Abstract: A method of landing an aircraft in which the aircraft receives information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the aircraft; determines a landing plan of the aircraft based on the information; and lands the aircraft based on the landing plan. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack.

Abstract: An aircraft control system (100) including an input interface (102), an output interface (114) and a processing engine (108) having a classifier (110) that applies input data (104) generated by the input interface (102) to generate output control data (112). The classifier (110) has a plurality of parameters which represent a control policy for operating the aircraft (800). The output interface (114) generates control outputs to control the aircraft (800) based on the output control data (112). A machine learning system (900) for training the classifier (110) including an environment (902), a pathway evaluation engine (904), storage (906), and a training engine (908). The machine learning system (900) generates training data (912) by selecting a pathway representing an operating procedure using the pathway evaluation engine (904). The training engine (908) trains the classifier (110) using the training data (912).

Abstract: An aircraft braking system for an aircraft, the aircraft including first and second brakes, and first and second energy distribution systems for delivering energy to the first and second brakes to operate the respective first and second brakes. The aircraft braking system is switchable between: a first configuration, in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake; and a second configuration, in which the first energy distribution system is coupled to both the first and second brakes.

Abstract: An aircraft controller 5, aircraft braking system 13 and method for determining braking parameters. The aircraft controller 5 is configured to determine information associated with an aircraft taxiing route associated with an aircraft 1. On the basis of the information, the aircraft controller 5 determines a first braking parameter for a first main landing gear 8 of the aircraft 1 and a second braking parameter for a second main landing gear 9 of the aircraft 1 during a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the first 8 and second 9 main landing gears during the landing event.

Abstract: A speed determination system for an aircraft including one or more interfaces arranged to receive first speed data from a first speed measurement system and second speed data from a second speed measurement system. The first speed measurement system provides the first speed data using global positioning system data. The second speed measurement system provides the second speed data based on a second speed measurement. The speed determination system includes a processor arranged to determine whether the data received from the first speed measurement system is reliable. If global positioning data is determined to be reliable, the speed determination system determines a speed from the first speed data and determines correction values for the second speed measurement system. If global positioning data is determined to be unreliable, the speed determination system determines a speed from the second speed data and the correction values.

Abstract: An aircraft braking controller for an aircraft, the aircraft braking controller configured to determine a position of at least a part of a landing gear of the aircraft during retraction of the landing gear into the aircraft, and control braking of a wheel of the landing gear based on the position determined.

Abstract: An aircraft system having a first set of components for performing a function of the aircraft system, and a second, alternative, set of components for performing the function of the aircraft system. The aircraft system has and a controller configured to receive scenario data indicative of a scenario during which the function of the aircraft system is to be performed, and, where each of the first and second sets of components are operational, the controller is configured to select between the first or the second set of components to perform the aircraft system function during the scenario based on the received scenario data. The controller is configured to control the selected set of components to perform the function during the scenario.

Abstract: A method of testing a system model is disclosed. The system model includes a system parameter and three or more equipment models, each equipment model includes an equipment parameter which models a parameter of a respective equipment. The method includes (a) making a series of changes of the equipment parameter of one of the equipment models so that the equipment parameter of the one of the equipment models adopts a series of test values of the equipment parameter; (b) operating the system model to determine a series of test values of the system parameter, each test value of the system parameter is determined in accordance with a respective one of the test values of the equipment parameter; (c) determining a weight of the selected one of the equipment models, the weight of the one of the equipment models indicates a sensitivity of the system parameter to the series of changes in the equipment parameter of the one of the equipment models; and (d) outputting the weight of the one of the equipment models.

Abstract: A hydraulic system 300 for an aircraft including a backup hydraulic pressure source 216 to provide hydraulic pressure to a brake 222 in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system 300 also includes a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear 100. The backup hydraulic pressure source 216 is arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.

Abstract: An aircraft control system (100) including an aircraft control module (110), a trained classifier module (120), and an aircraft control processing engine (13). The aircraft control module (110) generates first control outputs (104a to 104c) based on received aircraft operating inputs (102a to 102d). The trained classifier module receives the aircraft operating inputs (102a to 102d) and generates second control outputs (104d to 104f). The aircraft control processing engine (130) receives the first control outputs (104a to 104c) and the second control outputs (104d to 104f) and generates operating control outputs (106a to 106c), based on the received first control outputs and second control outputs. The aircraft control processing engine (130) then controls the aircraft using the operating control outputs (106a to 106c).

Abstract: A method of controlling the motion of a turning aircraft during taxiing on the ground, the aircraft having a steerable landing gear, for example a nose landing gear, operating in a free-to-caster mode, includes (a) ascertaining the rotational position (?) of the steerable landing gear relative to the longitudinal axis (L) of the aircraft (b) receiving a control instruction that would, if effected, continue turning of the aircraft in the same direction away from the longitudinal axis, and (c) modifying the control instruction so that the angle between the rotational position of the steerable landing gear and the longitudinal axis will be lower than the angle that would otherwise be observed had the control instruction been effected and not so modified. The risk of damage to the steerable landing gear through over-steering may thus be reduced.

Abstract: A method of determining the integrity of an electric or hydraulic braking control system. A reduction rate of a voltage or hydraulic pressure in the braking control system is determined, and the integrity of the braking control system is determined by comparing the reduction rate with a threshold. The braking control system may be an aircraft braking control system, and the method may be performed during flight of the aircraft—typically during cruise.

Abstract: A method of braking left and right landing gear wheels on respective left and right sides of an aircraft. A desired left braking parameter (L) is received for the left wheel and a desired right braking parameter (R) is received for the right wheel. The left wheel is braked with a reduced left braking parameter (L?) which is less than the desired left braking parameter (L), and the right wheel is braked with a reduced right braking parameter (R?) which is less than the desired right braking parameter (R). A difference between the braking parameters is maintained so that L??R?=L?R.

Abstract: A method of determining the integrity of an electric or hydraulic energy source of a braking control system. The energy source is charged or discharged, and two or more measurements of voltage or hydraulic pressure are taken from the braking control system. A difference between at least two of the measurements is determined in order to determine a change or rate of change in voltage or hydraulic pressure caused by the charging or discharging of the energy source. The integrity of the energy source is determined by checking whether the change or rate of change in voltage or hydraulic pressure meets predetermined criteria. The check may comprise comparing the change or rate of change of the voltage or hydraulic pressure to a threshold—for instance checking whether the change exceeds a threshold, or falls between an upper threshold and a lower threshold.

Abstract: A multi-layered blister package includes a first panel having at least one blister pocket receiving aperture defined therein, wherein a blister pocket protrudes through the at least one blister pocket receiving aperture and retains an article therein. A second panel has at least one exit aperture defined therein, wherein the at least one exit aperture aligns with the at least one blister pocket receiving aperture when the first panel is disposed over the second panel. A third panel having at least one intermediate aperture defined therein, wherein the at least one intermediate aperture aligns with and is between the at least one exit aperture and the at least one blister pocket receiving aperture when the third panel is pivoted to a first position.

Abstract: A server creates a plurality of projects pertaining to providing manufacturing service results. Each of the plurality of projects specifies operations to be performed relating to providing the manufacturing service results and at least one of the plurality of projects generates a requested manufacturing service result. The server initiates the at least one project that generates the requested manufacturing service result, wherein the at least one project is associated with an execution engine. The initiation of the at least one project may include sending input data to the execution engine based on configuration data that is associated with the execution engine, and obtaining the requested manufacturing service result from the execution engine. The server provides the requested manufacturing server result to at least one recipient.

Abstract: A lockable package includes an outer sleeve defined by connected first and second panels, the sleeve having at least one open end. An inner container is slidable within the sleeve, and having a first portion joined to a second portion, wherein at least one of a height and a width of the first portion is less than a corresponding height and width of the second portion. A difference between one of the height and the width of the first portion and the corresponding height and width of the second portion defines a ridge. A locking assembly is provided at the at least one open end of the sleeve and is configured to releasably engage the ridge, wherein the inner container is removable through the open end of the sleeve by disengaging the locking assembly from the ridge.

Abstract: A multi-layered blister package includes a first panel having at least one blister pocket receiving aperture defined therein, wherein a blister pocket protrudes through the at least one blister pocket receiving aperture and retains an article therein. A second panel has at least one exit aperture defined therein, wherein the at least one exit aperture aligns with the at least one blister pocket receiving aperture when the first panel is disposed over the second panel. A third panel having at least one intermediate aperture defined therein, wherein the at least one intermediate aperture aligns with and is between the at least one exit aperture and the at least one blister pocket receiving aperture when the third panel is pivoted to a first position.

Abstract: A server creates a plurality of projects pertaining to providing manufacturing service results. Each of the plurality of projects specifies operations to be performed relating to providing the manufacturing service results and at least one of the plurality of projects generates a requested manufacturing service result. The server initiates the at least one project that generates the requested manufacturing service result, wherein the at least one project is associated with an execution engine. The initiation of the at least one project may include sending input data to the execution engine based on configuration data that is associated with the execution engine, and obtaining the requested manufacturing service result from the execution engine. The server provides the requested manufacturing server result to at least one recipient.

Abstract: A multi-layered blister package includes a first panel having at least one first aperture defined therein, wherein a blister pocket is visible through the at least one first aperture and retains an article therein. A second panel has at least one exit aperture defined therein by a first non-continuous cut line, wherein the at least one exit aperture aligns with the at least one first aperture when the first panel is disposed over the second panel. A first fold line separates the first and second panels. A biasing force transmitting member is provided with the first panel, such that a biasing force is applied to the blister pocket via the biasing force transmitting member. The biasing force transmitting member includes at least one of a plurality of spring legs encompassing the at least one first aperture and a shield member disposed between the first panel and the blister pocket.