System for maneuvering an aircraft landing gear and aircraft comprising same
View Patent ↗The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control channel for the hatches ( 16 ), a control channel for the landing gear ( 15 ), the general control unit, the hatch control channel and the landing gear control channel being controlled by an electric power source, when the aircraft is in normal operating conditions, emergency operating conditions and in maintenance phase. The invention also concerns an aircraft comprising such a system.
1. A system for maneuvering a landing gear of an aircraft mounted so as to be hinged in a gear compartment closed by a set of doors, comprising:
a general control unit of the gear compartment to trigger the different maneuvers;
a door control channel;
a landing-gear control channel; and
a single commonly shared system for controlling the landing gear and the set of doors, the single commonly shared system configured to be implemented in each of a normal operation, an emergency operation and a maintenance phase of the aircraft, the single commonly shared system comprising the general control unit, the door control channel and the landing-gear control channel such that the single commonly shared system is controlled by a single source of electrical energy in each of the normal operation, the emergency operation and the maintenance phase,
and wherein the door control channel and the gear control channel being each connected to the general control unit solely by an electrical link and being capable of receiving control commands sent by the general control unit according to a predetermined sequencing.
2. A system according to claim 1 , wherein the door control channel comprises at least one electrically controlled door-locking device, at least one door-actuation unit and one electrically controlled unit to control the actuation unit.
3. A system according to claim 2 , wherein the door control channel comprises at least one electrical actuating mechanism associated with the door-locking device and one electrical actuating mechanism associated with the control unit for the door actuation unit.
4. A system according to claim 2 , wherein the door control channel comprises an electrical control unit placed outside the aircraft, activating the opening of the main door in maintenance phase.
5. A system according to claim 1 , wherein the gear control channel comprises at least one electrically controlled landing-gear holding device, at least one gear actuation unit and one electrically controlled unit to control the actuation unit.
6. A system according to claim 5 , wherein the gear control channel comprises at least one electrical actuating mechanism associated with the gear-holding device and one electrical actuating mechanism associated with the control unit for the gear actuating unit.
7. A system according to claim 1 wherein, in normal operation, the source of energy is an available general electrical power supply of the aircraft.
8. A system according to claim 1 wherein, in emergency operation, the source of energy is a general electrical supply of the aircraft or a secondary electrical source of the aircraft, comprising a propeller.
9. A system according to claim 1 wherein, in the maintenance phase, the source of energy is an available electrical source of the aircraft or an auxiliary electrical source on the ground.
10. A system according to claim 1 , wherein the electrical link between the general control unit and the door control and gear control channels is a wire link.
11. A system according to claim 1 , wherein the general control unit provides for a sequencing in the actuation of the door-locking and gear-holding device and in the actuation units.
12. An aircraft comprising a retractable landing gear, comprising a system for maneuvering the landing gear according to claim 1 .