Aircraft inceptor apparatus and aircraft flight control system

A flight control system for an aircraft, comprising at least one inceptor apparatus, which is electronically or optically connected with a flight control computer system, the flight control computer system being configured to effect a flight control of the aircraft based on flight control signals or commands received from the at least one inceptor apparatus;

• wherein the at least one inceptor apparatus comprises:
• an apparatus base;
• a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, wherein the primary inceptor member is mounted at a primary inceptor member base on the apparatus base;
• a primary sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the primary inceptor member around each of two independent maneuvering axes associated to the primary inceptor member, ii) forces acting on or via the primary inceptor member in pivoting directions with respect to each of the two independent maneuvering axes associated to the primary inceptor member, and iii) lateral flexing or bending of the primary inceptor member;
• a secondary inceptor member having an actuating portion, wherein the secondary inceptor member is mounted at a secondary inceptor member base on an upper mounting portion of the primary inceptor member opposite to the primary inceptor member base;
• and
• a secondary sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the secondary inceptor member around each of two independent maneuvering axes associated to the secondary inceptor member, ii) forces acting on or via the secondary inceptor member in pivoting directions with respect to each of the two independent maneuvering axes associated to the secondary inceptor member, and iii) lateral flexing or bending of the secondary inceptor member;
• wherein the flight control computer system is configured to effect the flight control in a primary control mode based on flight control signals or commands corresponding to or being based on the electronic flight control signals or commands generated by the primary sensor assembly of the at least one inceptor apparatus and to effect the flight control in a secondary control mode based on flight control signals or commands corresponding to or being based on the electronic flight control signals or commands generated by the secondary sensor assembly of the at least one inceptor apparatus;
• wherein the flight control computer system is configured to switch between the primary control mode and the secondary control mode based on at least one further control signal or command received from the at least one inceptor apparatus;
• wherein the flight control computer system can be switched between the primary control mode and the secondary control mode by manually operating a control member of the at least one inceptor apparatus;
• wherein the control member is a movable guard member, which blocks at least one of manual access to the secondary inceptor member and an actuation of the secondary inceptor member in a blocking position and enables manual actuation of the secondary inceptor member in an enablement position;
• wherein a redundancy management functionality of the flight control computer system or a separate redundancy management controller of the flight control system is configured to switch automatically between the primary control mode and the secondary control mode based on at least one of i) monitoring at least one condition related to the at least one inceptor apparatus, ii) at least one flight control signal or command received from the at least one inceptor apparatus, iii) lack of at least one control signal or command to be received from the at least one inceptor apparatus, iv) electronic flight control signals or commands generated by the primary sensor assembly and v) electronic flight control signals or commands generated by the secondary sensor assembly;
• and
• wherein the flight control computer system or the redundancy management functionality of the flight control computer system or the redundancy management controller is configured to recognize at least one failover condition of the at least one inceptor apparatus, wherein the at least one failover condition is related at least one of the primary sensor assembly and the primary control mode and indicates a possible impairment or failure to effect the flight control based on the electronic flight control signals or commands generated by the primary sensor assembly of the at least one inceptor apparatus;
• and is configured to initiate or effect a switching over from the primary control mode to the secondary control mode upon recognizing at least one failover condition.

A flight control system for an aircraft, comprising at least one inceptor apparatus, which is electronically or optically connected with a flight control computer system, the flight control computer system being configured to effect a flight control of the aircraft based on flight control signals or commands received from the at least one inceptor apparatus;

• wherein the at least one inceptor apparatus comprises:
• an apparatus base;
• a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, wherein the primary inceptor member is mounted at a primary inceptor member base on the apparatus base;
• a primary sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the primary inceptor member around each of two independent maneuvering axes associated to the primary inceptor member, ii) forces acting on or via the primary inceptor member in pivoting directions with respect to each of the two independent maneuvering axes associated to the primary inceptor member, and iii) lateral flexing or bending of the primary inceptor member;
• a secondary inceptor member having an actuating portion, wherein the secondary inceptor member is mounted at a secondary inceptor member base on an upper mounting portion of the primary inceptor member opposite to the primary inceptor member base;
• and
• a secondary sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the secondary inceptor member around each of two independent maneuvering axes associated to the secondary inceptor member, ii) forces acting on or via the secondary inceptor member in pivoting directions with respect to each of the two independent maneuvering axes associated to the secondary inceptor member, and iii) lateral flexing or bending of the secondary inceptor member;
• wherein the flight control computer system is configured to effect the flight control in a primary control mode based on flight control signals or commands corresponding to or being based on the electronic flight control signals or commands generated by the primary sensor assembly of the at least one inceptor apparatus and to effect the flight control in a secondary control mode based on flight control signals or commands corresponding to or being based on the electronic flight control signals or commands generated by the secondary sensor assembly of the at least one inceptor apparatus;
• wherein the flight control computer system is configured to switch between the primary control mode and the secondary control mode based on at least one further control signal or command received from the at least one inceptor apparatus;
• wherein the flight control computer system can be switched between the primary control mode and the secondary control mode by manually operating a control member of the at least one inceptor apparatus;
• wherein the control member is a movable guard member, which blocks at least one of manual access to the secondary inceptor member and an actuation of the secondary inceptor member in a blocking position and enables manual actuation of the secondary inceptor member in an enablement position;
• and
• wherein the flight control system is configured such that the primary control mode is a normal control mode, in which the flight control of the aircraft is based on input provided by a pilot by the primary inceptor member, and that the secondary control mode is a redundancy control mode, in which the flight control is based on pilot input provided by the pilot by means of the secondary inceptor member, so that the secondary inceptor member redundantly enables pilot input in case the pilot input by the primary inceptor member fails.