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Redundancy sensor inertial measurement device

An inertial measurement device and sensor technology, applied in the direction of measuring devices, navigation through speed/acceleration measurement, instruments, etc., can solve the problems of carrier size, weight, power consumption, and increase in development costs, so as to achieve maximum application value and reduce The effect of measuring error influence and reducing influence

Inactive Publication Date: 2012-05-02
FLIGHT AUTOMATIC CONTROL RES INST
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Problems solved by technology

[0003] The use of multiple sets of inertial navigation systems will undoubtedly increase the size, weight, power consumption and development cost of the carrier, which limits the application of this method on some carriers, such as aircraft, spacecraft, satellites (limited in shape and weight) and Automobile (cost constrained), etc.

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  • Redundancy sensor inertial measurement device
  • Redundancy sensor inertial measurement device
  • Redundancy sensor inertial measurement device

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Embodiment Construction

[0019] The present invention will be described in further detail below by means of specific embodiments:

[0020] Please also see Figure 1-Figure 5 , the structure of the inertial measurement device for the redundancy sensor of the present invention is given. The inertial measurement device of the redundancy sensor of the present invention comprises a mounting base 1 , a gyroscope 2 , an accelerometer 3 , a shock absorber 4 and a screw 5 . Wherein, the installation base is an 18-hedron, in which there are 6 planes perpendicular to the corresponding X, Y, Z coordinate axes, which are respectively XX plane 6, YY plane 7, ZZ plane 8 and the planes opposite to them— —X'X' plane, Y'Y' plane, Z'Z' plane.

[0021] In addition, a pair of slopes are symmetrically arranged on adjacent sides of the above-mentioned six planes perpendicular to the coordinate axes. Among them, the two sides of the ZZ plane 8 are the AA plane 9 and the BB plane 10, and the normal lines A, B and the Z axis...

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Abstract

The invention relates to a high-reliability inertial measurement device which can be used to reduce inertial measurement device measuring random errors. The redundancy sensor inertial measurement device contains an installation pedestal, gyroscopes, accelerometers, vibration dampers and screws. The installation pedestal has 18 hedral surfaces, wherein six planes are perpendicular to a motion reference axis and a normal line of any one of the other twelve planes has an included angle of 31 Deg 43 Min 2.9 Sec to one reference axis. The gyroscopes and the accelerometers are assembled on the pedestal. Two parallel planes are respectively provided with a gyroscope and an accelerometer. On the pedestal, the vibration dampers are assembled on two parallel planes which are perpendicular to a samereference axis. According to the invention, it is ensured that parallel translation or rotation in the direction of any one reference axis can be simultaneously measured by five inertial elements. The redundancy sensor inertial measurement device has advantages of good vibration damping performance, strong environmental adaptation and high reliability, can be used to effectively raise navigation precision with the cooperation of value processing, and simultaneously is convenient to process, requires low cost, and has large practical application values.

Description

technical field [0001] The invention relates to an inertial measurement device which has high reliability and can reduce the influence of random error in inertial device measurement. Background technique [0002] The inertial navigation system (hereinafter referred to as the inertial navigation system) provides navigation and attitude control information for carriers such as aircraft, spacecraft, ships, and ground mobile equipment. If only one set is configured, once a failure occurs, it will bring serious or catastrophic impact. Therefore, in the application process of the inertial navigation system, multiple sets of inertial navigation system fault-tolerant configuration or sensor redundancy configuration are usually used to detect, isolate and reconfigure the equipment in the system, so as to improve the reliability of the inertial navigation system , to ensure the safety of the carrier operation and the positioning accuracy during the navigation process. [0003] The u...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/16G01C25/00
Inventor 王京献张明辉
Owner FLIGHT AUTOMATIC CONTROL RES INST
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