Landing gear system for mobile object
View Patent ↗A gear system for a mobile object may include: a first shaft unit configured to adjust a driving direction of a fuselage; a second shaft unit coupled to the first shaft unit and configured to retract the first shaft unit into the fuselage or extend the first shaft unit, retracted into the fuselage, from the fuselage; a driver configured to supply driving force through which the first shaft unit and the second shaft unit can move; and a power transmission unit configured to selectively transmit the driving force of the driver to one of the first shaft unit and the second shaft unit by coupling the driver to one of the first shaft unit and the second shaft unit.
1 . A landing gear system comprising:
a first shaft device configured to adjust a driving direction of a fuselage;
a second shaft device coupled to the first shaft device and configured to retract the first shaft device into the fuselage or extend the first shaft device from the fuselage;
a driver configured to supply driving force to operate one of the first shaft device and the second shaft device; and
a power transmission device configured to transfer the driving force of the driver to the one of the first shaft device and the second shaft device by coupling the driver to the one of the first shaft device and the second shaft device,
wherein the second shaft device comprises:
a first gear formed on at least a portion of an outer circumferential surface of a second shaft;
a second gear spaced apart from the first gear and connected to the power transmission device; and
a flexible drive transmission member configured to couple the first gear and the second gear.
2 . The landing gear system according to claim 1 , wherein the driver comprises an electric motor configured to supply the driving force to the one of the first shaft device and the second shaft device.
3 . The landing gear system according to claim 1 , wherein the flexible drive transmission member comprises a gear chain or a timing belt.
4 . The landing gear system according to claim 1 , further comprising a guide link configured to guide a path through which the first shaft device is retracted into, or extended from, the fuselage.
5 . The landing gear system according to claim 4 , wherein the guide link comprises:
a first link comprising one end coupled to the fuselage; and
a second link comprising a first end coupled to the first link and a second end coupled to the first shaft device.
6 . A landing gear system, comprising:
a first shaft device configured to adjust a driving direction of a fuselage;
a second shaft device coupled to the first shaft device and configured to retract the first shaft device into the fuselage or extend the first shaft device from the fuselage;
a driver configured to supply driving force to operate one of the first shaft device and the second shaft device; and
a power transmission device configured to transfer the driving force of the driver to the one of the first shaft device and the second shaft device by coupling the driver to the one of the first shaft device and the second shaft device;
a guide link configured to guide a path through which the first shaft device is retracted into, or extended from, the fuselage; and
a fixing unit configured to fix the first shaft device to the fuselage while the first shaft device is retracted into the fuselage,
wherein the fixing unit comprises a fixing pin protruding from at least a portion of the guide link, and
wherein in a state in which the first shaft device is retracted into the fuselage, the fixing pin is inserted into and fixed to a fixing body provided in the fuselage.
7 . The landing gear system according to claim 6 , wherein the fixing unit is configured to fix the fuselage and the guide link in a state in which the first shaft device is retracted into the fuselage.
8 . The landing gear system according to claim 6 , wherein the fixing pin comprises:
a pin body portion comprising a first end coupled to the guide link, wherein the pin body portion protrudes from the guide link to have a predetermined length; and
a pin head portion disposed at a second end of the pin body portion, wherein at least a portion of the pin head portion forms a cross-sectional area larger than a cross-sectional area of the pin body portion.
9 . The landing gear system according to claim 6 , wherein the fixing body comprises:
a fixing ring configured to form a fixing hole through which the fixing pin can penetrate; and
a stopper configured to reduce a size of the fixing hole.
10 . A landing gear system comprising:
a landing gear comprising a first shaft and a second shaft configured to rotate in different directions, wherein the first shaft is configured to change a driving direction of a fuselage, and the second shaft is configured to retract or extend the first shaft into or from the fuselage; and
a driver configured to supply driving force to rotate one of the first shaft and the second shaft,
wherein the driver comprises an electric motor configured to supply the driving force to the one of the first shaft and the second shaft,
wherein a shaft device comprises:
a first gear formed on at least a portion of an outer circumferential surface of the second shaft;
a second gear spaced apart from the first gear and connected to a power transmission device; and
a flexible drive transmission member configured to couple the first gear and the second gear.
11 . The landing gear system according to claim 10 , further comprising:
a controller configured to control the driver and the power transmission device,
wherein the controller is configured to control the power transmission device so that the power transmission device transfers the driving force of the driver to the one of the first shaft and the second shaft.
12 . The landing gear system according to claim 11 , wherein the controller is configured to control the power transmission device so that when a tire is in contact with the ground, driving force of the driver is transferred to the first shaft.
13 . The landing gear system according to claim 11 , wherein the controller is configured to control, based on a speed of the fuselage exceeding a predetermined speed, the power transmission device to decouple power transfer from the driver to the first shaft.
14 . The landing gear system according to claim 11 , wherein the controller is configured to control, based on the fuselage being taken off from the ground, the power transmission device to transfer driving force of the driver to the second shaft.
15 . The landing gear system according to claim 11 , further comprising a fixing unit configured to fix the first shaft to the fuselage in a state in which the first shaft is retracted into the fuselage,
wherein the controller is configured to control the fixing unit to fix the first shaft to the fuselage.
16 . The landing gear system according to claim 15 , wherein the controller is configured to control the power transmission device, in a state in which the first shaft is fixed to the fuselage, to decouple power transfer from the driver to the first shaft and the second shaft.