Limit gravity center loading method of helicopter

A helicopter and center of gravity technology, which is applied to aircraft parts, ground equipment, transportation and packaging, etc., can solve the problems of inconvenient calculation and inability to realize stowage, and achieve the effect of simple stowage method

Active Publication Date: 2014-12-24
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

The calculation result of this method is accurate, but the stowage cannot be realized w

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  • Limit gravity center loading method of helicopter
  • Limit gravity center loading method of helicopter
  • Limit gravity center loading method of helicopter

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Embodiment Construction

[0018] The helicopter limit center of gravity stowage method involved in the present invention is carried out below in conjunction with accompanying drawing

[0019] Detailed step by step.

[0020] first step:

[0021] Determine the known parameters: the empty weight of a helicopter is 1360kg, the empty center of gravity is (3.507, 0.024, -1.689), and the empty moment of inertia is (1031.88, 4861.66, 4012.66, 47.38, -9.93, 323.76). See Table 1 for the stowage weight limit conditions of the stowage points. Stowage is required to satisfy the limit center of gravity X=3.170 in the longitudinal direction, and the take-off weight is 2000kg.

[0022] Table 1 Weight limit conditions for loading points

[0023]

[0024] Step two:

[0025] Determine the stowage priority order according to the factors affecting the maximum moment of inertia:

[0026] Ask to get the longitudinal limit X m = 3.170m when the ultimate loading scheme, it is necessary to obtain the maximum moment of ...

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Abstract

The invention provides a limit gravity center loading method of a helicopter, belongs to a helicopter weight design technology and relates to a design method of achieving maximal rotational inertia value by virtue of rapid loading based on priority sequence. The method is characterized in that the limit gravity center of the helicopter means that the helicopter is in a limit take-off weight and limit gravity center state and simultaneously achieves the maximal rotational inertia value; the rotational inertia value is determined by the weight of each loading point and the distances between the coordinates of each loading point and limit coordinates; priority sequencing is performed on the loading points by virtue of the distances of the loading points and weight loading is rapidly performed on the loading points by use of the priority sequence. By utilizing a priority sequence method, not only can the rotational inertia calculated value of the loading scheme in a loading direction be maximal, but also the advantages of rapidness and convenience are achieved, the diversity of loading schemes is avoided, and an optimal technical scheme can be provided for helicopter pneumatic calculation, structure and landing chassis strength design and flight verification processes.

Description

technical field [0001] The invention belongs to the helicopter weight design technology, and designs a design method for obtaining the maximum moment of inertia value through fast loading based on priority order. Background technique [0002] The limit center of gravity refers to the point corresponding to each limit state of the envelope of the center of gravity of the helicopter, and is usually defined by the combination of the center of gravity and weight as the abscissa and ordinate. In the process of helicopter aerodynamic calculation, structure and landing gear strength design, and flight verification, in order to calculate, evaluate and verify the scheme or performance under the limit center of gravity, it is necessary to provide the limit center of gravity loading scheme and the corresponding whole machine moment of inertia. The loading scheme at the limit center of gravity point refers to the weight and center of gravity distribution that can make the helicopter at ...

Claims

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Application Information

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IPC IPC(8): B64F5/00
Inventor 吕春雷黄利叶昌敬罗丫李亚楠李云鹏
Owner CHINA HELICOPTER RES & DEV INST
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