A tool for fabricating a control surface is disclosed. In various embodiments, the tool includes a first block defining a longitudinal direction running between a leading edge end and a trailing edge end; a first sidewall spaced a first lateral distance from the first block to form a first closeout channel running in the longitudinal direction between the first block and the first sidewall; and a second sidewall configured to form a second closeout channel running in the longitudinal direction, the second closeout channel disposed laterally opposite the tool from the first closeout channel.

Wings do not produce lift. It is the thrust provided by an engine (or engines) that enable an aircraft to rise off the ground.

Aerial vehicles may include one or more directional sensors embedded into wings, rudders, ailerons, flaps or other control surfaces. When the aerial vehicles are operating in modes that do not require the use of such surfaces, a surface having a directional sensor embedded therein may be repositioned or reoriented to align the directional sensor toward an area or axis of interest, and information may be gathered from the area or axis of interest using the directional sensor. One or more safety lights, running lights or other illuminators may cast light of a desired color, frequency or wavelength toward the area or axis of interest. The directional sensors may include cameras, radar or laser sensors, or any other reorientable sensors.

A system and method for detecting yoke interference for an aircraft having an auto pitch trim function is provided. The system includes a source of elevator load data, a source of aircraft speed data, and a processing system. The processing system is coupled to receive the elevator load data, the aircraft speed data, and initial condition center-of-gravity (CG) data that is representative of at least an estimated initial position of the CG of the aircraft. The processing system is configured to process at least the speed data and the initial condition CG data to: (i) determine an expected elevator load on the elevator flight control surface, (ii) determine if the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, and (iii) when the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, generate a disconnect signal that will disable the auto pitch trim function.

A system and method for detecting yoke interference for an aircraft having an auto pitch trim function is provided. The system includes a source of elevator load data, a source of aircraft speed data, and a processing system. The processing system is coupled to receive the elevator load data, the aircraft speed data, and initial condition center-of-gravity (CG) data that is representative of at least an estimated initial position of the CG of the aircraft. The processing system is configured to process at least the speed data and the initial condition CG data to: (i) determine an expected elevator load on the elevator flight control surface, (ii) determine if the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, and (iii) when the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, generate a disconnect signal that will disable the auto pitch trim function.

Systems and methods for optically measuring a position of a measurement surface relative to a reference position. The system is a wireless network comprising a centrally located data acquisition computer and a multiplicity of remotely located sensor modules mounted at different locations within wireless communication range of a central receiver. Each sensor module is mounted to a clamp that is made specific to a control surface location and embedded with an RFID tag to denote clamp location. The optical components of the sensor modules are selected to enable indication of the linear position of a measurement surface relative to a reference position and then broadcast the measurement results. The broadcast results are received by the central receiver and processed by the data acquisition computer, which hosts human interface software that displays measurement data.

An actuating mechanism is disclosed for a body in an air and/or space vehicle. having at least one control surface on the body for moving relative to the body and thereby enabling control of the air flow and enabling the air vehicle to maneuver. The actuating mechanism has at least two actuators produced from an electro-active polymer material between the body and the control surface for changing its form depending on electrical energy and thereby triggering the control surfaced.

The present disclosure relates to a structural component of an aircraft wing body and an aircraft including the structural component. According to an aspect of the present disclosure, a structural component of an aircraft wing body is provided. The structural component includes a body part and a profile. The body part includes an edge portion formed by end portions of a first skin and a second skin of the body part superposed together. The profile is attached to the edge portion. The profile has an outer profile conforming to an outer profile of the body part such that the structural component, as a whole, exhibits an aerodynamic outer profile after the profile is attached to the edge portion. The profile is attached to the edge portion via a plurality of separate intermediate members or by contacting the edge portion.

The present disclosure relates to a structural component of an aircraft wing body and an aircraft including the structural component. According to an aspect of the present disclosure, a structural component of an aircraft wing body is provided. The structural component includes a body part and a profile. The body part includes an edge portion formed by end portions of a first skin and a second skin of the body part superposed together. The profile is attached to the edge portion. The profile has an outer profile conforming to an outer profile of the body part such that the structural component, as a whole, exhibits an aerodynamic outer profile after the profile is attached to the edge portion. The profile is attached to the edge portion via a plurality of separate intermediate members or by contacting the edge portion.

A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.