GPS and navigation GPS)، GLONASS، GALILEO
Mohammad Hosein Shafiei; meisam jowkar; Behrooz Safarinejad
Volume 13, Issue 3 , September 2020, , Pages 69-77
Abstract
In this paper a new structure for the inertia measurement unit is presented; the proposed structure consists of three rotary discs around the three main axes in the body, and an accelerometer is mounted on each disc. It is shown in this paper that the proposed structure reduces the effect of disturbing ...
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In this paper a new structure for the inertia measurement unit is presented; the proposed structure consists of three rotary discs around the three main axes in the body, and an accelerometer is mounted on each disc. It is shown in this paper that the proposed structure reduces the effect of disturbing accelerometer parameters, such as constant and variable bias, as well as noise depletion. Due to the proposed rotational structure, it is necessary to continuously sample the accelerometers. In order to use the sampled data, calculations should be performed in discrete mode. In this paper, a method for combining this information is presented. By examining the proposed equations, the successful performance of this method is shown in the reduction of the effect of three constant bias parameters and the bias of the accelerometer and the measured noise. As well as the efficiency of the proposed method for measuring the acceleration of the device using Numerical representation is shown.
Morteza Tayefi; Ghasem Kahe; Mijtaba Mehrafrooz
Volume 12, Issue 4 , December 2019, , Pages 69-77
Abstract
Sounding rockets provide a useful platform for the aerospace research activities in which carry out a research payload to the space and recover it in the ground. In the flight path, it does scientific experiments and acquire the result for more analysis in the ground. All of the well-known aerospace ...
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Sounding rockets provide a useful platform for the aerospace research activities in which carry out a research payload to the space and recover it in the ground. In the flight path, it does scientific experiments and acquire the result for more analysis in the ground. All of the well-known aerospace centers around the world use frequently the various forms of sounding rocket to test and evaluate their sensitive space components. Actually, space qualification process of a space module is completed sometimes through a real space flight using the sounding rocket. In this paper the performance of a MEMS based inertial measurement unit (IMU) is investigated. The investigation result shows that using appropriate filtering, MEMS based IMU can measure appropriately the dynamic behavior of the sounding rocket. These data may be used for further identification and validation tests.
