Satellite Dynamics about Small Bodies: Averaged Solar Radiation Pressure Effects

1999 ◽  
Vol 47 (1-2) ◽  
pp. 25-46 ◽  
Author(s):  
D. J. Scheeres
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Pressure Effects ◽  
Small Bodies ◽  
Satellite Dynamics

Minimization of Solar Radiation Pressure Effects for Gravity-Gradient Stabilized Satellites

1966 ◽  
Vol 88 (2) ◽  
pp. 444-450 ◽  
Author(s):  
R. J. McElvain ◽  
L. Schwartz
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
External Disturbance ◽  
Solar Radiation Pressure ◽  
Pressure Effects ◽  
Gravity Gradient ◽  
Physical Parameters ◽  
Multiple Reflections ◽  
Minimization Procedure ◽  
Vehicle Configuration

The considerations necessary for minimization of solar radiation pressure effects for gravity-gradient stabilized vehicles are presented here. Owing to the rather weak restoring forces available for gravity-gradient stabilized vehicles, solar pressure torques represent a prime source of attitude errors unless steps are taken to minimize their effects. The solar torque minimization procedure generally consists of four distinct steps for a given vehicle configuration: (a) Derivation of the solar torque expressions for the characteristic vehicle configuration, including such effects as diffuse reflection, multiple reflections, and so on; (b) identification of the relative contribution of the solar torques on the various surfaces, and facilitation of solar torque minimization by balancing torque contributions of similar time variation and opposite sign against one another; (c) minimization of the torque about the vehicle axis with the weakest restoring torque (usually the local vertical) via optimization of reflectance characteristics and other physical parameters (using a steepest descent or similar approach); and (d) determination of the vehicle attitude response for the nominal configuration and reflectances, suggesting any configurational changes which might reduce peak attitude errors if necessary. The minimization procedure is performed in this paper using the NASA / Hughes Applications Technology Satellite (ATS) as a prime example of a gravity-gradient-stabilized satellite in an environment where solar pressure is the predominant external disturbance. The application of the solar balancing techniques to the ATS configuration resulted in peak yaw torques of less than 1 dyne-cm for the synchronous altitude satellite, and corresponding peak attitude errors of less than 1 deg in all axes due to solar pressure torques. Although the torque minimization procedures presented here are applicable in the general sense, the application of the techniques to a specific configuration requires derivation of the solar torque expressions for that particular configuration; therefore, the torque minimization example for the NASA/Hughes ATS vehicle can serve as a guide for other configuration applications.

scholarly journals Modelling of Solar Radiation Pressure Effects: Parameter Analysis for the MICROSCOPE Mission

2015 ◽  
Vol 2015 ◽  
pp. 1-14 ◽  
Author(s):  
Meike List ◽  
Stefanie Bremer ◽  
Benny Rievers ◽  
Hanns Selig
Keyword(s):  
Solar Radiation ◽  
Surface Properties ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Numerical Approach ◽  
Pressure Effects ◽  
Parameter Analysis ◽  
Optical Surface ◽  
Satellite Geometry ◽  
Conventional Models

Modern scientific space missions pose high requirements on the accuracy of the prediction and the analysis of satellite motion. On the one hand, accurate orbit propagation models are needed for the design and the preparation of a mission. On the other hand, these models are needed for the mission data analysis itself, thus allowing for the identification of unexpected disturbances, couplings, and noises which may affect the scientific signals. We present a numerical approach for Solar Radiation Pressure modelling, which is one of the main contributors for nongravitational disturbances for Earth orbiting satellites. The here introduced modelling approach allows for the inclusion of detailed spacecraft geometries, optical surface properties, and the variation of these optical surface properties (material degradation) during the mission lifetime. By using the geometry definition, surface property definitions, and mission definition of the French MICROSCOPE mission we highlight the benefit of an accurate Solar Radiation Pressure modelling versus conventional methods such as the Cannonball model or a Wing-Box approach. Our analysis shows that the implementation of a detailed satellite geometry and the consideration of changing surface properties allow for the detection of systematics which are not detectable by conventional models.

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