A system for managing the deceleration of an aircraft enabling the control in real time of the position of the aircraft on a braking axis, includes a braking system; a calculator configured to: calculate, from aircraft data and from external data, a sequence of use of the braking system intended to brake the aircraft over a predetermined braking distance which associates a predetermined position on the braking axis with each braking instant; update in real time the sequence of use as a function of the difference between the position of the aircraft and the predetermined position; and a controller configured to control the braking system as a function of the sequence of use.

A flight path generation apparatus (300) is configured to generate a flight path for an aircraft (100) capable of autonomously flying, and includes: an airframe information acquisition unit (301) configured to acquire airframe information including airframe IDs and take-off places of a plurality of aircraft (100); a movement information acquisition unit (302) configured to acquire movement information related to scheduled take-off times and destinations of the plurality of aircraft; a generation unit (303) configured to generate flight paths from the take-off places to landing places corresponding to the destinations based on the airframe information and the movement information; and a communication unit (304) configured to transmit the flight paths to the aircraft.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, an apparatus for close formation flight, comprises a plurality of sensors for collecting measurements characterizing airflow near an aircraft. The plurality of sensors are attachable to at least one of a wing, fuselage, or tail of the aircraft, and the measurements provide information about airflow velocity in a direction transverse to a direction of the aircraft flight.

A method is provided for improving aircraft engine operating efficiency during flight in aircraft driven on the ground by electric taxi systems that extends engine warm up and cool down time during ground operations without increasing the time an aircraft spends on the ground. Aircraft are driven by electric taxi systems between landing and take off with the main engines simultaneously maintained at throttle setting for time periods that ensure even and symmetrical heating or cooling for all engine components. When the aircraft reaches a location where idle or take off thrust is required before take off, engine thrust may be increased without the adverse effects of differential thermal expansion of engine components during flight. Aircraft engines may be designed to rely on electric taxi operation and extended warm up and cool down times without delaying push back or taxi-in or otherwise negatively impacting airport operations.

A gravity simulation system, including a computing system running a program thereon to receive input for a gravity environment and calculate the gravity environment based on a predetermined gravity algorithm, and a gravity simulation aircraft connected to the computing system to simulate the gravity environment received from the computing system based on at least one of a flight setting and a gravity setting.

A gravity simulation system, including a computing system running a program thereon to receive input for a gravity environment and calculate the gravity environment based on a predetermined gravity algorithm, and a gravity simulation aircraft connected to the computing system to simulate the gravity environment received from the computing system based on at least one of a flight setting and a gravity setting.

A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.

A maneuvering support apparatus 10 comprises a flight control unit 11 that causes a second unmanned aerial vehicle having an imaging device to fly so as to follow a first unmanned aerial vehicle maneuvered by a pilot, and further, and controls the second unmanned aerial vehicle so that the first unmanned aerial vehicle is captured by the imaging device, an image display unit 12 that acquires an image data of an image captured by the imaging device, and displays the image based on the acquired image data on a screen of a display device.

A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.