Airplane front wheel folding brake device

Abstract

The invention discloses an aircraft front wheel retracting brake device. Comprising a friction deceleration plate mounting base (5), the waist portion of the upper surface of the friction deceleration plate mounting base (5) is hinged to the lower end of a spring rod (6), and the upper end of the spring rod (6) is hinged to a spring rod connecting support (8) fixed to an airplane; the lower end of the friction speed-reducing plate mounting base (5) is hinged with a friction speed-reducing plate connecting support (10) fixed on the airplane; and a friction speed brake (3) is fixed on the lower surface of the friction speed brake mounting base (5). The front wheel can be quickly braked after being put away from the ground, and meanwhile the brake device is simple, reliable and good in maintainability.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structure design, in particular to an aircraft front wheel retracting brake device. Background Art

[0002] As the role of aircraft landing gear in modern aircraft design becomes increasingly prominent, designers are faced with new challenges. They need to design the safest and most reliable landing gear with the lightest weight and most compact structure. In order to reduce the weight of the aircraft system, simplify the system complexity, and save system costs, most aircraft currently do not use brake wheels on the front wheels, especially light aircraft. Because the front wheels of the aircraft have no brake device, after the front landing gear is retracted, the front wheels can only rely on air resistance and the friction of the axle to gradually slow down under the action of inertia, and it takes a long time to stop rotating. Since the retracted position of the front wheels is usually very close to the pilot, the sound and vibration caused by the rotation of the front wheels after being retracted into the wheel bay sometimes distract the pilot's attention during takeoff. Summary of the invention

[0003] The purpose of the present invention is to provide a front wheel retracting brake device for an aircraft, which can ensure that the front wheel can be quickly braked when retracting from the ground, and the brake device needs to be simple, reliable and easy to maintain.

[0004] Technical solution. An aircraft front wheel retracting brake device comprises a friction deceleration plate mounting base, wherein the waist of the upper surface of the friction deceleration plate mounting base is hinged to the lower end of the spring rod, the upper end of the spring rod is hinged to the spring rod connecting support fixed on the aircraft; the lower end of the friction deceleration plate mounting base is hinged to the friction deceleration plate connecting support fixed on the aircraft; and a friction deceleration plate is fixed to the lower surface of the friction deceleration plate mounting base.

[0005] In the aforementioned aircraft front wheel retracting brake device, the spring rod includes a rod end cover, a spring and a sleeve, the rod body on the upper side of the rod end cover extends into the lower side of the sleeve and is slidably connected to the sleeve, and a spring is sleeved between the rod end cover and the sleeve; the lower side of the rod end cover is hinged to the waist of the upper surface of the friction deceleration plate mounting base, and the upper side of the sleeve is hinged to the spring rod connecting support.

[0006] In the aforementioned aircraft front wheel retracting brake device, the upper side of the sleeve is threadedly connected to the earring bolt, and the earring bolt is hinged to the spring rod connecting support.

[0007] In the aforementioned aircraft front wheel retracting brake device, a tightening nut is threadedly connected to the earring bolt.

[0008] In the aforementioned aircraft front wheel retracting brake device, a bushing is provided at the position where the sleeve and the rod end cover rod body are slidably connected; the rod end cover rod body is connected to the limit nut after extending out of the bushing.

[0009] In the aforementioned aircraft front wheel retracting brake device, the friction deceleration plate is fixed to the lower surface of the friction deceleration plate mounting base via fixing bolts.

[0010] In the aforementioned aircraft front wheel retracting brake device, the lower end of the friction deceleration plate mounting base is hinged to the friction deceleration plate connecting support via the connecting shaft A.

[0011] In the aforementioned aircraft front wheel retracting brake device, the upper end of the spring rod is hinged to the spring rod connecting support fixed on the aircraft via the connecting shaft B.

[0012] In the aforementioned aircraft front wheel retracting brake device, the waist portion of the upper surface of the friction deceleration plate mounting base is hinged to the lower end of the spring rod via the connecting shaft C.

[0013] Beneficial effects: The aircraft front wheel retracting brake device of the present invention uses the landing gear in the retracting process as a power source when the landing gear is in the retracting process, and the tire gradually presses against the friction deceleration plate of the brake device, and the friction force of the friction deceleration plate on the tire is used to quickly decelerate the front wheel, so that it stops rotating in a short time. In addition, the friction force between the tire and the deceleration plate can be ensured by adjusting the length of the spring rod, and the overall structure is light in weight, easy to maintain, and reasonable and reliable in structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 Schematic diagram of the front wheel retracting brake device of the aircraft of the present invention;

[0015] Figure 2 It is a schematic diagram of the spring rod structure. DETAILED DESCRIPTION

[0016] Embodiment 1. A front wheel retracting brake device for an aircraft, see Figure 1-Figure 2 , including a friction deceleration plate mounting base 5, the waist of the upper surface of the friction deceleration plate mounting base 5 is hinged to the lower end of the spring rod 6, the upper end of the spring rod 6 is hinged to the spring rod connecting support 8 fixed on the aircraft; the lower end of the friction deceleration plate mounting base 5 is hinged to the friction deceleration plate connecting support 10 fixed on the aircraft; the friction deceleration plate mounting base 5 has a friction deceleration plate 3 fixed on its lower surface.

[0017] The aforementioned spring rod 6 includes a rod end cover 11, a spring 12 and a sleeve 13. The rod body on the upper side of the rod end cover 11 extends into the lower side of the sleeve 13 and is slidably connected to the sleeve 13. A spring 12 is sleeved between the rod end cover 11 and the sleeve 13. The lower side of the rod end cover 11 is hinged to the waist of the upper surface of the friction deceleration plate mounting base 5, and the upper side of the sleeve 13 is hinged to the spring rod connecting support 8.

[0018] The upper side of the aforementioned sleeve 13 is threadedly connected to the earring bolt 15, and the earring bolt 15 is hinged to the spring rod connecting support 8.

[0019] The aforementioned earring bolt 15 is threadedly connected with a tightening nut 14 .

[0020] A bushing 16 is provided at the position where the sleeve 13 and the rod body with the rod end cover 11 are slidably connected; the rod body with the rod end cover 11 is connected to the limit nut 16 after extending out of the bushing 16 .

[0021] The aforementioned friction deceleration plate 3 is fixed to the lower surface of the friction deceleration plate mounting base 5 via fixing bolts 4 .

[0022] The lower end of the friction deceleration brake mounting base 5 is hinged to the friction deceleration brake connecting support 10 via the connecting shaft A1.

[0023] The upper end of the aforementioned spring rod 6 is hinged to a spring rod connecting support 8 fixed on the aircraft via a connecting shaft B7.

[0024] The waist of the upper surface of the aforementioned friction deceleration plate mounting base 5 is hinged to the lower end of the spring rod 6 via the connecting shaft C9.

[0025] When the landing gear is retracted, after the tire 2 is retracted, the tire 2 contacts the friction deceleration plate 3, and the friction deceleration plate 3 and the friction deceleration plate mounting base 5 rotate around the connection point of the friction deceleration plate connecting support 8.

[0026] After the spring rod 6 is subjected to the force of the tire, the friction deceleration plate mounting base 5 compresses the spring rod 6, and the rod end cover 11 inside the spring rod 6 compresses the spring 12, and the rod end cover 11 penetrates into the cavity in the sleeve 13. The friction deceleration plate 3 is pressed against the tire 2 under the action of the spring 12 of the spring rod 6, generating a friction deceleration effect.

[0027] The earring bolt 15 in the spring rod 6 can be used to adjust the length of the spring rod to ensure the fit between the friction deceleration plate 3 and the tire 2.

Claims

1. An aircraft front wheel retracting brake device, characterized in that: The invention comprises a friction deceleration plate mounting base (5), wherein the waist of the upper surface of the friction deceleration plate mounting base (5) is hinged to the lower end of a spring rod (6), and the upper end of the spring rod (6) is hinged to a spring rod connecting support (8) fixed on the aircraft; the lower end of the friction deceleration plate mounting base (5) is hinged to a friction deceleration plate connecting support (10) fixed on the aircraft; and a friction deceleration plate (3) is fixed to the lower surface of the friction deceleration plate mounting base (5).

2. The aircraft front wheel retracting brake device according to claim 1, characterized in that: The spring rod (6) comprises a rod end cover (11), a spring (12) and a sleeve (13); the rod body on the upper side of the rod end cover (11) extends into the lower side of the sleeve (13) and is slidably connected to the sleeve (13); a spring (12) is sleeved between the rod end cover (11) and the sleeve (13); the lower side of the rod end cover (11) is hinged to the waist of the upper surface of the friction deceleration plate mounting base (5), and the upper side of the sleeve (13) is hinged to the spring rod connecting support (8).

3. The aircraft front wheel retracting brake device according to claim 2, characterized in that: The upper side of the sleeve (13) is threadedly connected to the earring bolt (15), and the earring bolt (15) is hingedly connected to the spring rod connecting support (8).

4. The aircraft front wheel retracting brake device according to claim 3, characterized in that: The earring bolt (15) is threadedly connected with a tightening nut (14).

5. The aircraft front wheel retracting brake device according to claim 2, characterized in that: A bushing (16) is provided at a position where the sleeve (13) and the rod body with the rod end cover (11) are slidably connected; the rod body with the rod end cover (11) is connected to the limiting nut (16) after extending out of the bushing (16).

6. The aircraft front wheel retracting brake device according to claim 1, characterized in that: The friction deceleration plate (3) is fixed to the lower surface of the friction deceleration plate mounting base (5) via fixing bolts (4).

7. The aircraft front wheel retracting brake device according to claim 1, characterized in that: The lower end of the friction deceleration plate mounting base (5) is hinged to the friction deceleration plate connecting support (10) via a connecting shaft A (1).

8. The aircraft front wheel retracting brake device according to claim 1, characterized in that: The upper end of the spring rod (6) is hinged to a spring rod connecting support (8) fixed on the aircraft via a connecting shaft B (7).

9. The aircraft front wheel retracting brake device according to claim 1, characterized in that: The waist portion of the upper surface of the friction deceleration plate mounting base (5) is hinged to the lower end of the spring rod (6) via a connecting shaft C (9).

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