阅读说明：本技术 一种起落架收放结构 (landing gear retraction structure ) 是由 张威 马驰 孙继勇 李田囡 傅碧华 张宏 周全树 于 2019-11-15 设计创作，主要内容包括：本发明公开了一种起落架收放结构,包括起落架支柱,以及驱动起落架支柱在收起位置和放下位置之间切换的收放驱动装置,收放驱动装置包括箱体和设于箱体内的驱动机构,驱动机构包括与箱体相连的驱动件、与驱动件传动连接的传动组件,传动组件具有末级传动轴,所述箱体与末级传动轴抱轴相连,末级传动轴的一端与机身固连。由此,起落架支柱上集成的收放装置带动起落架自身旋转收放,不仅减少了在机身上安装的旋转接头数量,且其结构更精简,收藏空间更小,安装约束更少,设计更为简单。尤其适用于小型航空器可收放式起落架。(The invention discloses an undercarriage folding and unfolding structure, which comprises an undercarriage supporting post and a folding and unfolding driving device for driving the undercarriage supporting post to switch between a folding position and a unfolding position, wherein the folding and unfolding driving device comprises a box body and a driving mechanism arranged in the box body, the driving mechanism comprises a driving piece connected with the box body and a transmission assembly in transmission connection with the driving piece, the transmission assembly is provided with a final-stage transmission shaft, the box body is connected with the final-stage transmission shaft in an encircling manner, and the end of the final-stage transmission shaft is fixedly connected with a machine body.)

The utility model provides an kind undercarriage receive and releases structure, including undercarriage pillar (1) to and drive undercarriage pillar (1) receive and release drive arrangement (5) of switching between the stowing position and the position of putting down, its characterized in that, receive and release drive arrangement (5) including box (12) and locate the actuating mechanism in box (12), actuating mechanism includes driving piece (7) that link to each other with box (12), the transmission assembly who is connected with driving piece (7) transmission, transmission assembly has final drive shaft (11), box (12) with final drive shaft (11) are embraced the axle and are linked to each other, the end of final drive shaft (11) links firmly with the fuselage.

2. A landing gear retraction and extension structure according to claim 1, wherein the drive member (7) is an electric motor.

3. A landing gear retraction and extension structure according to claim 2, wherein the drive assembly includes a worm (8) in driving connection with the motor, and a worm gear (9) in meshing drive with the worm (8), the worm gear (9) being fixed to the final drive shaft (11).

4. A landing gear retraction and extension structure according to claim 2, wherein the drive assembly comprises a worm (8) in driving connection with the motor, a worm wheel (9) in meshing drive with the worm (8), and a gear set in driving connection with the worm wheel (9), the final gear of the gear set being fixed to the final drive shaft (11).

5. A landing gear retraction arrangement according to claim 4, wherein the gear set includes a pinion gear (13) in driving connection with the turbine (9), and a bull gear (14) in meshing engagement with the pinion gear (13), the pinion gear (13) and turbine (9) each being mounted on primary drive shaft (15), the bull gear (14) being fixed to the final drive shaft (11).

6. Landing gear retraction arrangement according to claim 5, wherein the pinion (13) and gearwheel (14) are provided in gear box (10).

7. Landing gear retraction structure according to claim 1, wherein the end of the final drive shaft (11) is secured to the fuselage by means of a joint (4).

8. A landing gear retraction structure according to any of claims 1 to 7, wherein the casing (12) is formed integrally with the landing gear strut (1) .

9. A landing gear retraction structure according to any of claims 1 to 7 to , wherein the fuselage is provided with a stop (6) to limit the landing gear leg (1) to the lowered position.

10. A landing gear retraction structure according to any of claims 1 to 7 to , wherein the landing gear leg (1) is rotated to a set angle towards the nose after the central axis of the landing gear leg (1) is in the vertical direction to reach the down position, the set angle being an acute angle.

Technical Field

The invention relates to the technical field of aircraft landing gears, in particular to landing gear retraction structures.

Background

With the rapid development of small airplanes and unmanned planes, the demand of high-speed and light small aircrafts is increasing. Particularly, the rise of all-electric aircraft has increasingly highlighted the need for lightening retractable landing gear and saving installation space.

At present, for retractable landing gears of small airplanes and unmanned planes, the retractable structure is generally shown in figure 1, a end of a retractable actuator cylinder 2 is hinged on a fuselage through a joint 16, the other end of the retractable actuator cylinder is connected with a landing gear strut 1, the landing gear strut 1 is hinged with the fuselage through a joint 4, the retractable actuator cylinder 2 drives the landing gear strut 1 to rotate around the joint 4 through telescopic motion to achieve the retractable function of the landing gear.

Disclosure of Invention

The invention aims to solve the technical problem of overcoming the defects of the prior art and provides landing gear retracting and releasing structures which simplify the installation arrangement of the landing gear, reduce the weight of the landing gear and save the structural space of the landing gear.

In order to solve the technical problems, the invention adopts the following technical scheme:

kinds of undercarriage receive and releases structure, including the undercarriage pillar to and the drive undercarriage pillar receive and releases drive arrangement who switches between the retracting position and the position of putting down, receive and release drive arrangement and include the box and locate the actuating mechanism in the box, actuating mechanism includes the driving piece that links to each other with the box, the transmission assembly who is connected with the driving piece transmission, transmission assembly has the final stage transmission shaft, the box with the shaft is embraced to the final stage transmission shaft links to each other, the end and the fuselage of final stage transmission shaft link firmly.

Compared with the traditional undercarriage retracting mode, the invention reduces the number of rotary joints arranged on the body, simplifies the installation arrangement of the undercarriage, adopts the retracting device integrated on the undercarriage support to drive the undercarriage to rotate and retract, has more simplified structure, smaller storage space and less installation restriction, has simpler design, and is particularly suitable for the retractable undercarriage of a small aircraft.

improvement of the technical proposal:

the driving piece is a motor.

The transmission assembly comprises a worm in transmission connection with the motor and a worm wheel in meshing transmission with the worm, and the worm wheel is fixed on the final-stage transmission shaft. The self-locking characteristic of the worm gear is utilized to replace a position locking device, so that the structure is simplified, and the weight of the landing gear is reduced.

The transmission assembly comprises a worm in transmission connection with the motor, a worm wheel in meshing transmission with the worm, and a gear set in transmission connection with the worm wheel, and a final-stage gear of the gear set is fixed on the final-stage transmission shaft. The output load required by the power device is reduced by using the reduction gear set, and the position locking of the landing gear is realized by using the self-locking characteristic of the worm gear.

The traditional retraction mode driven by a retraction actuator cylinder determines the retraction angle of the undercarriage according to the stroke and the mounting position of the actuator cylinder, and the adjustable range is very limited.

The gear set comprises a small gear in transmission connection with the turbine and a large gear meshed with the small gear, the small gear and the turbine are both mounted on the primary transmission shaft, and the large gear is fixed on the final transmission shaft.

The pinion and the bull gear are located in the gearbox.

And the end of the final drive shaft is fixedly connected with the machine body through a joint.

The box is formed integrally with the landing gear leg .

And the body is provided with a limiting block which limits the landing gear strut to a down position.

The undercarriage pillar rotates to the central axis of the undercarriage pillar and rotates towards the nose along the vertical direction for a set angle so as to reach the laying-down position, and the set angle is an acute angle. The structural design can prevent the retraction jack from bearing the ground load of the landing gear during ground running and landing, improve the reliability of the retraction jack and reduce the space and weight of the landing gear.

Compared with the prior art, the invention has the advantages that:

1. compared with the traditional undercarriage retraction and extension mode, the invention reduces the number of rotary joints arranged on the undercarriage and simplifies the installation arrangement of the undercarriage.

2. The traditional retraction mode driven by a retraction actuator cylinder determines the retraction angle of the undercarriage according to the stroke and the mounting position of the actuator cylinder, and the adjustable range is very limited.

3. This patent adopts the integrated winding and unwinding devices drive undercarriage self rotation and receive and release on the undercarriage pillar, and its structure is more retrencied, and the collection space is littleer, and the installation restraint is still less, and the design is simpler.

4. The invention utilizes the self-locking characteristic of the worm gear to replace a position locking device, thereby simplifying the structure and reducing the weight of the landing gear.

5. The invention avoids the retraction jack bearing the ground load of the landing gear during ground running and landing, improves the reliability of the retraction jack and simultaneously reduces the space and the weight of the landing gear.

Drawings

FIG. 1 is a schematic view of a conventional landing gear retraction configuration (with the landing gear retracted in phantom).

FIG. 2 is a schematic view of a landing gear retraction configuration (with the landing gear retracted in phantom) according to an embodiment of the present invention.

FIG. 3 is a schematic diagram of a landing gear retraction structure according to an embodiment of the present invention.

FIG. 4 is a schematic ground load view of the landing gear retraction structure in a lowered position in accordance with an embodiment of the present invention.

Illustration of the drawings: 1. a landing gear strut; 2. retracting and releasing the actuating cylinder; 3. a landing gear bay; 4. a joint; 5. a retraction drive device; 6. a limiting block; 7. a drive member; 8. a worm; 9. a turbine; 10. a gear case; 11. a final drive shaft; 12. a box body; 13. a pinion gear; 14. a bull gear; 15. a primary drive shaft; 16. and (4) a joint.

Detailed Description

The invention is further described with reference to specific preferred embodiments, but not intended to limit the scope of the invention.