Aircraft rotational inertia measuring platform and identification method

A technology of moment of inertia and measurement platform, which is applied to measurement devices, machine/structural component testing, static/dynamic balance testing, etc., and can solve the problems of insignificant test results, difficult direct identification, and poor operability, etc. Achieve the effect of outstanding universal applicability, reliable identification method, and easy installation and testing

Pending Publication Date: 2021-10-01
JIANGSU UNIV
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  • Abstract
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  • Application Information

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Problems solved by technology

Traditional moment of inertia measurement methods mainly include three-line pendulum method, torsion pendulum method and compound pendulum method, etc., and the test effect for aircraft moment of inertia is not obvious. The error is large and it is not easy to directly identify and apply to the flight control microcontroller

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  • Aircraft rotational inertia measuring platform and identification method
  • Aircraft rotational inertia measuring platform and identification method
  • Aircraft rotational inertia measuring platform and identification method

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Embodiment Construction

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention.

[0027] Such as figure 1 The overall structure diagram of the aircraft moment of inertia measurement platform shown is mainly composed of the following parts: 1-aircraft mounting plate; 2-connecting flange; 3-first support plate; 4-first transmission optical axis; 5- The first plum blossom coupling; 6-dynamic torque sensor; 7-the second support plate; 8-support frame; 9-the second plum blossom coupling; 10-the third support plate; 11-the second transmission optical axis; 12 - the third plum blossom coupling; 13 - the fourth support plate; 14 - Omron encoder; 15 - fixed frame. In the whole structure, there are multiple mounting holes on the aircraft mounting plate 1, except for the fixing holes of the multi-axis test of the aircraft, other fixing holes for the measured objects ...

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Abstract

The invention discloses an aircraft rotational inertia measuring platform and a measurement data identification method. The aircraft rotational inertia measuring platform comprises an aircraft mounting disc 1, a connecting flange 2, a first supporting plate 3, a first transmission optical shaft 4, a first plum coupling 5, a dynamic torque sensor 6, a second supporting plate 7, a supporting frame 8, a second plum coupling 9, a third supporting plate 10, a second transmission optical shaft 11, a first plum coupling 12, a fourth supporting plate 13, an Omron encoder 14 and a fixing frame 15. The whole structure of the aircraft rotational inertia measuring platform is made of aluminum profiles and is stable and reliable; and the mounting disc is a carbon fiber plate, is light in weight, can bear large pressure, is not liable to deform, and facilitates the installation and testing of the aircraft.

Description

technical field [0001] The invention belongs to the technical field of moment of inertia measurement, and in particular relates to an aircraft moment of inertia measurement platform and an identification method. Background technique [0002] Moment of inertia is a measure of inertia when a rigid body rotates around an axis. It can be used to establish the relationship between angular momentum, angular velocity, torque, and angular acceleration. Its value depends on the shape, mass distribution, and position of the rotational axis of the object. For a uniform rigid body with regular shape, its moment of inertia can be directly calculated by formula, but for the moment of inertia of irregular rigid body or non-uniform rigid body, it is difficult to calculate accurate results by theoretical formula, and it is generally measured by experimental method. [0003] In the aircraft system, the moment of inertia can directly reflect the current heading information of the aircraft, and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M1/10
CPCG01M1/10
Inventor 刘慧沈亚运沈跃孙志伟王辉
Owner JIANGSU UNIV
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