Analog Studies of the Limit-cycle Fuel Consumption of a Spinning Symmetric Drag-free Satellite
Analog simulation of limit-cycle fuel consumption of spinning symmetric drag-free satellite
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Analog simulation of limit-cycle fuel consumption of spinning symmetric drag-free satellite
Attitude-translation motion coupling effect on stability of gravity-stabilized drag-free satellites
Drag-free satellite design and propulsion requirements, noting orbit perturbation mechanisms
Drag-free satellite design and propulsion requirements, noting orbit perturbation mechanisms
Motion in the general gravity field is described mathematically. A covariance analysis, based on two simple models, is presented. Two drag-free space probes were considered, for which the orbital elements are given.
The design of a drag-free satellite and its application to measuring tidal interaction of the earth and tesseral harmonics are discussed. Principle areas of discussion are: (1) the feasibility of making geophysical measurements which are not possible with conventional satellites, and (2) design of attitude and translation control systems for spinning vehicle and possible coupling of attitude and translation control for gravity stabilized vehicles.
Zero gravity satellite concept feasibility and control system design evaluation using air cushion vehicle
Aeronomy experiment satellite polar orbit, control analysis, and control simulation
Control analysis of spinning drag free satellite controller to reduce trajectory errors from mass attraction
Drag free spacecraft performance in deep space, examining inner residual disturbance forces for motion control systems
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The use of estimators or observers is discussed as applied to satellite attitude control and the control of drag-free satellites. The practical problems of implementation are discussed, and the relative advantages of full and reduced state estimators are compared, particularly in terms of their effectiveness and bandwidth as filters. Three applications are used to illustrate the principles. They are: (1) a reaction wheel control system, (2) a spinning attitude control system, and (3) a drag-free satellite translational control system. Fixed estimator gains are shown to be adequate for these (and many other) applications. Our experience in the hardware realization of estimators has led to categorize the error sources in terms of those that improve with increased estimator gains and those that get worse with increased estimator gains.
Spurious solar-wind effects are a potential noise source in future Laser Interferometer Space Antenna (LISA) measurements. One noise coupling mechanism is constrained by estimating solar-wind effects on acceleration noise in LISA Pathfinder (LPF). While LISA is designed for drag-free differential measurement, predicting the realistic impact both bounds the operational environment and assesses whether LISA could provide serendipitous space-weather observations. Data from NASA's Advanced Composition Explorer (ACE), situated at the L1 Lagrange point, serves as a reliable source of solar-wind data. The data sets are compared over the 114 d time period from 1 March 2016 to 23 June 2016. This period gives the longest readily-available open data set, without interference from other commissioning activities. To evaluate space weather effects, the data from both satellites are formatted, gap-filled/interpolated, and fast-Fourier transformed for amplitude spectral density and coherence comparisons. Solar wind effects are not seen in a coherence plot between LPF and ACE; modest coherence in the planned LISA observational frequency band can be attributed to chance. This result indicates that measurable correlation due to solar-wind acceleration noise over 3 month timescales will be a negligible noise source. LISA is unlikely to inform solar wind measurements routinely. Another source of noise from the Sun, solar radiation pressure, is estimated to impart greater acceleration noise, but has yet to be analyzed.
Accuracy and speed comparison between drag-free and numerical satellite orbit prediction methods
Drag measuring requirements and comparison of accelerometer or drag-free satellite control systems usage for atmospheric density determination
Mean orbital elements for Vinti spheroidal theory of drag-free satellite motion applied to ballistic trajectories
Mean orbital element determination using Vintis spheroidal theory of drag-free satellite motion applied to ballistic trajectories
ESRO is considering a space experiment which is the definition phase. A more complete utilization of space techniques, leading to highly accurate acceleration measurements in a heliocentric spacecraft, together with an improved laser signal propagation method (using a space-borne atomic clock), could substantially increase the validity of the gravitational time delay test during solar conjunction. Preliminary investigations of the primary required techniques were carried out. These studies included an orbit analysis, investigation of drag-free techniques, and studies of the time measuring instrument. These studies were used to define the framework of a space experiment on gravitation theories. A preliminary feasibility study of the mission is being undertaken.