Review of Attitude Representations Used for Aircraft Kinematics

Phillips, Warren F.; Hailey, Christine E.; Gebert, Glenn

doi:10.2514/2.3083

Cited by 61 publications

(54 citation statements)

References 3 publications

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“…We chose to express the attitude in Euler angles representation because it is more intuitive than quaternion for the reader. The mathematical transformation between the quaternion and Euler angles was given in [24]. The results show that the q-AKF can provide the best performance even during the high external acceleration phases, for example during the interval (23-30 s).…”

Section: A Adaptive Filter Performances With γ =mentioning

confidence: 99%

Adaptive Kalman filter for MEMS-IMU based attitude estimation under external acceleration and parsimonious use of gyroscopes

Makni

Fourati

Kibangou

2014

2014 European Control Conference (ECC)

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Section: A Adaptive Filter Performances With γ =mentioning

confidence: 99%

Adaptive Kalman filter for MEMS-IMU based attitude estimation under external acceleration and parsimonious use of gyroscopes

Makni

Fourati

Kibangou

2014

2014 European Control Conference (ECC)

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“…Inertial frame to Body frame The transformation from the Inertial frame to the Body frame is done using quaternions and the rotation matrix takes the form [24]: The angular velocities in the Body frame can now be determined using: respectively measured from the hinge point of the wings, located at the nose. This position can be seen in Fig.…”

Section: Of 31mentioning

confidence: 99%

Rigid-Body Kinematics Versus Flapping Kinematics of a Flapping Wing Micro Air Vehicle

Caetano

Weehuizen

Visser

et al. 2015

Journal of Guidance, Control, and Dynamics

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“…twelve differential equations including: force equations, kinematic equations, moment equations and navigation equations [48]. In this model, the kinematics equations are changed to the Euler- Rodrigues quaternions [49], as quaternion equations are linear and the solution is free from the singularity exhibited with simple Euler angle equations.…”

Section: Equation Of Motion-thementioning

confidence: 99%

A Mars VTOL Aerobot - Preliminary Design, Dynamics and Control

Song

Underwood

2007

2007 IEEE Aerospace Conference

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Abstract-In this paper, we propose the use of a novel fixed-wing vertical take-off and landing (VTOL) aerobot. A mission profile to investigate the Isidis Planitia region of Mars is proposed based on the knowledge of the planet's geophysical characteristics, its atmosphere and terrain. The aerobot design is described from the aspects of vehicle selection, its propulsion system, power system, payload, thermal management, structure, mass budget, and control strategy and sensor suite. The aerobot proposed in this paper is believed to be a practical and realistic solution to the problem of investigating the Martian surface. A six-degreeof-freedom flight simulator has been created to support the aerobot design process by providing performance evaluations. The nonlinear dynamics is then linearized to a state-space formulation at a certain trimmed equilibrium point Basic autopilot modes are developed for the aerobot based on the linearized state-space model. The results of the simulation show the aerobot is stable and controllable.

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Review of Attitude Representations Used for Aircraft Kinematics

Cited by 61 publications

References 3 publications

Adaptive Kalman filter for MEMS-IMU based attitude estimation under external acceleration and parsimonious use of gyroscopes

Adaptive Kalman filter for MEMS-IMU based attitude estimation under external acceleration and parsimonious use of gyroscopes

Rigid-Body Kinematics Versus Flapping Kinematics of a Flapping Wing Micro Air Vehicle

A Mars VTOL Aerobot - Preliminary Design, Dynamics and Control

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