Electra Aero, Inc.

Massachusetts Institute of Technology

Robert John Hansman

Christopher B Courtin

Oliver Masefield

Mark Drela

John S Langford, Iii

Luke Loftis Jensen

Clement Li

In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.

System and method for controlling flight path of a blown lift aircraft

In some embodiments, a pilot guidance display system may include a display operatively coupled to an aircraft and configured to provide a plurality of indications and a plurality of limits to a pilot. The pilot guidance display may also include a computing device operatively coupled to the aircraft and communicatively coupled to the display. The computing device may have at least one processor configured to update the plurality of indications and the plurality of limits on the display in real-time based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft. The plurality of limits may include a first maximum angle of attack indicator. Methods and computer implemented operations are also disclosed.

System and method for a pilot guidance display of an aircraft

An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.

System and method for controlling differential thrust of a blown lift aircraft

A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

System and method for lift augmentation of aircraft wings

An embodiment includes an apparatus that supports a user to make planning decisions of fuel efficiency of an aircraft versus time of arrival of the aircraft along a flight path. An embodiment of the apparatus accepts input data related to the aircraft. The input data may include (i) flight plan data that includes a flight path of the aircraft, (ii) state of the aircraft along the flight path, (iii) environmental data, and (iv) an aircraft performance model of the aircraft. The apparatus calculates aircraft performance and an objective function for a range of altitudes and speeds as a function of the input data. The apparatus causes a user interface to display aircraft performance contour boundaries and a vertical routing path that meets the objective function to provide graphical representations to support a user's planning decisions.

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Cambridge, MA, United States of America

Robert John Hansman