Get Aerospace Avionics Systems: A Modern Synthesis PDF

By George Siouris

ISBN-10: 0126468907

ISBN-13: 9780126468908

Aerospace Avionics structures: a contemporary Synthesis is the 1st new textbook on inertial navigation because the mid-1970s. This far-reaching, up to date, and seriously illustrated quantity meets the desires of first-year graduate scholars in aeronautical engineering in addition to the calls for of pros requiring present details. The well-respected writer offers a balanced blend of conception and up to date perform and alertness in inertial navigation, devoting the most important quantity of area to themes that may be priceless to so much readers or that aren't accurately or basically taken care of in different places within the technical literature.

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Extra info for Aerospace Avionics Systems: A Modern Synthesis

Sample text

2. Coordinate Transformations 21 standardized definitions of the Euler angles. For a particular choice of Euler angles, the rotation order selected and/or defined must be used consistently. That is, if the order of rotation is interchanged, a different Euler angle representation is defined. As stated above, the position of the body axes can be arrived at by a series of three ordered right-handed rotations. With the (x, y, z ) axes coinciding with the ( X , Y, 2 ) axes, a rotation is made of the ( X , Y, Z ) system about the Z axis through an angle yr, the yaw or heading angle.

Pitch angle is the angle betwcen the body axis and the hody axis pri~jectionon the liorirontal plane. yh into the horizo~ltalplanc. In this transformation, it will be assumed that the navigation frame is defined by the local earth axes with thc x,, axis pointing north, the y,, iixis east. and the 2 , axis down. With this arrangement of navigation coordinates, wc have a righthanded north east d o w n (NED) system. The geometric configuration of the aircraft body axes is illustrated in Fig. 2-9. Also, this figure shows the order o r rotation from the navigation axes to the body axes.

R,v, z) body axes relative to thc inertial ( X . Y . Z ) t~xcs. as depicted in Fig. 2-4. The Euler angles (I), 0, yr) correspond to thc convcntional roll pitch yaw angles. For cxamplc, the heading (yaw) of an aircraft is displayed to the pilot on a heading indicator, such as the heading situation indicator (HSI). while the pitch and roll of the aircraft arc indicalcd o n an attitude indicator, such as the attitude direction indicator (AT)[). It should be pointed out, however. that the Euler angles are not uniquely defined.

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Aerospace Avionics Systems: A Modern Synthesis by George Siouris


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