阅读说明：本技术 一种加强收拢舱门闭合紧密度的飞机起落架 (Aircraft landing gear for enhancing closing tightness of furled cabin door ) 是由 王巍 胡玉秀 金文瀚 闫梦娜 乌琛 闵习瑞 于 2019-12-06 设计创作，主要内容包括：本发明涉及一种加强收拢舱门闭合紧密度的飞机起落架,包括承重轮一和承重轮二,承重轮一和承重轮二间采用轮轴连接,轮轴两端均设置有刹车盘,刹车盘下端摩擦连接有刹车杆,轮轴上端连接有活塞杆,刹车杆另一端转动连接在活塞杆上,活塞杆侧壁上相对设置有两个油泵,油泵一侧通过螺纹连接有排油阀；活塞杆外滑动连接有外筒,外筒顶部焊装有固定环；所述外筒上焊接有收拢舱门装置、电推杆收放装置以及连杆收放装置,电推杆收放装置和连杆收放装置通过液压杆连接,实现对起落架的折叠回收。本发明能够减缓飞机起落架与风的阻力,提高飞机收拢舱门定位准确性及回收效率,并确保飞机起落架的平稳,保证飞机的安全降落。(The invention relates to an aircraft landing gear for enhancing the closing tightness of a furled cabin door, which comprises a first bearing wheel and a second bearing wheel, wherein the first bearing wheel and the second bearing wheel are connected by a wheel shaft; the piston rod is externally connected with an outer cylinder in a sliding manner, and the top of the outer cylinder is welded with a fixing ring; the outer barrel is welded with a folding cabin door device, an electric push rod folding and unfolding device and a connecting rod folding and unfolding device, and the electric push rod folding and unfolding device and the connecting rod folding and unfolding device are connected through a hydraulic rod to achieve folding and folding recovery of the undercarriage. The invention can slow down the resistance of the landing gear and wind, improve the positioning accuracy and recovery efficiency of the folding cabin door of the airplane, ensure the stability of the landing gear of the airplane and ensure the safe landing of the airplane.)

1. The utility model provides an strengthen aircraft landing gear who draws in cabin door closeness in which characterized in that: the oil pump device comprises a first bearing wheel and a second bearing wheel, wherein the first bearing wheel and the second bearing wheel are connected by a wheel shaft, brake discs are arranged at two ends of the wheel shaft, the lower end of each brake disc is connected with a brake rod in a friction mode, the upper end of the wheel shaft is connected with a piston rod, the other end of each brake rod is rotatably connected onto the piston rod, two oil pumps are oppositely arranged on the side wall of the piston rod, and one side of each oil pump is connected with; the piston rod is externally connected with an outer cylinder in a sliding manner, and the top of the outer cylinder is welded with a fixing ring; the outer barrel is welded with a folding cabin door device, an electric push rod folding and unfolding device and a connecting rod folding and unfolding device, and the electric push rod folding and unfolding device and the connecting rod folding and unfolding device are connected through a hydraulic rod to achieve folding and folding recovery of the undercarriage.

2. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 1, wherein: the furling cabin door device comprises a support rod and a furling cabin door, the support rod is welded on the outer wall of the outer barrel, the other end of the support rod is connected with an inner plate through screws, sealing strips are arranged around the inner plate, and an outer cabin plate is welded on the outer side of the inner plate to form the furling cabin door.

3. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 2, wherein: the sealing strip is fixed with the inner plate in a clamping and pressing mode.

4. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 1, wherein: the electric push rod retracting device comprises a fixing seat, a first declination spring, a second declination spring and an electric push rod, wherein the fixing seat is welded on the outer wall of the outer barrel, the first declination spring and the second declination spring are hinged to the fixing seat through a connecting shaft, the electric push rod is hinged to the top ends of the first declination spring and the second declination spring, and one end of the hydraulic rod is hinged to the hinged position of the electric push rod and the first declination spring and the second declination spring.

5. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 1, wherein: the connecting rod winding and unwinding devices comprise a first clamping plate, a second clamping plate, a connecting rod and a rotating pipe, wherein the first clamping plate and the second clamping plate are welded on the outer wall of the outer barrel, the connecting rod is hinged with the first clamping plate and the second clamping plate through a connecting shaft, the rotating pipe is rotatably connected to the end part of the connecting rod, the upper end of the rotating pipe is rotatably connected with a rotating ring, and the other end of the hydraulic rod is rotatably connected to the connecting position of the connecting rod and the rotating pipe.

6. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 1, wherein: and the brake disc is in interference connection with the wheel shaft.

7. An aircraft landing gear for enhancing closeness of a furled door in accordance with claim 1, wherein: the oil pump is connected with the piston rod through threads.

Technical Field

The invention belongs to the technical field of airplanes, and particularly relates to an aircraft landing gear for enhancing closing tightness of a furled cabin door.

Background

The landing gear is an accessory device for supporting the airplane and moving on the ground (water surface) when the lower part of the airplane is used for taking off and landing or sliding on the ground (water surface), the landing gear is the only part for supporting the whole airplane, so that the landing gear is an inseparable part of the airplane, the airplane cannot move on the ground without the landing gear, and the landing gear can be retracted according to the flight performance after the airplane takes off.

The hatch door that draws in of undercarriage, the majority adopts single-layer construction, because of sealed not tight, air flow in flight, just increased with the resistance of wind, when drawing in the hatch door, mostly be fixed knot structure between undercarriage and the hatch door, the hatch door is fixed a position inaccurate when drawing in, influences the efficiency that the hatch door was drawn in to the undercarriage, when the aircraft descends, lead to with the ground between the friction grow, it is unstable to appear descending easily, consequently need an enhancement to draw in the aircraft undercarriage of hatch door closed compactness to solve current problem promptly.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides the aircraft landing gear for enhancing the closing tightness of the folding cabin door, which can slow down the resistance of the aircraft landing gear and wind, improve the efficiency of the aircraft landing gear for folding the cabin door, ensure the stability of the aircraft landing gear and ensure the safe landing of the aircraft.

An aircraft landing gear for enhancing the closing tightness of a furled cabin door comprises a first bearing wheel and a second bearing wheel, wherein the first bearing wheel and the second bearing wheel are connected by a wheel shaft, brake discs are arranged at two ends of the wheel shaft, the lower end of each brake disc is connected with a brake rod in a friction mode, the upper end of the wheel shaft is connected with a piston rod, the other end of each brake rod is rotatably connected to the piston rod, two oil pumps are oppositely arranged on the side wall of the piston rod, and one side of each oil pump is connected with an; the piston rod is externally connected with an outer cylinder in a sliding manner, and the top of the outer cylinder is welded with a fixing ring; the outer barrel is welded with a folding cabin door device, an electric push rod folding and unfolding device and a connecting rod folding and unfolding device, and the electric push rod folding and unfolding device and the connecting rod folding and unfolding device are connected through a hydraulic rod to achieve folding and folding recovery of the undercarriage.

The furling cabin door device comprises a support rod and a furling cabin door, the support rod is welded on the outer wall of the outer barrel, the other end of the support rod is connected with an inner plate through screws, sealing strips are arranged around the inner plate, and an outer cabin plate is welded on the outer side of the inner plate to form the furling cabin door.

The sealing strip is fixed with the inner plate in a clamping and pressing mode.

The electric push rod retracting device comprises a fixing seat, a first declination spring, a second declination spring and an electric push rod, wherein the fixing seat is welded on the outer wall of the outer barrel, the first declination spring and the second declination spring are hinged to the fixing seat through a connecting shaft, the electric push rod is hinged to the top ends of the first declination spring and the second declination spring, and one end of the hydraulic rod is hinged to the hinged position of the electric push rod and the first declination spring and the second declination spring.

The connecting rod winding and unwinding devices comprise a first clamping plate, a second clamping plate, a connecting rod and a rotating pipe, wherein the first clamping plate and the second clamping plate are welded on the outer wall of the outer barrel, the connecting rod is hinged with the first clamping plate and the second clamping plate through a connecting shaft, the rotating pipe is rotatably connected to the end part of the connecting rod, the upper end of the rotating pipe is rotatably connected with a rotating ring, and the other end of the hydraulic rod is rotatably connected to the connecting position of the connecting rod and the rotating pipe.

And the brake disc is in interference connection with the wheel shaft.

The oil pump is connected with the piston rod through threads.

The invention has the beneficial effects that:

1. by arranging the inner plate, the sealing strip and the outer cabin plate, the aircraft landing gear can be closed more tightly when the cabin door is folded, the resistance between the aircraft landing gear and wind is reduced, and the requirement for closing the cabin door when the aircraft landing gear is folded is met;

2. the electric push rod, the hydraulic rod, the connecting shaft, the first declination spring and the second declination spring are arranged, so that the folding cabin door can be accurately positioned during the recovery through the sliding of the hydraulic rod and under the action of the electric push rod, the first declination spring and the second declination spring, the accurate recovery of the folding cabin door is realized, and the recovery efficiency of the folding cabin door of the landing gear of the airplane is improved;

3. the outer cylinder, the piston rod, the brake rod and the brake disc are arranged to provide buffering for the contact between the first bearing wheel and the second bearing wheel and the ground, so that the friction force between the first bearing wheel and the second bearing wheel and the ground can be reduced, the landing gear of the airplane is ensured to be stable and reliable, and the airplane can land safely.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a rear view of the present invention;

FIG. 3 is an enlarged view of portion A of FIG. 1;

FIG. 4 is an enlarged view of portion B of FIG. 1;

wherein the content of the first and second substances,

1 bearing wheel I, 2 bearing wheel II, 3 wheel shafts, 4 brake discs, 5 brake levers, 6 piston rods, 7 oil pumps, 8 outer cylinders, 9 supporting rods, 10 inner plates, 11 sealing strips, 12 outer cabin plates, 13 clamping plates I, 14 clamping plates II, 15 connecting rods, 16 rotating pipes, 17 rotating rings, 18 fixing seats, 19 connecting shafts, 20 declination spring I, 21 declination spring II, 22 hydraulic rods, 23 electric push rods, 24 fixing rings and 25 oil discharge valves.

Detailed Description

For better understanding of the present invention, the technical solutions and effects of the present invention will be described in detail by the following embodiments with reference to the accompanying drawings.