CN-122009475-A - Interconnected landing gear system, aircraft and cooperative control method thereof

CN122009475ACN 122009475 ACN122009475 ACN 122009475ACN-122009475-A

Abstract

The present disclosure provides an interconnected landing gear system, an aircraft, and a cooperative control method thereof. The interconnected landing gear system comprises a plurality of landing gears, wherein each landing gear comprises an oil-gas shock absorption strut, a hydraulic pipeline, at least one control valve and a controller, the oil-gas shock absorption strut is provided with an oil cavity, an air cavity and a piston rod which can extend and retract along the axial direction of the oil-gas shock absorption strut, the hydraulic pipeline is communicated with the oil cavities of at least two landing gears, the at least one control valve is arranged on the hydraulic pipeline, and the controller is configured to control the control valve on the hydraulic pipeline between a first oil cavity of the landing gear in contact with the ground and a second oil cavity of at least one suspended landing gear to be opened when at least one landing gear is in contact with the ground and other landing gears are suspended, so that the first oil cavity is communicated with the second oil cavity, the oil in the first oil cavity flows to the second oil cavity, the piston rod of the suspended landing gear is driven to extend, and the load of the landing gear system is balanced.

Inventors

ZHU JIANXIN
LI FUYOU
GUO YONG
Ma Zhanhao
HE DONGZE

Assignees

山河智能装备股份有限公司

Dates

Publication Date: 20260512
Application Date: 20260324

Claims (10)

1. An interconnected landing gear system, comprising: A plurality of landing gears, each landing gear comprising an oil and gas shock strut having an oil cavity, an air cavity, and a piston rod that is retractable along an axial direction of the oil and gas shock strut; the hydraulic pipeline is communicated with the oil cavities of at least two landing gears; at least one control valve disposed in the hydraulic line; And the controller is configured to control a control valve on a hydraulic pipeline between a first oil cavity of the landing gear in contact with the ground and a second oil cavity of the at least one suspended landing gear to be opened under the condition that at least one landing gear is in contact with the ground and other landing gears are suspended, so that the first oil cavity is communicated with the second oil cavity, oil in the first oil cavity flows to the second oil cavity, a piston rod of the suspended landing gear is driven to extend, and the load of the interconnected landing gear system is balanced.
2. The interconnected landing gear system of claim 1, further comprising: A plurality of sets of sensors configured to acquire oil pressures of the plurality of oil chambers and displacement of the piston rod, respectively; the controller includes: and the judging module is configured to determine the landing gear in contact with the ground and the suspended landing gear according to the oil pressure, the displacement and the combination of the body posture information and the acceleration information.
3. The interconnected landing gear system of claim 2, wherein the controller further comprises: a determining module configured to determine a target oil pressure range and a target displacement range of the plurality of oil chambers based on the plurality of oil pressures, the plurality of displacements, the body posture information, and the acceleration information, to determine an opening degree of at least one of the control valves based on the plurality of target oil pressure ranges and the target displacement ranges, to change a flow resistance of the oil, to maintain the oil pressures in the plurality of oil chambers in the target oil pressure ranges, and to maintain displacements of the plurality of piston rods in the target displacement ranges.
4. An interconnected landing gear system according to claim 3, wherein the determination module comprises: A storage unit configured to store a relationship table of a relationship of flight attitude information, acceleration information, a target oil pressure range, and a target displacement range; And a searching unit configured to search the target oil pressure range and the target displacement range from the relation table according to the flight attitude information and the acceleration information.
5. The interconnected landing gear system of claim 1, wherein a plurality of the landing gears comprise: Two main landing gears; the hydraulic pipeline at least comprises a first pipeline connecting the front landing gear oil cavity and at least one main landing gear oil cavity, and a second pipeline connecting the two main landing gear oil cavities.
6. The interconnected landing gear system of claim 1, further comprising: And the energy accumulator is connected to the hydraulic pipeline and is suitable for absorbing or releasing hydraulic oil so as to inhibit pressure fluctuation in the hydraulic pipeline and temporarily store part of hydraulic energy.
7. The interconnected landing gear system of claim 1, further comprising: The hydraulic energy conversion unit is arranged on the hydraulic pipeline and is suitable for driving oil to flow in the hydraulic pipeline so as to adjust the posture of the landing gear.
8. The interconnected landing gear system of claim 7, wherein the hydraulic energy conversion unit is further configured to convert kinetic energy of the oil to electrical energy for storage.
9. An air-craft having the function of providing a plurality of air-craft units, characterized by comprising the following steps: A body; an interconnected landing gear system according to any of claims 1 to 8, mounted beneath the fuselage.
10. A method of cooperative control of an interconnected landing gear system according to any of claims 1 to 8, comprising: acquiring pressure, piston rod displacement and fuselage posture and acceleration information of oil cavities of a plurality of landing gears; Determining landing gear and suspended landing gear which are in contact with the ground according to the pressure of the oil cavities of the landing gear, the displacement of the piston rod and the information of the posture and acceleration of the landing gear; Under the condition that at least one landing gear is in contact with the ground and other landing gears are suspended, a control valve on a hydraulic pipeline between a first oil cavity of the landing gear in contact with the ground and a second oil cavity of the at least one suspended landing gear is controlled to be opened, so that the first oil cavity is communicated with the second oil cavity, oil in the first oil cavity flows to the second oil cavity, a piston rod of the suspended landing gear is driven to extend, and the load of the interconnected landing gear system is balanced.

Description

Interconnected landing gear system, aircraft and cooperative control method thereof Technical Field At least one embodiment of the present disclosure relates to the field of aircraft technology, and more particularly, to an interconnected landing gear system, an aircraft, and a cooperative control method for the interconnected landing gear system. Background The main landing gear and the nose landing gear of an aircraft are typically equipped with separate hydro-pneumatic shock struts as a cushioning system. The basic principle of the buffering system is that in the landing impact and ground running process, the landing gear strut is compressed, oil in the oil cavity flows through the fixed orifice to generate damping, and meanwhile gas in the air cavity is compressed, so that impact kinetic energy is converted into heat energy and dissipated. However, such independent passive cushioning systems have the disadvantage that the energy dissipation of the system is single and each landing gear can only handle the impact energy to which it is subjected. Disclosure of Invention In view of this, the present disclosure provides an interconnected landing gear system, an aircraft, and a cooperative control method of the interconnected landing gear system, capable of balancing the load of the interconnected landing gear system. As a first aspect of an embodiment of the present disclosure, there is provided an interconnected landing gear system, comprising a plurality of landing gears, each landing gear including an oil and gas shock strut having an oil chamber, an air chamber, and a piston rod that is retractable in an axial direction of the oil and gas shock strut, a hydraulic line that communicates with the oil chambers of at least two landing gears, at least one control valve disposed in the hydraulic line, and a controller configured to control, in a case where at least one landing gear is in contact with the ground and the other landing gear is suspended, a control valve on the hydraulic line between the first oil chamber of the landing gear in contact with the ground and the second oil chamber of the at least one suspended landing gear to open so that the first oil chamber communicates with the second oil chamber, so that the oil flow in the first oil chamber is directed toward the second oil chamber to drive the piston rod of the suspended landing gear to extend, equalizing a load of the interconnected landing gear system. According to an embodiment of the disclosure, the interconnected landing gear system further comprises a plurality of groups of sensors configured to acquire oil pressures of the plurality of oil chambers and displacement of the piston rod, respectively, and the controller comprises a judging module configured to determine landing gear in contact with the ground and suspended landing gear according to the plurality of oil pressures, the plurality of displacements and combined with the body attitude information and the acceleration information. According to an embodiment of the present disclosure, the controller further includes a determining module configured to determine a target oil pressure range and a target displacement range of the plurality of oil chambers based on the plurality of oil pressures, the plurality of displacements, the body posture information, and the acceleration information, to determine an opening degree of at least one of the control valves based on the plurality of target oil pressure ranges and the target displacement ranges, to change a flow resistance of the oil, to maintain the oil pressures in the plurality of oil chambers in the target oil pressure ranges, and to maintain the displacements of the plurality of piston rods in the target displacement ranges. According to the embodiment of the disclosure, the determining module comprises a storage unit and a searching unit, wherein the storage unit is configured to store a relation table of the relation among the flight attitude information, the acceleration information, the target oil pressure range and the target displacement range, and the searching unit is configured to search the target oil pressure range and the target displacement range from the relation table according to the flight attitude information and the acceleration information. According to an embodiment of the disclosure, the plurality of landing gears includes two main landing gears, the nose landing gear, the hydraulic line includes at least a first line connecting the nose landing gear oil chamber with at least one main landing gear oil chamber, and a second line connecting the two main landing gear oil chambers. According to an embodiment of the present disclosure, the interconnected landing gear system further includes an accumulator coupled to the hydraulic line and adapted to absorb or release hydraulic oil to dampen pressure fluctuations within the hydraulic line and temporarily store a portion of the hydraulic energy. According to an embo