Method for measuring installation errors of star sensor and strapdown inertial measurement unit of aircraft
A technology of star sensor and strapdown inertial group, which can be used in measurement devices, instruments, etc., and can solve the problems of increasing the complexity and accuracy of the test process.
Active Publication Date: 2016-03-23
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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However, the establishment of the geographic coordinate system and the celestial coordinate system must be based on the north reference established in advance or the north reference established by high-precision inertial units. At the same time, the conversion between the equatorial coordinate system and the geographic coordinate system must introduce the hour angle information based on the vernal equinox (UT1 ), the introduction of these information increases the complexity and precision of the testing process
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[0020] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.
[0021] Such as figure 1 As shown, the present invention provides a method for measuring the installation error of an aircraft star sensor and a strapdown inertial set, the method includes the following steps:
[0022] S1. Establish an intermediate conversion coordinate system O m x m Y m Z m , the origin O of the intermediate transformation coordinate system m and inertial group coordinate...
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The invention discloses a method for measuring the installation errors of a star sensor and a strapdown inertial measurement unit of an aircraft. The method comprises the following steps that S1, an intermediate conversion coordinate system OmXmYmZm is set up, an original point of the coordinate system coincides with an original point of an internal measurement unit coordinate system, an OmXmYmZm plane is located in the local horizontal plane, the direction of an OmXm axis is the longitudinal direction of the aircraft, and the direction of an OmYm axis is aligned to a strapdown inertial measurement unit prism; S2, a posture matrix C<t> of the strapdown inertial measurement unit under the intermediate conversion coordinate system is calculated; S3, a posture matrix C<s><t> of a measurement coordinate system of the star sensor in the intermediate conversion coordinate system is calculated; S4, a conversion matrix (please see the formula in the specification) of the measurement coordinate system of the star sensor under the internal measurement unit coordinate system is calculated, the projection relation between all axes on the measurement coordinate system of the star sensor and all axes of the internal measurement unit coordinate system is determined, and the installation errors of the star sensor and the strapdown inertial measurement unit are obtained. The method is convenient and fast to use and high in accuracy, and the installation errors of the star sensor and the strapdown inertial measurement unit can be fast measured indoors.
Description
technical field [0001] The invention belongs to the technical field of aircraft inertial / astronomical integrated navigation, and more particularly relates to a method for measuring the installation error of an aircraft star sensor and a strapdown inertial set. Background technique [0002] Celestial navigation is a high-precision navigation technology that uses the position of stars as a reference object. It often forms a high-precision autonomous integrated navigation system with the strapdown inertial navigation system on the aircraft. Since the SIM and the star sensor on the aircraft are often installed in different positions of the aircraft carrier, there is a fixed installation error between the two, especially the difference between the measurement coordinate system of the star sensor and the SIM coordinate system. The installation error directly affects the transfer accuracy between celestial navigation and inertial navigation. Therefore, in order to ensure the accur...
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Login to View More IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 王亚军周海李春权王勇陆壮志
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD