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Many textbooks utilized in universities implement the DATCOM method of stability and control. Shortly before compilation of the DATCOM was completed, a computerized version called Digital DATCOM was created. The USAF S&C Digital DATCOM implements the DATCOM methods in an easy to use manner.
Stability derivatives, and also control derivatives, are measures of how particular forces and moments on an aircraft change as other parameters related to stability change (parameters such as airspeed, altitude, angle of attack, etc.). For a defined "trim" flight condition, changes and oscillations occur in these parameters.
In February 1976, work commenced to automate the methods contained in the USAF Stability and Control DATCOM, specifically those contained in sections 4, 5, 6 and 7.The work was performed by the McDonnell Douglas Corporation under contract with the United States Air Force in conjunction with engineers at the Air Force Flight Dynamics Laboratory in Wright-Patterson Air Force Base.
Aircraft are designed to avoid the following aeroelastic problems: divergence where the aerodynamic forces increase the twist of a wing which further increases forces; control reversal where control activation produces an opposite aerodynamic moment that reduces, or in extreme cases reverses, the control effectiveness; and
Most aircraft trimmed for straight-and-level flight, if flown stick-fixed, will eventually develop a tightening spiral-dive. [2] If a spiral dive is entered unintentionally, the result can be fatal. A spiral dive is not a spin; it starts, not with a stall or from torque, but with a random perturbation, increasing roll and airspeed.
An aircraft stabilizer is an aerodynamic surface, typically including one or more movable control surfaces, [1] [2] that provides longitudinal (pitch) and/or directional (yaw) stability and control. A stabilizer can feature a fixed or adjustable structure on which any movable control surfaces are hinged, or it can itself be a fully movable ...
The longitudinal stability of an aircraft, also called pitch stability, [2] refers to the aircraft's stability in its plane of symmetry [2] about the lateral axis (the axis along the wingspan). [1] It is an important aspect of the handling qualities of the aircraft, and one of the main factors determining the ease with which the pilot is able ...
The key feature of the gyroscopic stabilizer apparatus was that it incorporated a gyroscope to regulate the control surfaces of the aircraft. [1] Lawrence Sperry managed to design a smaller and lighter version of a gyroscope, [1] and the device was integrated into an aircraft's hydraulic control system. Using a negative feedback loop, the ...