hatch (2) has an area a, the left hatch (1) has an area b, and the small hatch (6) has an area c, and c+b>a.

3. The main landing gear bay door mechanism of Claim 1, wherein, The first connecting bracket (31) is an arc-shaped bracket.

4. The main landing gear bay door mechanism of Claim 1, wherein, The second connecting bracket (51) is an arc-shaped bracket.

5. The main landing gear bay door mechanism of Claim 1, wherein, The left hatch (1) and the right hatch (2) are further provided with a rotating bracket (7) following the left hatch (1) and the right hatch (2), the second stowing and driving mechanism (4) and the rotating bracket (7) are staggered on the right hatch (2), and the first stowing and driving mechanism (3), the third stowing and driving mechanism (5) and the rotating bracket (7) are staggered on the left hatch (1).

6. An aircraft comprising a fuselage having a nacelle capable of housing a main landing gear, characterised in that, The first stowing and driving mechanism (3), the third stowing and driving mechanism (5) and the second stowing and driving mechanism (4) are hinged to corresponding positions of a fuselage.

7. A method of stowing a main landing gear of an aircraft as claimed in claim 6, characterised in that, It comprises: Step one, main landing gear is put down: Step 1.1, drive the hatch to open: Step 1, the main landing gear is put down: Step 1.1, the left door (1) and the right door (2) are opened: Step 1.2, the main landing gear is put down: Step 1.3, the left door (1) and the right door (2) are closed: Step 1.4, the small door (6) is opened: Step 1.5, the main landing gear is put up: Step 1.6, the small door (6) is closed: Step 1.7, the left door (1) and the right door (2) are opened: Step 1.8, the main landing gear is put up: Step 1.9, the left door (1) and the right door (2) are closed: Step 2, the main landing gear is put up: Step 2.1, the left door (1) and the right door (2) are opened: Step 2.2, the main landing gear is put up: Step 2.3, the doors are closed: Step 2.4, the small door (6) is opened: Step 2.5, the main landing gear is put down: Step 2.6, the small door (6) is closed: Step 2.7, the left door (1) and the right door (2) are opened: Step 2.8, the main landing gear is put down: Step 2.9, the left door (1) and the right door (2) are closed: Step 2.10, the small door (6) is opened: Step 2.11, the main landing gear is put up: Step 2.12, the small door (6) is closed.

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