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- W2079277227 abstract "HE cases of damage caused by nose-first landings that have recently been reported in Ref. 1 are a clear indication that this subject deserves serious attention and that it is not merely a theoretical exercise. However, while being of interest to the landing-gear designer, the Engineering Note lacks an explanation of why the value of /* should be taken as equal to 0.8/2 or less (and as a consequence, why the vertical energy ratio of 1.25 or more is to be used at the nose gear). The reason may be found in Ref. 2. In the example for nose-gear landing-impact given there, the polar moment of inertia in pitch about the e.g. used a radius of gyration kcg of 44.7% of the spacing between the gears /, compared to the value of A: cg of 28.7% that is actually used in the Engineering Note. Reference 2 also showed that the equivalent at the nose gear was 2.20 times the mass there, and that this ratio is roughly proportional to the relative size of the moment of inertia in pitch. Then, by taking proportions for the example in the Engineering Note. Equivalent - 2.20 x (0.287/0.447) - 1.40 of the static mass. With the design sinking speed ]/sink this will directly affect the vertical energy that is absorbed by the nose gear. It is close to the value of 1.50 times the normal sinking energy that is suggested in the Engineering Note. In general, these values for equivalent at the nose gear exceed the ones that are specified in FAR 25.725 Airworthiness Regulations. A more exact method of analysis is provided in Ref. 2, however, it should be further noted that the effect of fuselage flexibility will reduce this ratio, particularly on the larger sizes of aircraft." @default.
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- W2079277227 date "1995-07-01" @default.
- W2079277227 modified "2023-09-27" @default.
- W2079277227 title "Comment on 'Aircraft landing gear positioning concerning abnormal landing cases'" @default.
- W2079277227 doi "https://doi.org/10.2514/3.46816" @default.
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