Abstract: An aircraft landing gear bay door 140 including an attachment mechanism suitable for pivotally mounting the door to an aircraft, a first side 141 arranged to face inwardly in relation to the aircraft landing gear bay when the door is closed and face towards one side of a main leg of the landing gear when the door is open and the landing gear is deployed, and a second opposite side 142. The shape formed from the first and second sides provides an aerofoil profile of the door. The invention also provides an aircraft landing gear arrangement 100, an aircraft 1000, methods of operating an aircraft and a method of reducing noise.

Abstract: An automated food processing machine includes a receptacle, a slitter assembly, and a controller. The slitter assembly is coupled to a first motion actuator and includes a third motion actuator coupled to a slitter blade. In response to an input signal, the controller is configured to (1) actuate the first motion actuator to translate the slitter assembly along a first axis until the slitter blade has penetrated into a whole fruit or vegetable, and (2) actuate the third motion actuator to move the slitter blade relative to the slitter assembly with a component along an axis that is not parallel to the first axis.

Abstract: An aerodynamic body for use on an aircraft including at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations. The ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position, the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

Abstract: An automated food processing machine includes a receptacle, a slitter assembly, and a controller. The slitter assembly is coupled to a first motion actuator and includes a third motion actuator coupled to a slitter blade. In response to an input signal, the controller is configured to (1) actuate the first motion actuator to translate the slitter assembly along a first axis until the slitter blade has penetrated into a whole fruit or vegetable, and (2) actuate the third motion actuator to move the slitter blade relative to the slitter assembly with a component along an axis that is not parallel to the first axis.

Abstract: An automated food processing machine receives a whole fruit or vegetable and presses it through a blade set to form slices or wedges. The machine includes a controller coupled to various components including linear motion actuators, a user interface, and sensors. One motion actuator coupled to a slitting blade. Another motion actuator is coupled to a ram. In response to an input the controller activates the motion actuators in a sequence including (1) linear motion of the slitting blade to form a slit in the whole fruit or vegetable and (2) linear motion of the ram to press the whole fruit or vegetable through a blade set to form the slices or wedges.

Abstract: An aerodynamic body for use on an aircraft including at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations. The ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position, the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

Abstract: A System and Method for Driver Risk Assessment through Continuous Performance Monitoring. The system and method analyzes the full sensor data stream emanating from a vehicle when being driven. The system and method is configurable to rely upon either onboard sensors or the user's smartphone to alert the data capture systems that a driving trip has started or stopped. The system relies on the data contained within the stream to generate the driver's score, rather than upon events resulting from the sensors exceeding a threshold value. The method takes the flow of data and generate scores for sub-sets of the data stream of a standard length so that each user's driving performance can be compared to other drivers being monitored by the method and system.

Abstract: A System and Method for Driver Risk Assessment through Continuous Performance Monitoring. The system and method analyzes the full sensor data stream emanating from a vehicle when being driven. The system and method is configurable to rely upon either onboard sensors or the user's smartphone to alert the data capture systems that a driving trip has started or stopped. The system relies on the data contained within the stream to generate the driver's score, rather than upon events resulting from the sensors exceeding a threshold value. The method takes the flow of data and generate scores for sub-sets of the data stream of a standard length so that each user's driving performance can be compared to other drivers being monitored by the method and system.

Abstract: An automated food processing machine receives a whole fruit or vegetable and presses it through a blade set to form slices or wedges. The machine includes a controller coupled to various components including linear motion actuators, a user interface, and sensors. One motion actuator coupled to a slitting blade. Another motion actuator is coupled to a ram. In response to an input the controller activates the motion actuators in a sequence including (1) linear motion of the slitting blade to form a slit in the whole fruit or vegetable and (2) linear motion of the ram to press the whole fruit or vegetable through a blade set to form the slices or wedges.

Abstract: An automated food processing machine receives a whole fruit or vegetable and presses it through a blade set to form slices or wedges. The machine includes a controller coupled to various components including linear motion actuators, a user interface, and sensors. One motion actuator coupled to a slitting blade. Another motion actuator is coupled to a ram. In response to an input the controller activates the motion actuators in a sequence including (1) linear motion of the slitting blade to form a slit in the whole fruit or vegetable and (2) linear motion of the ram to press the whole fruit or vegetable through a blade set to form the slices or wedges.

Abstract: An automated food processing machine receives a whole fruit or vegetable and presses it through a blade set to form slices or wedges. The machine includes a controller coupled to various components including linear motion actuators, a user interface, and sensors. One motion actuator coupled to a slitting blade. Another motion actuator is coupled to a ram. In response to an input the controller activates the motion actuators in a sequence including (1) linear motion of the slitting blade to form a slit in the whole fruit or vegetable and (2) linear motion of the ram to press the whole fruit or vegetable through a blade set to form the slices or wedges.

Abstract: An aircraft slat deployment mechanism including a first drive member coupled to a slat at a first pivot point and a second drive member coupled to the slat at a second pivot point offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion is carried by the drive shaft. The first pinion is arranged to transmit mechanical power from the drive shaft to the first drive member via the first rack. A second rack is provided on the second drive member, and a second pinion is carried by the drive shaft. The second pinion has a different radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the first and second drive members move at a different speed.

Abstract: An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.

Abstract: An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.

Abstract: An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.

Abstract: An aircraft slat deployment mechanism comprising: a first drive member coupled to the slat at a first pivot point; and a second drive member coupled to the slat at a second pivot point which is offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion is carried by the drive shaft. The first pinion is arranged to transmit mechanical power from the drive shaft to the first drive member via the first rack. A second rack is provided on the second drive member, and a second pinion is carried by the drive shaft. The second pinion has a different radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the second drive member moves at a different speed to the first drive member.

Abstract: An aircraft comprises a wing having a positive dihedral, the wing comprising a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.