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公开(公告)号：US20220185455A1
公开(公告)日：2022-06-16
申请号：US17550006
申请日：2021-12-14
申请人： DASSAULT AVIATION
摘要： A piloting device for piloting an aircraft comprises a first and a second control stick mounted movable on a support. The device comprises a priority selection module configured to switch the first and second control sticks between a piloting configuration and a non-piloting configuration. The device further comprises a detection system for detecting the positions of the first and second control sticks; a first and second actuation system configured to generate respective first and second forces on the respective first and second control stick; and a control module configured to control the actuation system of the control stick which is in a non-piloting configuration such that the positions of the control sticks are identical.
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2.发明申请公开(公告)号：US20220340294A1
公开(公告)日：2022-10-27
申请号：US17724662
申请日：2022-04-20
申请人： DASSAULT AVIATION
发明人： Jérôme LE BORLOCH , François PINEAU
摘要： A command device for controlling a mechanical energy reduction assembly of an aircraft, movable between an inactive configuration and a maximum mechanical energy reduction configuration, includes a rocker button, movable between a mechanical energy reduction assembly configuration maintaining position, a first position of incremental movement of the mechanical energy reduction assembly to its maximum mechanical energy reduction configuration and a second position of incremental movement of the mechanical energy reduction assembly to its inactive configuration. The command device further includes at least one return element configured to return the rocker button to its maintaining position.
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公开(公告)号：US20220340261A1
公开(公告)日：2022-10-27
申请号：US17724653
申请日：2022-04-20
申请人： DASSAULT AVIATION
发明人： Jérôme LE BORLOCH , François PINEAU
摘要： A control system is for a high lift assembly of an aircraft. The assembly is controllable in two aerodynamic configurations each with different lift. The control system includes a manual control device operable by a pilot of the aircraft. The manual control device includes at least one member movable relative to a base body. The movable member can be moved relative to the base body between a rest position, a first position and a second distinct position. The manual control device includes a resilient return device for the movable member in the rest position. The manual control device issues a signal when the movable member reaches either the first or second position, to move the high lift assembly between two of the aerodynamic configurations.
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公开(公告)号：US20220185454A1
公开(公告)日：2022-06-16
申请号：US17549992
申请日：2021-12-14
申请人： DASSAULT AVIATION
发明人： Jérôme LE BORLOCH
摘要： A piloting device for piloting an aircraft includes a first and a second control stick movably mounted on a support, a detection system for detecting the positions of the first and second control sticks, an elastic mechanism configured to apply a restoring force to the second control stick, first and second actuation systems configured to apply respective first and second position adjustment forces to the respective first and second control sticks, and a control module configured to control the second adjustment force so that the positions of the first and second control sticks are identical. The control module is configured to control the first adjustment force based on the second adjustment force and the restoring force.
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5.发明申请公开(公告)号：US20180155008A1
公开(公告)日：2018-06-07
申请号：US15809388
申请日：2017-11-10
申请人： DASSAULT AVIATION
发明人： Jérôme LE BORLOCH
CPC分类号： B64C13/0425 , B64D31/04 , B64D43/00 , B64D45/00 , G05G1/04
摘要： A device for managing the mechanical energy of an aircraft, having a light system, includes a support defining a guide; at least one control lever for varying the mechanical energy of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the control lever in the guide, configured to create position information for the position of the control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes at least one light strip extending on the support along at least part of the travel of the control lever in the guide; and a control unit of the at least one light strip, configured to display at least one light indication at least at one given point of the lighted position ramp calculated as a function of a movement context of the aircraft.
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公开(公告)号：US20180134404A1
公开(公告)日：2018-05-17
申请号：US15809385
申请日：2017-11-10
申请人： DASSAULT AVIATION
发明人： Eric GRANIER , Jérôme LE BORLOCH
IPC分类号： B64D31/04
CPC分类号： B64D31/04 , B64C13/503 , B64C13/506 , B64C13/507 , B64D31/14
摘要： A device for managing the mechanical energy of an aircraft, with a force application system on a control lever, includes a support defining a guide; a moving control lever for controlling varying a mechanical energy variation of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the moving lever in the guide, configured to create position information for the position of the moving lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an active force applicator for applying a force on the moving lever, configured to generate a force applied on the moving lever. The force depends on the position of the moving lever in the guide.
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公开(公告)号：US20180134403A1
公开(公告)日：2018-05-17
申请号：US15809374
申请日：2017-11-10
申请人： DASSAULT AVIATION
发明人： Eric GRANIER , Jérôme LE BORLOCH
IPC分类号： B64D31/04
摘要： A device for managing the mechanical energy of an aircraft, having an energy management auxiliary system, includes a support defining a guide, a centralized control lever for varying the energy of the aircraft, at least one position sensor detecting the position of the centralized control lever in the guide. The position sensor is configured to create position information for the position of the centralized control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an auxiliary support; for the or each motor of the aircraft, an individual control lever for the individual propulsion of the motor, mounted movably in the auxiliary support; and at least one auxiliary position sensor detecting the position of the or each individual lever configured to generate information intended to be sent to the flight control unit of the aircraft.
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