CN212074403U - Automatic remote control type aircraft auxiliary undercarriage - Google Patents
Automatic remote control type aircraft auxiliary undercarriage Download PDFInfo
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- CN212074403U CN212074403U CN202020660600.1U CN202020660600U CN212074403U CN 212074403 U CN212074403 U CN 212074403U CN 202020660600 U CN202020660600 U CN 202020660600U CN 212074403 U CN212074403 U CN 212074403U
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Abstract
The utility model discloses an automatic remote control type airplane auxiliary undercarriage, which comprises a main shaft, a steering gear, a steering connecting rod, an auxiliary connecting rod, an airplane wheel, a driving cylinder, an auxiliary cylinder, a driving motor, a controller and a digital remote control board, wherein the airplane wheel comprises a driving wheel and an auxiliary wheel, one end of the main shaft is connected with the steering gear, the other end of the main shaft is connected with a limiter, the two symmetrical ends of the steering gear are respectively connected with the steering connecting rod, and the other end of the steering connecting rod is connected with the driving wheel; the other end of the auxiliary connecting rod is connected with an auxiliary cylinder after being connected with the auxiliary wheel, and the auxiliary cylinder is connected with the main shaft; the controller is provided with a cylinder and steering gear control, positioning, speed regulation, starting braking and locking module and a power supply module; the digital remote control board is provided with a steering operation rod, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller; the limiter of the main shaft is connected with the bearing shaft of the undercarriage, and the undercarriage retracts into the undercarriage cabin. The utility model discloses realize the automatic control aircraft migration, fix a position moreover accurate error-free.
Description
Technical Field
The utility model relates to an aircraft appurtenance field specifically indicates an automatic remote control formula aircraft assists undercarriage.
Background
The landing gear of the airplane is an indispensable supporting component for the airplane to fly and land or slide on the ground, and is retracted according to the flight performance of the airplane after the airplane takes off.
The airplane turning mode includes two modes, one mode is that the airplane turns through single braking of a main wheel or the thrust or the pulling force of a left engine and a right engine, the other mode is that the front wheel is controlled by a front wheel turning mechanism to deflect so that the airplane turns, the prior mode is adopted by a common light airplane, while the middle-sized and above airplanes are difficult to turn due to the fact that the front wheel turning mechanism is used for realizing turning, the main wheel of the heavy airplane can also deflect in cooperation with the front wheel except for the front wheel adding turning mechanism in the turning of the heavy airplane, and the turning performance of the airplane is improved.
However, the turning mechanism of some heavy passenger aircraft or heavy aircraft usually fixes the front wheel in the vehicle through the special vehicle of ground service, and the steering of the aircraft is realized through the traction and the steering of the ground service vehicle, and the turning mechanism is inconvenient to fix the undercarriage (front wheel) on one hand, inconvenient to remove the undercarriage from the ground service vehicle on the other hand, and needs the cooperation of a plurality of ground service personnel to move the aircraft in an accurate position during the steering.
SUMMERY OF THE UTILITY MODEL
To the problem, the utility model aims at providing an automatic remote control formula aircraft auxiliary landing gear realizes automatic control aircraft migration through the manual control remote control board, fixes a position moreover and is accurate, uses manpower sparingly and material resources.
In order to realize the technical purpose, the utility model provides a technical scheme is:
an automatic remote control type airplane auxiliary undercarriage comprises a main shaft, a steering gear, a connecting rod, airplane wheels, two cylinders, a driving motor, a controller and a digital remote control board, wherein the airplane wheels comprise driving wheels and auxiliary wheels, the connecting rod comprises a steering connecting rod and an auxiliary connecting rod, the cylinders comprise driving cylinders and auxiliary cylinders, the number of the driving wheels is two, the first end of the main shaft is connected with the steering gear, the second end of the main shaft is provided with a stopper, the symmetrical ends of the two sides of the steering gear are respectively connected with the steering connecting rod, and the other end of the steering connecting rod is connected with the driving wheels; the auxiliary wheel is connected with an auxiliary connecting rod, the other end of the auxiliary connecting rod is connected with an auxiliary cylinder, and the other end of the auxiliary cylinder is connected with the main shaft; the main shaft is internally provided with a driving cylinder, the controller is electrically connected with the driving cylinder, the auxiliary cylinder, the steering gear, the limiter and the driving motor, and the controller is internally provided with a cylinder control module, a steering gear control module, a positioning module, a starting module, a speed regulating module, a braking module, a locking module and a power supply module; the digital remote control board is electrically connected with the controller and is provided with a steering operating rod, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller; the limiter is used for connecting an auxiliary undercarriage of the airplane and a bearing shaft of the undercarriage of the airplane, the driving cylinder is used for adjusting the length of the main shaft, and the auxiliary cylinder is used for retracting and releasing the auxiliary wheel; the limiter of the main shaft is connected with the bearing shaft of the undercarriage, and the undercarriage retracts into the undercarriage cabin.
The utility model has the advantages that: the airplane transfer is automatically controlled by manually controlling the remote control board, and the positioning is accurate and error-free.
The method is further optimized in that the controller and the digital remote control board are in signal connection with the landing gear control end of the airplane.
By adopting the technical scheme, after the controller is in signal connection with the control end of the aircraft landing gear, the retraction and landing actions of the aircraft landing gear can be realized by operating the digital controller in the standby state of the aircraft, the landing gear can be conveniently retracted by operating after the limiter of the aircraft auxiliary landing gear is connected with the bearing shaft of the aircraft landing gear, and the aircraft is controlled and operated to move after the landing gear is retracted.
Further optimization is that the connecting rod, the steering gear, the wheel and the driving motor are all required to meet the mechanical performance of the auxiliary equipment of the heavy passenger plane.
By adopting the technical scheme, the mechanical structure in the equipment needs to have certain bearing capacity, and the auxiliary undercarriage of the airplane can bear the weight of the head of the whole airplane after the undercarriage of the airplane is retracted.
Further optimization is that the driving motor adopts a permanent magnet synchronous motor.
By adopting the technical scheme, the whole transmission system of the permanent magnet synchronous motor is light in weight, unsprung weight is lighter than that of the traditional wheel axle transmission, power per unit weight is high, and a steering system such as a flexible steering frame and a single-axle steering frame is convenient to design due to the fact that no gear box is arranged, and power performance of driven equipment is improved.
Further optimization is that the positioning module in the controller is provided with an infrared detection positioning device.
By adopting the technical scheme, the infrared positioning device is accurate in positioning and small in moving error.
It is further optimized that the digital remote control panel displays the three-dimensional space position of the whole towed airplane in the operating state.
By adopting the technical scheme, the aircraft can be conveniently controlled to move by an operator through the position of the aircraft in the three-dimensional space.
Further optimized is that the maximum load bearing capacity of the main shaft is proportional to the weight of the fuselage.
By adopting the technical scheme, the airplane bodies of different types have different weights, the maximum bearing capacity of the required main shaft is different, and the applicable auxiliary undercarriage of the airplane is selected according to the known airplane type.
Further optimization is that the aircraft auxiliary landing gear further comprises a protective cover, and the protective cover is tightly matched with internal equipment of the aircraft auxiliary landing gear.
By adopting the technical scheme, the protective cover is the shell of the whole auxiliary undercarriage, and the design of the shell can protect internal equipment and mechanical structures and prevent the auxiliary undercarriage from being damaged by other materials when in use.
Drawings
FIG. 1 is a general schematic view of the present embodiment;
in the figure: 1-a stopper; 2-a main shaft; 3-an auxiliary cylinder; 4-a steering linkage; 5-a diverter; 6-auxiliary connecting rod; 7-an auxiliary wheel; 8-driving wheel.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings. It should be noted that, in the present application, the upper, lower, left and right terms are the same as the upper, lower, left and right terms in the drawings.
An automatic remote control type airplane auxiliary undercarriage is shown in figure 1 and comprises a main shaft 2, a steering gear 5, connecting rods, airplane wheels, air cylinders, a driving motor, a controller and a digital remote control board, wherein the airplane wheels comprise driving wheels 8 and auxiliary wheels 7, the connecting rods comprise steering connecting rods 4 and auxiliary connecting rods 6, the air cylinders comprise driving air cylinders and auxiliary air cylinders 3, the number of the driving wheels 8 is two, the first end of the main shaft 2 is connected with the steering gear 5, the second end of the main shaft 2 is provided with a limiting stopper 1, two symmetrical ends of the steering gear 5 are respectively connected with the steering connecting rods 4, and the other end of each steering connecting rod 4 is connected with the driving wheel 8; the auxiliary wheel 7 is connected with the auxiliary connecting rod 6, the other end of the auxiliary connecting rod 6 is connected with the auxiliary cylinder 3, and the other end of the auxiliary cylinder 3 is connected with the main shaft 2; the main shaft 2 is internally provided with a driving cylinder, the controller is electrically connected with the driving cylinder, the auxiliary cylinder 3, the steering gear 5, the limiter 1 and the driving motor, and the controller is internally provided with a cylinder control module, a steering gear 5 control module, a positioning module, a starting module, a speed regulating module, a braking module, a locking module and a power supply module; the digital remote control board is electrically connected with the controller and is provided with a steering operating rod, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller; the limiter 1 is used for connecting an auxiliary undercarriage of an airplane and a bearing shaft of the undercarriage of the airplane, the driving cylinder is used for adjusting the length of the main shaft 2, and the auxiliary cylinder 3 is used for retracting and releasing the auxiliary wheel 7; the limiter 1 of the main shaft 2 is connected with a bearing shaft of the undercarriage, and the undercarriage retracts into the undercarriage cabin.
The main shaft 2, the steering gear 5, the steering connecting rod 4 and the two driving wheels 8 are matched to realize a steering mechanism of the auxiliary undercarriage, the auxiliary connecting rod 6 and the auxiliary wheel 7 are the auxiliary mechanism of the auxiliary undercarriage, the auxiliary structure is controlled by the digital remote control board to contract after the limiter 1 of the main shaft 2 is connected with the bearing shaft of the auxiliary frame, the auxiliary wheel 7 leaves the ground, and after the airplane is moved, the auxiliary structure is released and the auxiliary undercarriage is moved to a corresponding position. The main shaft 2 is stretched and retracted by the driving cylinder, after the auxiliary undercarriage is moved to the position of the auxiliary undercarriage of the airplane, the height of the main shaft 2 needs to be adjusted when the limiter 1 is installed due to the difference of the heights of different undercarriage of the airplane, so that the limiter 1 on the top of the main shaft 2 is matched with a bearing shaft of the undercarriage of the airplane, and the driving cylinder is locked at the stretched and retracted position after the limiter 1 is matched with the main shaft; the auxiliary cylinder 3 is used for extending and retracting the auxiliary wheel 7, the auxiliary cylinder 3 is controlled to enable the auxiliary wheel 7 to be retracted and locked after the limiter 1 is matched with a bearing shaft of an aircraft landing gear, and after the aircraft is moved, the auxiliary cylinder 3 is controlled to enable the auxiliary wheel 7 to be extended and retracted to a ground contact position and locked.
The aircraft auxiliary landing gear further comprises a protective cover, the protective cover is tightly matched with internal equipment of the aircraft auxiliary landing gear, the protective cover is a shell of the whole auxiliary landing gear, the internal equipment and mechanical structures can be protected by the design of the shell, the auxiliary landing gear is prevented from being damaged by other materials when in use, and the controller is installed on the inner surface of the protective cover of the auxiliary landing gear to protect the controller.
The controller is used for controlling the operation of the air cylinder, the limiter 1, the steering gear 5 and the driving motor, and the controller receives an operation signal of the digital control board and controls downstream equipment to perform corresponding action according to an operation instruction. The control of the cylinder, the steering gear 5, the stopper 1 and the driving motor is respectively realized by a cylinder control module, a steering gear 5 control module, a positioning module, a starting module, a speed regulating module, a braking module, a locking module and a power module which are arranged in the controller, and the speed regulating module and the starting and braking module are used for starting and adjusting the power performance of the driving motor.
The digital remote control device comprises a steering operation rod of a digital remote control board, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller, wherein the steering operation rod controls the rotation of a steering gear 5; the display screen is used for displaying the process of the airplane being moved, the real-time position of the airplane and the control state of the auxiliary landing gear; the starting controller is used for controlling the starting and braking of the auxiliary landing gear of the airplane; the positioning calibrator is used for calibrating the accurate position of airplane migration, for example, when an airplane needs to be migrated to a gate, the positions of the gate and a gate of the airplane need to be accurately adjusted; the motor and cylinder controller is used for controlling the actions of the driving motor and the cylinder.
The controller and the digital remote control board are in signal connection with the landing gear control end of the airplane, after the controller is in signal connection with the landing gear control end of the airplane, the retraction and landing actions of the landing gear of the airplane can be realized by operating the digital controller under the standby state of the airplane, the landing gear is conveniently retracted by operating after the limiter 1 of the auxiliary landing gear of the airplane is connected with the bearing shaft of the landing gear of the airplane, and the airplane is controlled and operated to move after the landing gear is retracted. The positioning module in the controller is provided with an infrared detection positioning device, and the infrared detection positioning device is accurate in positioning and small in moving error; the digital remote control board displays the three-dimensional space position of the whole towed airplane in an operation state, and an operator can conveniently control the airplane to move through the position of the airplane in the three-dimensional space.
The connecting rod, the steering gear 5, the airplane wheels and the driving motor all need to meet the mechanical performance of auxiliary equipment of the heavy-duty airliner, and a mechanical structure in the equipment needs to have certain bearing capacity, so that the auxiliary undercarriage of the airplane can bear the weight of the head of the whole airplane after the undercarriage of the airplane is retracted; the maximum bearing capacity of the main shaft 2 is in direct proportion to the weight of the airplane body, the airplane bodies of different types have different weights, the required maximum bearing capacity of the main shaft 2 is different, and the applicable auxiliary undercarriage of the airplane is selected according to the known airplane type.
The driving motor adopts a permanent magnet synchronous motor, the whole transmission system of the permanent magnet synchronous motor is light in weight, unsprung weight is lighter than that of the traditional wheel axle transmission, power of unit weight is high, and a steering system such as a flexible steering frame and a single-axle steering frame is convenient to design due to the fact that no gear box is arranged, and power performance of driven equipment is improved.
The utility model discloses an automatic remote control type airplane auxiliary undercarriage, which comprises a main shaft, a steering gear, a steering connecting rod, an auxiliary connecting rod, an airplane wheel, a driving cylinder, an auxiliary cylinder, a driving motor, a controller and a digital remote control board, wherein the airplane wheel comprises a driving wheel and an auxiliary wheel, one end of the main shaft is connected with the steering gear, the other end of the main shaft is connected with a limiter, the two symmetrical ends of the steering gear are respectively connected with the steering connecting rod, and the other end of the steering connecting rod is connected with the driving wheel; the other end of the auxiliary connecting rod is connected with an auxiliary cylinder after being connected with the auxiliary wheel, and the auxiliary cylinder is connected with the main shaft; the controller is provided with a cylinder and steering gear control, positioning, speed regulation, starting braking and locking module and a power supply module; the digital remote control board is provided with a steering operation rod, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller; the limiter of the main shaft is connected with the bearing shaft of the undercarriage, and the undercarriage retracts into the undercarriage cabin. The utility model discloses realize the automatic control aircraft migration, fix a position moreover accurate error-free.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment without inventive contribution as required after reading the present specification, but all of them are protected by patent laws within the scope of the present invention.
Claims (8)
1. An automatic remote control formula aircraft assists undercarriage which characterized in that: the airplane wheel comprises a driving wheel and an auxiliary wheel, the connecting rod comprises a steering connecting rod and an auxiliary connecting rod, the cylinders comprise a driving cylinder and two auxiliary cylinders, the first end of the main shaft is connected with the steering device, the second end of the main shaft is provided with a stopper, the two symmetrical ends of the steering device are respectively connected with the steering connecting rod, and the other end of the steering connecting rod is connected with the driving wheel; the auxiliary wheel is connected with the auxiliary connecting rod, the other end of the auxiliary connecting rod is connected with the auxiliary cylinder, and the other end of the auxiliary cylinder is connected with the main shaft; the main shaft is internally provided with a driving cylinder, the controller is electrically connected with the driving cylinder, the auxiliary cylinder, the steering gear, the limiter and the driving motor, and the controller is internally provided with a cylinder control module, a steering gear control module, a positioning module, a starting module, a speed regulating module, a braking module, a locking module and a power supply module; the digital remote control board is electrically connected with the controller and is provided with a steering operating rod, a display screen, a starting brake, a positioning calibrator, a motor and a cylinder controller;
the limiting stopper is used for connecting the auxiliary aircraft landing gear and a bearing shaft of the aircraft landing gear, the driving cylinder is used for adjusting the length of the main shaft, and the auxiliary cylinder is used for retracting and releasing the auxiliary wheel; and the main shaft stopper is connected with the bearing shaft of the undercarriage, and the undercarriage retracts into the undercarriage cabin.
2. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the controller and the digital remote control board are in signal connection with the landing gear control end of the airplane.
3. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the connecting rod, the steering gear, the airplane wheel and the driving motor are all required to meet the mechanical performance of auxiliary equipment of the heavy-duty passenger airplane.
4. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the driving motor adopts a permanent magnet synchronous motor.
5. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: and a positioning module in the controller is provided with an infrared detection positioning device.
6. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the digital remote control panel displays the three-dimensional space position of the whole towed airplane in an operating state.
7. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the maximum load-bearing capacity of the main shaft is proportional to the weight of the fuselage.
8. An automatic remotely controlled aircraft auxiliary landing gear according to claim 1, wherein: the aircraft auxiliary landing gear further comprises a protective cover, and the protective cover is tightly matched with internal equipment of the aircraft auxiliary landing gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020660600.1U CN212074403U (en) | 2020-04-26 | 2020-04-26 | Automatic remote control type aircraft auxiliary undercarriage |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020660600.1U CN212074403U (en) | 2020-04-26 | 2020-04-26 | Automatic remote control type aircraft auxiliary undercarriage |
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| CN212074403U true CN212074403U (en) | 2020-12-04 |
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| CN202020660600.1U Active CN212074403U (en) | 2020-04-26 | 2020-04-26 | Automatic remote control type aircraft auxiliary undercarriage |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180092A (en) * | 2021-10-18 | 2022-03-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Launching control system of catapult plane |
-
2020
- 2020-04-26 CN CN202020660600.1U patent/CN212074403U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180092A (en) * | 2021-10-18 | 2022-03-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Launching control system of catapult plane |
| CN114180092B (en) * | 2021-10-18 | 2024-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Catapult aircraft take-off control system |
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