Euler axis/angle is a useful representation in many attitude control problems, being related to the single rotation that takes an “initial” reference frame to a “target” reference frame. As a matter of fact, there are some cases in which the nominal rotation cannot be performed. It is the case of spacecraft in underactuated conditions, where attitude effectors can deliver a control torque with two components only. In a recent work an admissible rotation was proposed in order to minimize the alignment error between the target and the attainable attitude. In this paper, the kinematic equations of the nonnominal Euler axis/angle rotation are presented.
Euler axis/angle is a useful representation in many attitude control problems, being related to the single rotation that takes an "initial" reference frame to a "target" reference frame. As a matter of fact, there are some cases in which the nominal rotation cannot be performed. It is the case of spacecraft in underactuated conditions, where attitude effectors can deliver a control torque with two components only. In a recent work an admissible rotation was proposed in order to minimize the alignment error between the target and the attainable attitude. In this paper, the kinematic equations of the nonnominal Euler axis/angle rotation are Presented.
Kinematic equations of nonnominal euler axis/angle rotation / De Angelis, Emanuele L.; Giulietti, Fabrizio. - ELETTRONICO. - 153:(2015), pp. IAA-AAS-DyCoSS2 -14-10-01 AAS 14-566.999-IAA-AAS-DyCoSS2 -14-10-01 AAS 14-566.1007. (Intervento presentato al convegno 2nd International Academy of Astronautics Conference on Dynamics and Control of Space Systems, DyCoSS 2014 tenutosi a ita nel 2014).
Kinematic equations of nonnominal euler axis/angle rotation
De Angelis, Emanuele L.;Giulietti, Fabrizio
2015
Abstract
Euler axis/angle is a useful representation in many attitude control problems, being related to the single rotation that takes an "initial" reference frame to a "target" reference frame. As a matter of fact, there are some cases in which the nominal rotation cannot be performed. It is the case of spacecraft in underactuated conditions, where attitude effectors can deliver a control torque with two components only. In a recent work an admissible rotation was proposed in order to minimize the alignment error between the target and the attainable attitude. In this paper, the kinematic equations of the nonnominal Euler axis/angle rotation are Presented.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
