Method for determining airplane body bottom suction during airplane water forced landing
A technology for determining the bottom of the fuselage, which is applied to aircraft parts, ground devices, transportation and packaging, etc., can solve the problems of not being able to simulate the suction effect of the bottom of the fuselage, and achieve improved analysis accuracy, strong operability, and clear thinking Effect
Active Publication Date: 2021-04-06
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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[0004] The purpose of the present invention is: the embodiment of the present invention provides a kind of method for determining the suction force at the bottom of the fuselage of an aircraft ditching, by establishing an engineering model of the suction correction engineering model at the bottom of the fuselage when the aircraft ditching, to solve the inability of the current SPH method to analyze the ditching of the aircraft Technical Problems in Simulating the Suction Effect of Fuselage Bottom
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[0039] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.
[0040] The following specific embodiments provided by the present invention can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments. The present invention will be further described in detail below in conjunction with the description and the accompanying drawings.
[0041] The embodiment of the present invention provides a method for determining the suction force at the bottom of the fuselage of an aircraft ditching. The method is based on Bernoulli's principle, by analyzing the air suction at the bottom of the fus...
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The invention discloses a method for determining an airplane body bottom suction during airplane water forced landing. The method comprises the following steps: 1, acquiring a geometrical characteristic angle of a fuselage bottom structure of the aircraft; 2, according to the geometrical characteristic angle alpha of the aircraft, calculating a vertical water entry pressure peak value of the aircraft configuration corresponding to the geometrical characteristic angle alpha; and 3, according to the vertical water entry pressure peak value calculated in the step 2, the geometrical characteristic angle alpha obtained in the step 1 and a pre-constructed suction model, obtaining the suction of the bottom of the fuselage during water forced landing of the aircraft; wherein a peak attenuation coefficient based on aircraft configuration is introduced into the suction model, and the aircraft configuration corresponding to different geometrical characteristic angles alpha has the corresponding peak attenuation coefficient. By establishing the fuselage bottom suction correction engineering model during aircraft water forced landing, the technical problem that the fuselage bottom suction effect cannot be simulated when an existing SPH method is used for aircraft water forced landing analysis is solved.
Description
technical field [0001] The invention relates to but is not limited to the technical fields of aircraft structural dynamics and hydrodynamics, and in particular relates to a method for determining suction at the bottom of an aircraft ditching fuselage. Background technique [0002] During the dynamic analysis of aircraft ditching, when the fuselage collides with the water surface, the water pressure will decrease as the flow velocity increases. When the water pressure decreases below the static pressure, cavitation will occur, resulting in Suction for the rear fuselage. If the influence of suction at the bottom of the fuselage is not considered in the analysis of ditching, the error of the dynamic response of the aircraft will be relatively large. figure 1 Shown is the effect of suction on the aircraft attitude angle during ditching. After considering the suction effect at the bottom of the fuselage, the change of the attitude angle of the aircraft is consistent with the tr...
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Login to View More IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 吕锦锋梁元党晓艳
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA