Nutational stability and passive control of spinning rockets with internal mass motion

Halsmer, Dominic; Mingori, D. L.

doi:10.2514/3.21525

Cited by 10 publications

(2 citation statements)

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“…Potential hazards of excessive nutation or coning motion might be poor initial conditions for subsequent mission operations, or possible loss of communications with a spacecraft due to incorrect pointing between its antenna and the base station. One such case of excessive nutation growth was observed in missions powered by the STAR-48 SRM [16,17,[28][29][30][31][32]. To mitigate this growth, an active nutation damper is used in these missions [33].…”

Section: Geometry Of Torque-free Motion and Nutation Angle Solutionmentioning

confidence: 99%

Geometry of motion and nutation stability of free axisymmetric variable mass systems

Nanjangud

2018

Nonlinear Dyn

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In classical mechanics, the 'geometry of motion' refers to a development to visualize the motion of freely spinning bodies. In this paper, such an approach of studying the rotational motion of axisymmetric variable mass systems is developed. An analytic solution to the second Euler angle characterising nutation naturally falls out of this method, without explicitly solving the nonlinear differential equations of motion. This is used to examine the coning motion of a free axisymmetric cylinder subject to three idealized models of mass loss and new insight into their rotational stability is presented. It is seen that the angular speeds for some configurations of these cylinders grow without bounds. In spite of this phenomenon, all configurations explored here are seen to exhibit nutational stability, a desirable property in solid rocket motors.allows Equations (11) and (12) to be combined to yield a differential equation linear in ω c :

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Section: Geometry Of Torque-free Motion and Nutation Angle Solutionmentioning

confidence: 99%

Geometry of motion and nutation stability of free axisymmetric variable mass systems

Nanjangud

2018

Nonlinear Dyn

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“…The use of shifting masses as attitude control actuators has already been proposed in the past to help detumble spacecraft (Edwards and Kaplan, 1974 ; Kunciw and Kaplan, 1976 ), control the coning motion of a spinning spacecraft (Hamidi-Hashemi, 1993 ; Halsmer and Mingori, 1995 ; Janssens and van der Ha, 2014 ), control the pitch and yaw of solar-sails (Wie, 2004 ; Wie and Murphy, 2007 ; Scholz et al, 2011 ) and, in general, to complement traditional attitude control actuators (Kumar, 2010 ; Ahn, 2012 ; Atkins and Henderson, 2012 ).…”

Section: Introductionmentioning

confidence: 99%

Attitude Stabilization of Spacecraft in Very Low Earth Orbit by Center-Of-Mass Shifting

2019

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At very low orbital altitudes ( 450 km) the aerodynamic forces can become major attitude disturbances. Certain missions that would benefit from a very low operational altitude require stable attitudes. The use of internal shifting masses, actively shifting the location of the spacecraft center-of-mass, thus modulating, in direction and magnitude, the aerodynamic torques, is here proposed as a method to reject these aerodynamic disturbances. A reduced one degree-of-freedom model is first used to evaluate the disturbance rejection capabilities of the method with respect to multiple system parameters (shifting mass, shifting range, vehicle size, and altitude). This analysis shows that small shifting masses and limited shifting ranges suffice if the nominal center-of-mass is relatively close to the estimated center-of-pressure. These results are confirmed when the analysis is extended to a full three rotational degrees-of-freedom model. The use of a quaternion feedback controller to detumble a spacecraft operating at very low altitudes is also explored. The analysis and numerical simulations are conducted using a nonlinear dynamic model that includes the full effects of the shifting masses, a realistic atmospheric model, and uncertain spacecraft aerodynamic properties. Finally, a practical implementation on a 3U CubeSat using commercial-off-the-shelf components is briefly presented, demonstrating the implementation feasibility of the proposed method.

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Approximate Solution to the Angular Speeds of a Nearly-Symmetric Mass-Varying Cylindrical Body

Nanjangud

Eke

2016

J of Astronaut Sci

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Nutational stability and passive control of spinning rockets with internal mass motion

Cited by 10 publications

References 1 publication

Geometry of motion and nutation stability of free axisymmetric variable mass systems

Geometry of motion and nutation stability of free axisymmetric variable mass systems

Attitude Stabilization of Spacecraft in Very Low Earth Orbit by Center-Of-Mass Shifting

Approximate Solution to the Angular Speeds of a Nearly-Symmetric Mass-Varying Cylindrical Body

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