The invention relates to an aircraft spin recovery improving device, belongs to the aircraft industry which comprises the aircraft controllability and the stability field, and aims at improving the use safety and reaching the necessary quality of the training aircraft. The plan of the device shows that the device comprises two horizontal tail strakes in lifting surface forms. The two lifting surfaces are symmetrically arranged on the tail part of the aircraft relative to the longitudinal symmetrical surface of the aircraft and are connected with a horizontal tail near the wing root chord of the horizontal tail. In a range of 1.1-1.5b of each lifting surface along the aircraft body length, the maximum width can be reached between each lifting surface and the connection part, and the maximum width is in the range of 0.1-0.15b, wherein b is the wing root chord of the horizontal tail. The swept-back angle from the middle of each lifting surface to the horizontal tail is 90 degrees to 115 degrees. When any of the present recovery method is operated, the device provided by the invention enables the aircraft to recover the spin even when all of the control mechanism is deflected to the middle position, so as to improve the aircraft operational safety substantially.
Aircraft recovery spin improving device
2015-12-02
Patent
Elektronische Ressource
Englisch
Prediction of aircraft spin recovery
AIAA | 1989
|Bridle Attachment for Aircraft Spin-Recovery Parachute
NTRS | 1985
|Aircraft Spin Recovery Using a Sliding-Mode Controller
Online Contents | 2010
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