CN-224225300-U - Multidirectional thrust line adjusting mechanism and aircraft

CN224225300UCN 224225300 UCN224225300 UCN 224225300UCN-224225300-U

Abstract

The utility model provides a multidirectional thrust line adjusting mechanism and an aircraft, wherein the multidirectional thrust line adjusting mechanism comprises a first fixed frame, a second fixed frame and a thrust cone, which are positioned on the aircraft, a pitching adjusting unit and a lateral adjusting unit, wherein the thrust cone is arranged between the first fixed frame and the second fixed frame, the rear end of the thrust cone faces the first fixed frame, a first adjusting ball is arranged on the first fixed frame, the first fixed frame is rotationally connected with the thrust cone ball through the first adjusting ball, the pitching adjusting unit is arranged on the second fixed frame and is used for adjusting the thrust cone along the vertical direction so as to enable the thrust cone to rotate along the first adjusting ball, and the lateral adjusting unit is arranged on the second fixed frame and is used for adjusting the thrust cone along the horizontal direction so as to enable the thrust cone to rotate along the first adjusting ball. Compared with the prior art, the multi-directional thrust line adjusting mechanism is arranged in the aircraft, so that the thrust line of the aircraft can be adjusted anytime and anywhere, and the adjusting process is convenient and rapid.

Inventors

GAO ZHE
LU JIA
JIANG LIZHAI
LIU YAO
XU FENG
WANG KUN
CHEN JIANLIN

Assignees

四川傲势乐翼科技有限公司

Dates

Publication Date: 20260512
Application Date: 20250522

Claims (10)

1. A multidirectional thrust line adjustment mechanism, comprising: The device comprises a first fixed frame, a second fixed frame and a thrust cone, wherein the first fixed frame, the second fixed frame and the thrust cone are arranged on an aircraft, the thrust cone is arranged between the first fixed frame and the second fixed frame, the rear end of the thrust cone faces the first fixed frame, a first adjusting ball is arranged on the first fixed frame, and the first fixed frame is rotationally connected with the thrust cone ball through the first adjusting ball; The pitching adjusting unit is arranged on the second fixed frame and is used for adjusting the thrust cone in the vertical direction so that the thrust cone rotates along the first adjusting ball; and the lateral adjusting unit is arranged on the second fixing frame and is used for adjusting the thrust cone along the horizontal direction so that the thrust cone rotates along the first adjusting ball.
2. The multidirectional thrust line adjusting mechanism according to claim 1, wherein the pitching adjusting unit comprises a pitching adjusting block, a first screw rod, a second screw rod and a Mongolian inner cushion block, the pitching adjusting block is located at the front end of the thrust cone, the first screw rod and the second screw rod are located at two sides of the second fixing frame respectively, the upper ends of the first screw rod and the second screw rod are in threaded connection with the pitching adjusting block, the Mongolian inner cushion block is located at the lower end of the second fixing frame, the first screw rod is in threaded connection with the Mongolian inner cushion block, and the second screw rod is connected with the Mongolian inner cushion block hole.
3. The multi-directional thrust line adjusting mechanism of claim 2, wherein the inner Monte cushion block is provided with a strip-shaped hole, and the lower end of the second screw rod passes through the strip-shaped hole.
4. The multi-directional thrust line adjusting mechanism of claim 3, wherein a Monte outer cushion block is arranged at the lower end of the Monte inner cushion block, a skin is arranged between the Monte outer cushion block and the Monte inner cushion block, two through holes are formed in the Monte outer cushion block, and the two through holes are respectively used for penetrating through the first screw rod and the second screw rod.
5. The multi-directional thrust line adjustment mechanism of claim 4, wherein said second fixed frame is provided with a rectangular slot in a vertical direction, a long edge of said rectangular slot being arranged in a vertical direction, said pitch adjustment block passing through said rectangular slot.
6. The multi-directional thrust line adjustment mechanism of claim 5, wherein the lateral adjustment unit comprises a lateral adjustment shaft and a lateral support frame, the lateral support frame is fixed on the second fixed frame and located on one side of the thrust cone, one side of the lateral adjustment shaft is rotatably connected with the lateral support frame, the lateral adjustment shaft is in threaded connection with the thrust cone, and the front end of the thrust cone is laterally moved by rotating the lateral adjustment shaft.
7. The multi-directional thrust line adjusting mechanism of claim 6, wherein the two lateral supporting frames are respectively positioned at two sides of the second fixed frame in the horizontal direction, and two ends of the lateral adjusting shaft are respectively connected with the two lateral supporting frames in a rotating way.
8. The multi-directional thrust line adjusting mechanism according to claim 7, wherein a long strip groove is formed in the front end of the thrust cone along the axial direction of the thrust cone, a second adjusting ball is slidably arranged in the long strip groove, a limit screw is arranged on the second adjusting ball, the middle of the lateral adjusting shaft is in threaded connection with the second adjusting ball, the limit screw limits the second adjusting ball from rotating along with the lateral adjusting shaft when the lateral adjusting shaft rotates, a long strip hole is formed in the lateral supporting frame along the vertical direction, and the lateral adjusting shaft penetrates through the long strip hole and can move along the long strip hole.
9. The multi-directional thrust line adjustment mechanism of any one of claims 1 to 8, wherein the first adjustment ball is provided with a stop pin at the top, and elongated holes are provided on both sides of the thrust cone.
10. An aircraft comprising the multidirectional thrust line adjustment mechanism of any one of claims 1-9, and The thrust cone rotating shaft is used for transmitting the thrust of the thrust cone to the aircraft, and the thrust cone rotating shaft is provided with a thrust cone outer cover plate.

Description

Multidirectional thrust line adjusting mechanism and aircraft Technical Field The utility model belongs to the technical field of aircrafts, and particularly relates to a multidirectional thrust line adjusting mechanism and an aircraft. Background The thrust lines of each aircraft are slightly different after the aircraft leaves the factory due to production and manufacturing and other reasons, if the thrust lines are not adjusted, the aircraft is fatal to a flight task, and the workload is large due to the fact that the aircraft is produced in a large scale and each aircraft needs to be adjusted. Currently, the thrust line of an aircraft is adjusted by adding a counterweight or a mobile device, but the thrust line is retested after adjustment, and if the adjustment amplitude is too large or insufficient, the above process is repeated until the requirement is met. In general, each aircraft needs to undergo a multi-adjustment process, and one aircraft is adjusted for more than two hours, especially after mass production, the adjustment process is very time-consuming and labor-consuming. Disclosure of utility model In view of the above-mentioned drawbacks of the prior art, an object of the present utility model is to provide a multi-directional thrust line adjusting mechanism for solving the problem that the adjustment of the thrust line after the delivery of the aircraft is time-consuming and laborious in the prior art. To achieve the above object and other related objects, the present utility model provides the following technical solutions: a multidirectional thrust line adjustment mechanism, comprising: The device comprises a first fixed frame, a second fixed frame and a thrust cone, wherein the first fixed frame, the second fixed frame and the thrust cone are arranged on an aircraft, the thrust cone is arranged between the first fixed frame and the second fixed frame, the rear end of the thrust cone faces the first fixed frame, a first adjusting ball is arranged on the first fixed frame, and the first fixed frame is rotationally connected with the thrust cone ball through the first adjusting ball; The pitching adjusting unit is arranged on the second fixed frame and is used for adjusting the thrust cone in the vertical direction so that the thrust cone rotates along the first adjusting ball; and the lateral adjusting unit is arranged on the second fixing frame and is used for adjusting the thrust cone along the horizontal direction so that the thrust cone rotates along the first adjusting ball. Optionally, the pitch adjusting unit comprises a pitch adjusting block, a first screw rod, a second screw rod and a Mongolian inner cushion block, wherein the pitch adjusting block is positioned at the front end of the thrust cone, the first screw rod and the second screw rod are respectively positioned at two sides of the second fixing frame, the upper ends of the first screw rod and the second screw rod are in threaded connection with the pitch adjusting block, the Mongolian inner cushion block is positioned at the lower end of the second fixing frame, the first screw rod is in threaded connection with the Mongolian inner cushion block, and the second screw rod is in threaded connection with the Mongolian inner cushion block hole. Optionally, a strip-shaped hole is formed in the Mongolian inner cushion block, and the lower end of the second screw rod penetrates through the strip-shaped hole. Optionally, the lower extreme of the inner Mongolian cushion is provided with an outer Mongolian cushion, be the covering in the middle of outer Mongolian cushion and the inner Mongolian cushion, be equipped with two through-holes on the outer Mongolian cushion, two through-holes are used for passing respectively first screw rod with the second screw rod. Optionally, the second fixed frame is provided with the rectangular channel along vertical direction, the long border vertical direction in rectangular channel arranges, pitch adjusting block passes the rectangular channel. Optionally, the side direction adjustment unit includes side direction adjustment shaft and side direction support frame, the side direction support frame is fixed on the second fixed frame and be located one side of thrust cone, side direction adjustment shaft one side with side direction support frame rotates to be connected, side direction adjustment shaft with thrust cone threaded connection makes through rotating the side direction adjustment shaft the front end lateral movement of thrust cone. Optionally, the lateral bracing frame is two, is located respectively the both sides in the horizontal direction of second fixed frame, the both ends of lateral adjustment axle are connected with two lateral bracing frames rotation respectively. Optionally, the front end of thrust awl is provided with rectangular groove along its axial, be provided with the second adjusting ball in rectangular inslot, be provided with stop screw on the second adjusting ball,