Disclosed is a helicopter having a longitudinal axis, a lateral axis and a vertical axis, a helicopter centre of mass and a maximum gross mass of less than 5000 kg, the helicopter comprising a fuselage elongate along the longitudinal axis, the fuselage comprising an aerodynamically shaped shell defining a front, a rear, a top and a bottom of the fuselage and a passenger cabin therein having two forward-facing front seating positions for the pilot and a co-pilot or a passenger, and forward-facing rear seating positions for at least 2 passengers, optionally 3 passengers; a primary fuel cell mounted substantially behind the passenger cabin; the front seating position for the pilot having a centre of mass at a first location substantially in front of the rotor hub location, and the primary fuel cell having a centre of mass at a second location substantially behind the rotor hub location; a landing gear arrangement; a power plant mounted substantially above and behind the passenger cabin, wherein the primary fuel cell is arranged to provide fuel to the power plant; and a secondary fuel cell having a centre of mass at a nose location in front of the rotor hub location by at least 1500 mm.
Disclosed is a collective control arrangement for a helicopter having a plurality of rotor blades, the collective control arrangement comprising: an armrest for a pilots seat, the armrest comprising an elongate channel; and a collective handle comprising: a first end slidably disposed in the elongate channel for coupling to one or more helicopter actuators that control collective pitch of the plurality of rotor blades; and a second end for gripping by a pilot. Advantageously the armrest comprises an elbow support portion configured to be located backwards of the hollow when the armrest is installed in the helicopter.
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
A light helicopter typically for 5 occupants is disclosed which achieves a hitherto unprecedented combination of range, speed and payload by adopting a novel approach to construction and positioning of components which affect overall aerodynamics in forward flight at speeds in excess of 70 metres per second and mass distribution and management of centre of gravity as fuel is consumed, load bearing strength and drag.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 41/00 - Power installations for auxiliary purposes
Disclosed is an autopilot system for a helicopter, the helicopter having: a cyclic and a collective that are physically coupled to helicopter actuators that control cyclic and collective pitch of main rotor blades of the helicopter and anti-torque pedals that are physically coupled to helicopter actuators that control the pitch of tail rotor blades of the helicopter; and at least one servomechanism configured to amplify force applied by the pilot to the cyclic, collective and/or anti-torque pedals; wherein the autopilot system comprises an autopilot actuator configured to: in an autopilot mode, control direction or orientation of the helicopter by applying force to a control link that is physically coupled to one of the helicopter actuators; and in a manual mode, provide stability or control augmentation by applying a force on one of the cyclic, the collective or one or both of the anti-torque pedals to influence the pilot's inputs to urge the helicopter away from a particular flight condition dependent on monitored aircraft parameters.
Disclosed is a ground movement system for a helicopter having a fuselage and rotor blades fixed to the top of the fuselage, the ground movement system comprising at least three wheels secured below the fuselage of the helicopter, the wheels being retractable during flight; a motor positioned in the hub or on the undercarriage leg of each of at least two of the wheels, wherein each motor is operable to rotate the wheel in forward and backward directions; wherein each motor allows the wheel to rotate freely when unpowered; at least one user interface operable to receive user input commands to control the speed and direction of travel of the helicopter using the ground movement system; and a control arrangement to provide control signals to each of the motors based on the user input commands.
Disclosed is a pitch and roll control arrangement for controlling both lateral and longitudinal orientation of an aircraft having at least one pilots seat, wherein the control arrangement comprises a handle (5110) positionable substantially above the pilot's seat and shaped to be gripped by a pilot (10); an elongate connector (5112) that extends in a generally forward direction from the handle portion to a forward joint; an elongate transverse arm (5116) extending generally transversely from the forward joint of the connector to a mounting location forward and to the side of the pilot in use; a mounting arrangement configured to support the transverse arm at the mounting location to permit the transverse arm to move laterally sideways and fore and aft and to constrain the forward joint to move generally horizontally as the handle is moved fore and aft and laterally by the pilot; a control coupling associated with the mounting arrangement arranged to provide at least one moving connection which moves in response to fore and aft movement and lateral movement of the handle for coupling to actuators of the aircraft.
B64D 43/00 - Arrangements or adaptations of instruments
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
Disclosed is a pilot aircraft system control input arrangement for a light aircraft having primary flight controls, the pilot aircraft system control input arrangement integrated into an armrest for a pilot's seat, the armrest providing forearm support for a pilot and having integrated therein or associated therewith a primary flight control and wherein the pilot aircraft system control input arrangement is disposed to be reached by fingers of a pilot with their forearm resting on the armrest, the pilot system control input arrangement comprising: a numerical keypad interface for inputting data; a rotatable selector for inputting data; a function selector operable to switch the pilot input arrangement between at least two input functions that each enable the pilot input arrangement to receive a different type of input, wherein the types of input for the at least two input functions are selected from at least two of the following input categories: a pressure setting for an altimeter; a transponder code for a transponder; a frequency for radio or navigation equipment; a course or heading for an autopilot or navigation equipment; an interfacing arrangement for communicating inputs to at least two aircraft systems selected from: an altimeter; a transponder; a radio; a navigation system; and an autopilot system.
The present disclosure relates to an instrument for an aircraft which is found to be particularly effective in alerting a pilot to departures from safe flight conditions and which is expected to reduce the incidence of accidents, particularly in less experienced pilots in high workload situations. It is particularly useful in helicopters but may be used in fixed wing aircraft also.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
A light helicopter typically for 5 occupants is disclosed which achieves a hitherto unprecedented combination of range, speed and payload by adopting a novel approach to construction and positioning of components which affect overall aerodynamics in forward flight at speeds in excess of 70 metres per second and mass distribution and management of centre of gravity as fuel is consumed, load bearing strength and drag.
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
F16H 3/00 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
Disclosed is an autopilot system for a helicopter, the helicopter having: a cyclic and a collective that are physically coupled to helicopter actuators that control cyclic and collective pitch of main rotor blades of the helicopter and anti-torque pedals that are physically coupled to helicopter actuators that control the pitch of tail rotor blades of the helicopter; and at least one servomechanism configured to amplify force applied by the pilot to the cyclic, collective and/or anti-torque pedals; wherein the autopilot system comprises an autopilot actuator configured to: in an autopilot mode, control direction or orientation of the helicopter by applying force to a control link that is physically coupled to one of the helicopter actuators; and in a manual mode, provide stability or control augmentation by applying a force on one of the cyclic, the collective or one or both of the anti-torque pedals to influence the pilot's inputs to urge the helicopter away from a particular flight condition dependent on monitored aircraft parameters.
Disclosed is a helicopter having a longitudinal axis, a lateral axis and a vertical axis, a helicopter centre of mass and a maximum gross mass of less than 5000kg, the helicopter comprising a fuselage elongate along the longitudinal axis, the fuselage comprising an aerodynamically shaped shell defining a front, a rear, a top and a bottom of the fuselage and a passenger cabin therein having two forward-facing front seating positions for the pilot and a co-pilot or a passenger, and forward-facing rear seating positions for at least 2 passengers, optionally 3 passengers; a primary fuel cell mounted substantially behind the passenger cabin; the front seating position for the pilot having a centre of mass at a first location substantially in front of the rotor hub location, and the primary fuel cell having a centre of mass at a second location substantially behind the rotor hub location; a landing gear arrangement; a power plant mounted substantially above and behind the passenger cabin, wherein the primary fuel cell is arranged to provide fuel to the power plant; and a secondary fuel cell having a centre of mass at a nose location in front of the rotor hub location by at least 1500mm.
Disclosed is a pitch and roll control arrangement for controlling both lateral and longitudinal orientation of an aircraft having at least one pilot's seat, wherein the control arrangement comprises a handle (5110) positionable substantially above the pilot's seat and shaped to be gripped by a pilot (10); an elongate connector (5112) that extends in a generally forward direction from the handle portion to a forward joint; an elongate transverse arm (5116) extending generally transversely from the forward joint of the connector to a mounting location forward and to the side of the pilot in use; a mounting arrangement configured to support the transverse arm at the mounting location to permit the transverse arm to move laterally sideways and fore and aft and to constrain the forward joint to move generally horizontally as the handle is moved fore and aft and laterally by the pilot; a control coupling associated with the mounting arrangement arranged to provide at least one moving connection which moves in response to fore and aft movement and lateral movement of the handle for coupling to actuators of the aircraft.
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
Disclosed is a collective control arrangement for a helicopter having a plurality of rotor blades, the collective control arrangement comprising: an armrest for a pilot's seat, the armrest comprising an elongate channel; and a collective handle comprising: a first end slidably disposed in the elongate channel for coupling to one or more helicopter actuators that control collective pitch of the plurality of rotor blades; and a second end for gripping by a pilot. Advantageously the armrest comprises an elbow support portion configured to be located backwards of the hollow when the armrest is installed in the helicopter.
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
Disclosed is a pilot aircraft system control input arrangement for a light aircraft having primary flight controls, the pilot aircraft system control input arrangement integrated into an armrest for a pilot's seat, the armrest providing forearm support for a pilot and having integrated therein or associated therewith a primary flight control and wherein the pilot aircraft system control input arrangement is disposed to be reached by fingers of a pilot with their forearm resting on the armrest, the pilot system control input arrangement comprising: a numerical keypad interface for inputting data; a rotatable selector for inputting data; a function selector operable to switch the pilot input arrangement between at least two input functions that each enable the pilot input arrangement to receive a different type of input, wherein the types of input for the at least two input functions are selected from at least two of the following input categories: a pressure setting for an altimeter; a transponder code for a transponder; a frequency for radio or navigation equipment; a course or heading for an autopilot or navigation equipment; an interfacing arrangement for communicating inputs to at least two aircraft systems selected from: an altimeter; a transponder; a radio; a navigation system; and an autopilot system.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
Disclosed is a ground movement system for a helicopter having a fuselage and rotor blades fixed to the top of the fuselage, the ground movement system comprising at least three wheels secured below the fuselage of the helicopter, the wheels being retractable during flight; a motor positioned in the hub or on the undercarriage leg of each of at least two of the wheels, wherein each motor is operable to rotate the wheel in forward and backward directions; wherein each motor allows the wheel to rotate freely when unpowered; at least one user interface operable to receive user input commands to control the speed and direction of travel of the helicopter using the ground movement system; and a control arrangement to provide control signals to each of the motors based on the user input commands.
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