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CN-224220734-U - Landing gear mechanism of space plane model

CN224220734UCN 224220734 UCN224220734 UCN 224220734UCN-224220734-U

Abstract

The utility model relates to the technical field of model aircrafts and discloses a space aircraft model landing gear mechanism, which comprises a first shell, wherein a second fixing plate is fixedly connected to the left end and the right end of the front side of the first shell at the rear side, a self-locking mechanism is rotationally connected to the outer wall of the second fixing plate, a third fixing plate is rotationally connected to the bottom end of the self-locking mechanism, a cabin cover is fixedly connected between the adjacent rear sides of the third fixing plates, and a first fixing plate is fixedly connected to the middle part of the front side of the first shell at the rear side. According to the utility model, the motor is used for starting output power, the first rotary joint is driven to rotate through the transmission connecting rod, the wheel is driven to turn over and touch the ground, the two self-locking mechanisms of the rotary joint lock the reverse motion after the rotary joint is in place, the transmission precision and the scene reduction degree are improved, the stable posture of the landing gear is kept, the landing gear cabin cover is simultaneously opened in the process, and the smooth and unimpeded process is ensured, so that the daily use requirements of operators are facilitated.

Inventors

  • KOU SONGLIN
  • WANG WEIFENG
  • Xing Yingxue

Assignees

  • 深圳市博尔创意文化发展有限公司

Dates

Publication Date
20260512
Application Date
20250714

Claims (7)

  1. 1. A space plane model undercarriage mechanism comprises two first shells (1) and is characterized in that the rear side is fixedly connected with a second fixing plate (10) at the left end and the right end of the first shell (1) at the front side, a self-locking mechanism (11) is rotationally connected to the outer wall of the second fixing plate (10), a third fixing plate (12) is rotationally connected to the bottom end of the self-locking mechanism (11), a cabin cover (6) is fixedly connected between the adjacent rear sides of the third fixing plate (12), a first fixing plate (9) is fixedly connected to the middle part of the front side of the first shell (1) at the rear side, a rotating shaft (14) is rotationally connected to the middle part of the front side of the first fixing plate (9), a second rotating joint (8) is rotationally connected to the front side of the rotating shaft (14), a sliding sleeve (13) is rotationally connected to the other end of the second rotating joint (8), a transmission connecting rod (3) is rotationally connected to the inner side of the sliding sleeve (13), a first rotating joint (4) is rotationally connected to the outer wall of the sliding sleeve (13), a second end of the first rotating joint (4) is fixedly connected to a motor (19), and a first motor (7) is rotationally connected to the outer wall of the first rotating plate (19).
  2. 2. The landing gear mechanism for the space shuttle model according to claim 1, wherein a tripod I (16) is fixedly connected to the middle upper portion of the rear side of the outer wall of the transmission connecting rod (3), and a supporting rod I (15) is fixedly connected to the top of the tripod I (16).
  3. 3. The landing gear mechanism for the space shuttle model according to claim 1, wherein a tripod (18) is fixedly connected to the middle upper part of the front side of the outer wall of the transmission connecting rod (3).
  4. 4. A space shuttle model landing gear mechanism according to claim 3, wherein the top of the tripod II (18) is fixedly connected with a support rod II (17).
  5. 5. A space shuttle model landing gear mechanism according to claim 1, wherein a second shell (2) is fixedly connected between the inner adjacent sides of the first shells (1).
  6. 6. A space shuttle model landing gear mechanism according to claim 1, characterized in that the bottom of the transmission link (3) is rotatably connected to the top of the L-shaped plate (19).
  7. 7. A space shuttle model landing gear mechanism according to claim 4, wherein the other ends of the second supporting rod (17) and the first supporting rod (15) are fixedly connected with the outer wall of the corresponding first shell (1).

Description

Landing gear mechanism of space plane model Technical Field The utility model relates to the technical field of model aircrafts, in particular to a space aircraft model landing gear mechanism. Background The landing gear technology of the space plane is developed on the basis of the landing gear technology of the plane, but has unique requirements and characteristics, because the space plane has high speed and heavy landing weight when returning and needs landing under various weather conditions and runway conditions, the landing gear has higher requirements on the aspects of structural strength, buffer performance, braking performance and reliability of the landing gear, and the landing gear adopts advanced designs and materials, such as high-strength aluminum alloy and titanium alloy, so as to reduce the weight and improve the bearing capacity, and is also provided with a complex buffer system and a braking system so as to ensure safe landing. The landing gear system of the current space plane and aircraft simulation model has the remarkable technical limitations that a main stream product adopts a fixed wheel frame or a simple manual folding structure, only static storage or basic angle adjustment can be realized, electromechanical cooperative action in the real landing gear folding and unfolding process can not be restored, a manual mechanism depends on external force operation of a user, a self-locking function is lacking after unfolding, the wheel frame swings back often due to vibration, the steering angle deviation of wheels is more than 15 degrees, and the landing gear is difficult to accurately simulate a landing posture, meanwhile, the landing gear hatch cover is separated from the wheel frame in a movement mode, and independent operation is needed, so that clamping and even component interference in the unfolding process are caused, the dynamic demonstration function of the model is severely limited, and therefore the user experience is reduced. Disclosure of utility model In order to make up for the defects, the utility model provides a landing gear mechanism of a space plane model, which aims to solve the problems that in the prior art, the electromechanical cooperative action of a real landing gear in the retraction process cannot be restored, the self-locking function is lacking after the landing gear is deployed, the backward swing angle deviation of a wheel carrier is larger than 15 degrees, and the landing posture is difficult to accurately simulate. In order to achieve the purpose, the space plane model undercarriage mechanism comprises two first shells, the left end and the right end of the front side of the first shells are fixedly connected with a second fixing plate, the outer wall of the second fixing plate is rotationally connected with a self-locking mechanism, the bottom end of the self-locking mechanism is rotationally connected with a third fixing plate, a cabin cover is fixedly connected between the adjacent rear sides of the two third fixing plates, the middle part of the front side of the first shells is fixedly connected with a first fixing plate, the middle part of the front side of the first fixing plate is rotationally connected with a rotating shaft, the front side of the rotating shaft is rotationally connected with a second rotary joint, the other end of the second rotary joint is rotationally connected with a sliding sleeve, the inner side of the sliding sleeve is slidingly connected with a transmission connecting rod, the outer wall of the sliding sleeve is rotationally connected with the first rotary joint, the other end of the first rotary joint is fixedly connected with an L-shaped plate, the outer wall of the L-shaped plate is rotationally connected with a wheel, and the right end of the rear side of the first shells is fixedly connected with a motor. As a further description of the above technical solution: The upper middle part of the rear side of the outer wall of the transmission connecting rod is fixedly connected with a tripod I, and the top of the tripod I is fixedly connected with a supporting rod I. As a further description of the above technical solution: the middle upper part of the front side of the outer wall of the transmission connecting rod is fixedly connected with a tripod II. As a further description of the above technical solution: And the top of the tripod II is fixedly connected with a support rod II. As a further description of the above technical solution: And a second shell is fixedly connected between the adjacent inner sides of the first shells. As a further description of the above technical solution: the bottom of the transmission connecting rod is rotationally connected with the top of the L-shaped plate. As a further description of the above technical solution: The other ends of the second support rod and the first support rod are fixedly connected with the outer wall of the corresponding shell I. The utility model has the followin