Determination method for horizontal tail installation angle of horizontal tail fixed airplane
A technology for determining the installation angle and method, which is applied to aircraft stability, aircraft parts, aircraft control, etc., and can solve problems such as the lack of a fast method for determining the installation angle
Active Publication Date: 2016-08-03
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0003] There is no method for quickly determining the installation angle in the prior art
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[0038] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention discloses a determination method for a horizontal tail installation angle of a horizontal tail fixed airplane. The method comprises the following steps: step 1: determining a first design optimization point; step 2: obtaining airplane parameters under the first design optimization point, and calculating a first horizontal tail installation angle of the first design optimization point through a formula; step 3: substituting the first horizontal tail installation angle into a flight process of the whole horizontal tail fixed airplane, and verifying whether an elevating rudder can guarantee normal flight of the horizontal tail fixed airplane in a self deflection angle range under the first horizontal tail installation angle or not; step 4: calculating a second horizontal tail installation angle according to a longitudinal maneuvering capability of the horizontal tail fixed airplane; and step 5: selecting one of the first horizontal tail installation angle and the second horizontal tail installation angle as an actual horizontal tail installation angle of the horizontal tail fixed airplane. The determination method for the horizontal tail installation angle of the horizontal tail fixed airplane, disclosed by the invention, can be used for determining a suitable horizontal tail installation angle.
Description
technical field [0001] The invention relates to the technical field of aircraft maneuverability and stability design, in particular to a method for determining the installation angle of a horizontal tail of an aircraft with a fixed horizontal tail. Background technique [0002] The horizontal tail and the rudder elevator located on the trailing edge of the horizontal tail play an important role in the longitudinal handling quality of the aircraft. For the non-movable horizontal tail aircraft, the horizontal tail is fixed at an installation angle, and the longitudinal trim and overload maneuver are completed by the elevator. At this time, it is extremely important to determine the installation angle of the fixed horizontal tail, which involves the rudder range of the elevator and the driver's control experience. [0003] There is no method for quickly determining the installation angle in the prior art. [0004] Therefore, it is desirable to have a technical solution to ove...
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Login to View More IPC IPC(8): B64F5/00B64C5/02
CPCB64C5/02
Inventor 窦炳耀吕新波齐万涛
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA