Noordwijk-Binnen, Netherlands
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Janssens F.L.,Wilhelminastraat 29 | Van Der Ha J.C.,5808 Bell Creek Road
Journal of Guidance, Control, and Dynamics | Year: 2015

The paper extends and clarifies the stability results for a spinning satellite under axial thrust in the presence of internal damped mass motion. It is known that prolate and oblate satellite configurations can be stabilized by damped mass motion. Here, the stability boundaries are established by exploiting the properties of the complex characteristic equation and the results are interpreted in terms of the physical system parameters. When the thrust level is the only free parameter, both prolate and oblate satellites can be stabilized provided that the thrust is within a specified range. This result is in contrast to the well-known maximum-axis rule for a free spinner where damping is always stabilizing (destabilizing) for an oblate (prolate) satellite. When adding a suitable spring-mass system, the minimum value of the spring constant that stabilizes the configuration can be established. In practice, however, the damping may well be too weak to be effective. Numerical illustrations are presented for the actual parameters of the Ulysses prolate configuration at orbit injection as well as for a fictitious oblate system. Finally, a new derivation of a previously established first integral for the undamped system is offered and its properties as a Lyapunov function are discussed. Copyright © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


Janssens F.L.,Wilhelminastraat 29 | van der Ha J.C.,5808 Bell Creek Road
Acta Astronautica | Year: 2015

The recovery from a flat-spin motion represents one of the most impressive practical applications in the field of spinning-satellite dynamics. The present paper presents flat-spin recovery maneuvers by means of a body-fixed torque within the plane perpendicular to the maximum principal axis of inertia. The conditions for a successful recovery are established. These are quite different from those obtained in the case when the torque is along the minimum axis of inertia where a minimum torque level is required for a successful recovery. If the torque component along the intermediate axis is negative, a recovery from a pure flat spin can be established for any torque magnitude. However, the time to recovery increases indefinitely when this torque component approaches zero. During the recovery maneuver, the angular velocity and angular momentum vectors become aligned with the minimum axis of inertia by turning over about 90° in the body frame. In inertial space, however, the angular momentum stays in the vicinity of its orientation before the start of the recovery. © 2015 IAA.


Janssens F.L.,Wilhelminastraat 29 | Van Der Ha J.C.,5808 Bell Creek Road
Acta Astronautica | Year: 2014

This paper considers a spinning rigid body and a particle with internal motion under axial thrust. This model is helpful for gaining insights into the nutation anomalies that occurred near the end of orbit injections performed by STAR-48 rocket motors. The stability of this system is investigated by means of linearized equations about a uniform spin reference state. In this model, a double root does not necessarily imply instability. The resulting stability condition defines a manifold in the parameter space. A detailed study of this manifold and the parameter space shows that the envelope of the constant solutions is in fact the stability boundary. Only part of the manifold defines a physical system and the range of frequency values that make the system unstable is restricted. Also it turns out that an increase of the spring stiffness, which restrains the internal motion, does not necessarily increase the stability margin. The application of the model is demonstrated using the orbit injection data of ESA's Ulysses satellite in 1990. © 2012 Elsevier B.V. All rights reserved.


Janssens F.,Wilhelminastraat 29 | Van Der Ha J.,5808 Bell Creek Rd
Advances in the Astronautical Sciences | Year: 2015

This paper discusses flat-spin recovery maneuvers by means of a body-fixed torque perpendicular to the maximum principal axis of inertia. The conditions for a successful recovery are established. These are quite different from those obtained when the torque is along the minimum axis of inertia where a minimum torque level is required for a successful recovery. If the torque component on the intermediate axis is negative, a recovery from a pure flat spin can be established for any torque magnitude but the time to recovery increases indefinitely. During the recovery maneuver, the angular velocity and angular momentum vectors become aligned with the minimum axis of inertia by turning over about 90° degrees in the body frame. In inertial space, however, the angular momentum stays in the vicinity of its orientation before the start of the recovery.


Janssens F.L.,Wilhelminastraat 29 | Van Der Ha J.C.,5808 Bell Creek Rd
Advances in the Astronautical Sciences | Year: 2013

The paper extends and clarifies the stability results for a spinning satellite under axial thrust in presence of internal damped mass motion. It is known that prolate and oblate satellite configurations can be stabilized by damped mass motion. Here, the stability boundaries are established by exploiting the properties of the complex characteristic equation and the results are interpreted in terms of the physical system parameters. When the thrust level is the only free parameter, both prolate and oblate satellites can be stabilized provided that the thrust is within a specified range. This result is in contrast to the well known maximumaxis rule for a free spinner where damping is always stabilizing (destabilizing) for an oblate (prolate) satellite. When adding a suitable spring-mass system, the minimum value of the spring constant required for stabilizing the configuration can be calculated. In practice, however, the damping may be too weak to be effective. Numerical illustrations are presented for the actual in-flight Ulysses parameters and for a fictitious oblate configuration. Finally, a new derivation of a previously established first integral for the undamped system is offered and its properties as a Lyapunov function are discussed. © 2013 2013 California Institute of Technology.


Janssens F.L.,Wilhelminastraat 29 | Van Der Ha J.C.,5808 Bell Creek Rd
Advances in the Astronautical Sciences | Year: 2014

The paper presents new analytical and numerical results in the field of self-excited rigid-body dynamics of spinning satellites. A practical solution for a flat-spin recovery maneuver is designed and evaluated. The proposed strategy uses a continuous body-fixed torque along the minor principal axis of inertia. The motion about the torque axis is similar to a pendulum which is either oscillating (i.e., no flat-spin recovery) or revolving (i.e., successful flat-spin recovery). The transition between these two cases defines the minimum required torque level. In the case when the recovery is successful the motion within the plane normal to the torque axis describes an ellipse with continuously growing angular velocity. The results established here are of considerable practical interest for the design of spacecraft that are required to spin about their minor axes of inertia due to launcher constraints or because of specific mission requirements.


Janssens F.L.,Wilhelminastraat 29 | Van Der Ha J.C.,5808 Bell Creek Rd.
Advances in the Astronautical Sciences | Year: 2012

This paper considers a spinning rigid body and a particle with internal motion under axial thrust. This model is helpful for gaining insights into the nutation anomalies that occurred near the end of orbit injections performed by STAR-48 rocket motors. The stability of this system is investigated by means of linearized equations about a uniform spin reference state. In this model, a double root does not necessarily imply instability. The resulting stability condition defines a manifold in the parameter space. A detailed study of this manifold and the parameter space shows that the envelope of the constant solutions is in fact the stability boundary. Only part of the manifold defines a physical system and the range of frequency values that make the system unstable is restricted. Also it turns out that an increase of the spring stiffness, which restrains the internal motion, does not necessarily increase the stability margin. The application of the model is demonstrated using the orbit injection data of ESA's Ulysses satellite in 1990.

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