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  • Radiometric Autonomous Navigation Fused with Optical for Deep Space Exploration
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2021-01-22
    Todd A. Ely, Jill Seubert, Nicholas Bradley, Ted Drain, Shyam Bhaskaran

    With the advent of the Deep Space Atomic Clock, operationally accurate and reliable one-way radiometric data sent from a radio beacon (i.e., a DSN antenna or other spacecraft) and collected using a spacecraft’s radio receiver enables the development and use of autonomous radio navigation. This work examines the fusion of radiometric data with optical data (i.e. OpNav) to yield robust and accurate trajectory

    更新日期:2021-01-24
  • Optimal Landing Strategy on a Uniformly Rotating Homogeneous Rectangular Parallelepiped
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-12-02
    Deep Parikh, Ashish Tewari

    Low-thrust, optimal strategies are investigated for making a smooth landing on a uniformly rotating, homogeneous rectangular parallelepiped while avoiding the sharp corners during the approach. The individual effects of principal spherical harmonic coefficients on the stability against impact are determined numerically. An iterative predictor-corrector algorithm is utilized to find a direct and retrograde

    更新日期:2020-12-02
  • Optical Properties of Thermal Control Coatings after Exposure to 90 keV Electrons
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-11-21
    Elena A. Plis, Daniel P. Engelhart, Russel Cooper, Dale Ferguson, Stephanie Schiefer, Ryan Hoffmann, Heather Cowardin, Miles Bengtson, Jordan Maxwell

    Thermal control paints are widely used in spacecraft industry to protect the spacecraft/satellite surfaces from the deleterious effects of the space environment. Dynamic reflectivity of spacecraft materials must be taken into account for improved space situational awareness (SSA). Additionally, a thorough characterization of each spacecraft material’s optical properties while on orbit can be used for

    更新日期:2020-11-21
  • An Adaptive Analytic Continuation Method for Computing the Perturbed Two-Body Problem State Transition Matrix
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-11-16
    Tahsinul Haque Tasif, Tarek A. Elgohary

    In this work, the Taylor series based technique, Analytic Continuation is implemented to develop a method for the computation of the gravity and drag perturbed State Transition Matrix (STM) incorporating adaptive time steps and expansion order. Analytic Continuation has been developed for the two-body problem based on two scalar variables f and gp and their higher order time derivatives using Leibniz

    更新日期:2020-11-16
  • On-Orbit Observations of Conjuncting Space Objects Prior to the Time of Closest Approach
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-11-11
    Robert Lauchie Scott, Stefan Thorsteinson, Viqar Abbasi

    Conjunction assessment of space objects in Low Earth Orbit (LEO) generally uses information collected by ground-based space surveillance sensors. These sensors track both the primary object (normally an active satellite) and the secondary object (typically space debris). The tracking data is used to update both objects’ orbits for collision risk assessment. The primary satellite’s involvement in this

    更新日期:2020-11-12
  • Optimal Beacons Selection for Deep-Space Optical Navigation
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-11-10
    V. Franzese, F. Topputo

    Deep-space optical navigation is among the most promising techniques to autonomously estimate the position of a spacecraft in deep space. The method relies on the acquisition of the line-of-sight directions to a number of navigation beacons. The position knowledge depends upon the tracked objects. This paper elaborates on the impact of the observation geometry to the overall performances of the method

    更新日期:2020-11-12
  • Nonlinear Controller Design for a Flexible Spacecraft
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-10-23
    Jose Luis Redondo Gutiérrez, Ansgar Heidecker

    This paper combines the nonlinear Udwadia-Kalaba control approach with the Assumed Mode Method to model flexible structures and derives an attitude controller for a spacecraft. The study case of this paper is a satellite with four flexible cantilever beams attached to a rigid central hub. Two main topics are covered in this paper. The first one is the formulation of the equation of motion and the second

    更新日期:2020-10-30
  • A Deep Learning Approach to Hazard Detection for Autonomous Lunar Landing
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-10-21
    Rahul Moghe, Renato Zanetti

    A deep learning approach is presented to detect safe landing locations using LIDAR scans of the Lunar surface. Semantic Segmentation is used to classify hazardous and safe locations from a LIDAR scan during the landing phase. Digital Elevation Maps from the Lunar Reconnaissance Orbiter mission are used to generate the training, validation, and testing dataset. The ground truth is generated using geometric

    更新日期:2020-10-30
  • Autonomous Precision Control of Satellite Formation Flight under Unknown Time-Varying Model and Environmental Uncertainties
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-10-15
    Hancheol Cho, Firdaus E. Udwadia, Thanapat Wanichanon

    This paper presents a new methodology for autonomous precision control of satellite formations in the presence of uncertainties and external disturbances. The methodology is developed in two steps. First, using a nominal system model that provides the best assessment of real-life uncertainties, a nonlinear controller that satisfies the formation configuration requirements is developed without making

    更新日期:2020-10-16
  • Real-Time Plume Detection and Segmentation Using Neural Networks
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-10-13
    Dwight Temple

    Applications of artificial intelligence have been gaining extraordinary traction in recent years across innumerable domains. These novel approaches and technological leaps permit leveraging profound quantities of data in a manner from which to elucidate and ease the modeling of arduous physical phenomena. ExoAnalytic collects over 500,000 resident space object images nightly with an arsenal of over

    更新日期:2020-10-13
  • Lagrangian Derivation of Variable-Mass Equations of Motion using an Arbitrary Attitude Parameterization
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-10-09
    Charles Champagne Cossette, James Richard Forbes, David Saussié

    Lagrange’s equation is a popular method of deriving equations of motion due to the ability to choose a variety of generalized coordinates and implement constraints. When using a Lagrangian formulation, part of the generalized coordinates may describe the attitude. This paper presents a means of deriving the dynamics of variable-mass systems using Lagrange’s equation while using an arbitrary constrained

    更新日期:2020-10-11
  • An Iterative Convex Programming Method for Rocket Landing Trajectory Optimization
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-09-30
    Jinbo Wang, Huixu Li, Hongbo Chen

    A rapid trajectory optimization method is proposed to solve the fuel-optimal Earth-landing problem of reusable rockets, in which the nonlinear aerodynamic drag force is non-negligible. To enable the online and autonomous operation ability, the method is designed based on convex optimization, which features rapid and deterministic convergence properties, and a homotopic-iterative strategy is proposed

    更新日期:2020-10-02
  • Fuel-Efficient Powered Descent Guidance on Large Planetary Bodies via Theory of Functional Connections
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-09-25
    Hunter Johnston, Enrico Schiassi, Roberto Furfaro, Daniele Mortari

    In this paper we present a new approach to solve the fuel-efficient powered descent guidance problem on large planetary bodies with no atmosphere (e.g., Moon or Mars) using the recently developed Theory of Functional Connections. The problem is formulated using the indirect method which casts the optimal guidance problem as a system of nonlinear two-point boundary value problems. Using the Theory of

    更新日期:2020-09-25
  • Precise Formation-Flying Telescope in Target-Centric Orbit: the Solar Case
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-09-22
    Pascal Saint-Hilaire, Jeffrey E. Marchese

    We present the general concept of a telescope with optics and detectors mounted on two separate spacecrafts, in orbit around the telescope’s target (scopocentric or target-centric orbit), and using propulsion to maintain the Target-Optics-Detector alignment and Optics-Detector distance. Specifically, we study the case of such a telescope with the Sun as the target, orbiting at \(\sim \)1 AU. We present

    更新日期:2020-09-22
  • Multiple Heterogeneous Sensor Tasking Optimization in the Absence of Measurement Feedback
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-09-09
    Bryan D. Little, Carolin E. Frueh

    Observations of resident space objects generated by sensors are the primary method of maintaining knowledge of the object states. With the increasing number of objects, efficient sensor allocation is becoming integral. This requires the coordination of multiple sensors with different capabilities in an optimized manner. While the optimization is greatly simplified if instantaneous communication between

    更新日期:2020-09-08
  • Adaptive Attitude Controller Design for a Rigid Satellite with Feedback Linearization Approach
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Akram Adnane, Abdellatif Bellar, Mohammed Arezki Si Mohammed, Jiang Hong, Zoubir Ahmed Foitih

    This paper investigates a novel adaptive attitude controller design for rigid microsatellite based on feedback linearization approach, in which an accurate attitude pointing is required within a strict power limitation for space environment. The control strategy is performed to guarantee the stability of the satellite attitude under the effect of uncertain actuator parameters such as torque magnitude

    更新日期:2020-08-24
  • Ortho-Skew and Ortho-Sym Matrix Trigonometry
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Daniele Mortari

    This paper introduces some properties of two families of matrices: the Ortho-Skew , which are simultaneously orthogonal and skew-Hermitian, and the real Ortho-Sym matrices, which are orthogonal and symmetric. These relationships consist of closed-form compact expressions of trigonometric and hyperbolic functions that show that multiples of these matrices can be interpreted as angles. The analogies

    更新日期:2020-08-24
  • Real Time Attitude Independent GPS Integer Ambiguity Resolution
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    E. Glenn Lightsey,John L. Crassidis

    In this paper, a new motion-based approach for Global Positioning System (GPS) integer ambiguity resolution is derived. The approach first represents the GPS sightline vectors in the body frame or the baseline vectors in the reference frame. The solution to this problem is always available as long as at least three non-coplanar baseline or sightline vectors exist. The body-frame sightline or reference-frame

    更新日期:2020-08-24
  • Reliable Star Pattern Identification Technique by Using Neural Networks
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Kun Tae Kim,Hyochoong Bang

    An approach to systematically structuring star patterns and an associated identification technique using a neural network and rule-based expert system is addressed. In stellar-inertial navigation systems based upon modern star trackers, star pattern identification has been characterized primarily as a database search problem. The proposed algorithm herein provides a methodology on how to efficiently

    更新日期:2020-08-24
  • Attitude Estimation or Quaternion Estimation?
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    F. Landis Markley

    The absence of a globally nonsingular three-parameter representation of the rotation group forces attitude Kalman filters to estimate either a singular or a redundant attitude representation. We compare two filtering strategies using simplified kinematics and measurement models. Our favored strategy estimates a three-parameter representation of attitude deviations from a reference attitude specified

    更新日期:2020-08-24
  • An Efficient and Robust Singular Value Method for Star Pattern Recognition and Attitude Determination
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Jer-Nan Juang,Hye-Young Kim,John L. Junkins

    A new star pattern recognition method is developed using singular value decomposition of a measured unit column vector matrix in a measurement frame and the corresponding cataloged vector matrix in a reference frame. It is shown that singular values and right singular vectors are invariant with respect to coordinate transformation and robust under uncertainty. One advantage of singular value comparison

    更新日期:2020-08-24
  • Attitude Analysis in Flatland: The Plane Truth
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Malcolm D. Sinister

    Many results in attitude analysis are still meaningful when the attitude is restricted to rotations about a single axis. Such a picture corresponds to attitude analysis in the Euclidean plane. The present report formalizes the representation of attitude in the plane and applies it to some well-known problems in a two-dimensional setting. In particular we carry out a covariance of a two-dimensional

    更新日期:2020-08-24
  • Challenges and Prospects of Coulomb Spacecraft Formation Control
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Hanspeter Schaub,Gordon G. Parker,Lyon B. King

    Spacecraft formation flying using Coulomb forces is a relatively new technology for spacecraft control and may have application for a wide variety of mission objectives including attitude control, collision avoidance, and orbit perturbation correction. Coulomb-controlled formations appear ideally suited for close formation-flying in high Earth orbits to perform wide field of view imaging missions using

    更新日期:2020-08-24
  • Modeling and Control of Satellite Formations in High Eccentricity Orbits
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Prasenjit Sengupta,Srinivas R. Vadali,Kyle T. Alfriend

    An analytical method has been developed to propagate the relative motion between two satellites in highly elliptic orbits. The method is kinematically exact. It maintains a high degree of accuracy even in the presence of J 2 perturbations arising from the nonspherical nature of the Earth. The true anomaly of the reference satellite is treated as the independent variable, instead of time. The relative

    更新日期:2020-08-24
  • Hamel Coefficients for the Rotational Motion of a Rigid Body
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    J. E. Hurtado

    A Lagrangian treatment of various forms of the rigid-body equations of motion is presented in this paper, including the most general expressions, which are the Boltzmann-Hamel equations. One key result that enables the derivations is the expression for the Hamel coefficients for the special case of rotational motion of a rigid body. The Hamel coefficients naturally arise in the Lagrange equations for

    更新日期:2020-08-24
  • The Flower Constellations
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Daniele Mortari,Matthew P. Wilkins,Christian Bruccoleri

    This paper introduces a methodology to design a set of satellite constellations, called the Flower Constellations , which is generally characterized by repeatable ground tracks and a suitable phasing mechanism. A Flower Constellation , which can be complete or restricted , is identified by a number of parameters. Three are integer parameters: the number of petals ( N p), the number of sidereal days

    更新日期:2020-08-24
  • Detection of Tethered Satellite Systems
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Nammi J. Choe,John E. Cochran,Jung H. Jo

    The detection and identification of tethered satellite systems is a problem of current interest. Most previous studies focused on the detection and identification of one tethered satellite system using the observations of one satellite in the system. Here, we consider the problem of determining which of two or more satellites that are observed to be in relatively close proximity are tethered. Two-satellite

    更新日期:2020-08-24
  • Adaptive Control—A Departure from the Certainty-Equivalence Paradigm
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Maruthi R. Akella

    A fundamental study of indirect adaptive control addressed towards a class of uncertain mechanical and aerospace systems is the subject of this paper. We utilize and build upon certain recent techniques within adaptive control that permit nonlinear parameterization of uncertainty, thereby amounting to a significant shift from the classical certainty equivalence methodology. Instead of the more popular

    更新日期:2020-08-24
  • Nonlinear PID-Like Controllers for Rigid-Body Attitude Stabilization
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    Kamesh Subbarao

    Globally asymptotically stabilizing control laws are derived for rigid spacecraft attitude regulation. Two different approaches are introduced, one that seeks to derive a PID-like controller through a special Lyapunov function construction involving quadratic cross state weighting and the other via recursive passivation. Numerical simulations are performed to illustrate the performance of the two control

    更新日期:2020-08-24
  • How Nonlinear Is It? A Tutorial on Nonlinearity of Orbit and Attitude Dynamics
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-24
    John L. Junkins,Puneet Singla

    Some observations are made on coordinate selection for the two most fundamental problems of astrodynamics, namely orbit dynamics and attitude dynamics, and some interesting connections and analogies between the two problems are explored. While an infinity of coordinate choices are feasible for each of these problems, we review four coordinate choices for each problem, including several that lead to

    更新日期:2020-08-24
  • The Potential of Remote Sensing for Neutral Atmospheric Density Estimation in a Data Assimilation System
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    C. F. Minter,T. J. Fuller-Rowell,M. V. Codrescu

    New data assimilation techniques have improved time-dependent estimates of the neutral atmospheric density, making it possible to better estimate the drag perturbation on low-Earth-orbiting satellites. This study looks at the potential for using satellite remote sensing from space as an effective density observation source in a data assimilation system. Changes in the neutral density can occur on a

    更新日期:2020-08-23
  • Sliding Mode Control and Optimization for Six DOF Satellite Formation Flying Considering Saturation
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Yunjun Xu

    This paper considers the problem of controlling both position and attitude states for a formation flying system using only thrusters. A coupled six degree of freedom position and attitude model is derived, where the coupling comes from the gravity gradient torque. Furthermore, the J2 perturbation, mass variation, thruster model, and thruster layout are considered. A globally stable chattering free

    更新日期:2020-08-23
  • Zero Relative Radial Acceleration Cones and Controlled Motions Suitable for Formation Flying
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    G. Gómez,M. Marcote,J. J. Masdemont,J. M. Mondelo

    Assume that a constellation of satellites is required to remain close to a given nominal trajectory and that there is some freedom in the selection of the geometry of the constellation. If we are interested in avoiding large variations of the mutual distances between the spacecraft, we can consider the possible existence of regions of zero relative radial acceleration with respect to the nominal trajectory

    更新日期:2020-08-23
  • Large Aperture Space Telescopes in Formation: Modeling, Metrology, and Control
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Edward Mettler,William G. Breckenridge,Marco B. Quadrelli

    In this paper we summarize a concept definition and feasibility analysis for formation flying a representative large space telescope composed of separated optical elements. A virtual-structure construct (an equivalent rigid body) is created by unique metrology and control that combines both centralized and decentralized methods. The formation may be in orbit at GEO for super-resolution Earth observation

    更新日期:2020-08-23
  • An Analytical Solution for Relative Motion with an Elliptic Reference Orbit
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Yohannes Ketema

    A method for the determination of accurate analytical expressions for the time dependence of the relative motion of two noninteracting masses under the gravitational influence of a spherical primary mass is presented and discussed. The case of the elliptic reference orbit is considered and the case of a circular reference orbit is analyzed as a special case. The approach also leads to accurate initial

    更新日期:2020-08-23
  • Low Energy Interplanetary Transfers Exploiting Invariant Manifolds of the Restricted Three-Body Problem
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Francesco Topputo,Massimiliano Vasile,Franco Bernelli-Zazzera

    In this paper, a technique for the analysis and the design of low-energy interplanetary transfers, exploiting the invariant manifolds of the restricted three-body problem, is presented. This approach decomposes the full four-body problem describing the dynamics of an interplanetary transfer between two planets, in two three-body problems each one having the Sun and one of the planets as primaries;

    更新日期:2020-08-23
  • QUEST and The Anti-QUEST: Good and Evil Attitude Estimation
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Yang Cheng,Malcolm D. Shuster

    An attitude determination algorithm, proposed 25 years ago as a back-up algorithm in case the QUEST algorithm failed to function properly on its maiden mission, is finally compared with the QUEST algorithm. A comparison of the attitude determination accuracies of both algorithms is carried out using the QUEST measurement model. The back-up algorithm, which we have chosen to call “The Anti-QUEST,” while

    更新日期:2020-08-23
  • Minimum-Parameter Representations of N -Dimensional Principal Rotations
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Andrew J. Sinclair,John E. Hurtado

    Classic techniques have been established to characterize N × N proper orthogonal matrices using the N -dimensional Euler’s theorem and the Cayley transform. These techniques provide separate descriptions of N -dimensional orientation in terms of the constituent principal rotations or a minimum-parameter representation. The two descriptions can be linked by the canonical form of the extended Rodrigues

    更新日期:2020-08-23
  • Stable Constellations of Frozen Elliptical Inclined Lunar Orbits
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Todd A. Ely

    Higher altitude orbits (in the 500 to 20,000 km range) at the Moon are dominated by Earth perturbations and result in motions that do not ascribe to the standard notions of orbits dominated by nonspherical gravity effects (such as from oblateness). This fact complicates orbit design of lunar orbiter constellations that require specific and persistent coverage over a selected lunar region. Using a combination

    更新日期:2020-08-23
  • Modeling of Image Formation in Multi-Spacecraft Interferometric Imaging Systems
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Suman Chakravorty,Pierre T. Kabamba,David C. Hyland

    In this paper, we develop a detailed model of the process of image formation in Multi-Spacecraft Interferometric Imaging Systems (MSIIS). We show that the Modulation Transfer Function of, and the noise corrupting, the synthesized optical instrument are dependent on the trajectories of the constituent spacecraft and obtain these explicit functional relationships. We show that “good” imaging using MSIIS

    更新日期:2020-08-23
  • Automatic Generation and Integration of Equations of Motion for Flexible Multibody Dynamical Systems
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    D. Todd Griffith,James D. Turner,John L. Junkins

    In this paper, we consider a new direction for generating and simultaneously solving equations of motion for dynamical systems, using automatic differentiation. We overview the current computational approaches for solving multibody dynamics problems and discuss several choices for equation of motion formulation. We present an operator-overloading method for generating equations of motion automatically

    更新日期:2020-08-23
  • Dynamics of Lagrangian Point Multi-Tethered Satellite Systems
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    B. Wong,A. K. Misra

    This paper examines the dynamics of a tether-connected multi-spacecraft system, arranged in a wheel-spoke configuration, in the vicinity of the L2 Lagrangian point of the Sun-Earth system. Equilibrium configurations of the system are determined and small motions about one of these configurations are analyzed. A simple feedback controller is also developed to stabilize the motion of the system. Numerical

    更新日期:2020-08-23
  • Navigation Accuracy Guidelines for Orbital Formation Flying
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    J. Russell Carpenter,Kyle T. Alfriend

    Some simple guidelines based on the accuracy in determining a satellite formation’s semimajor axis differences are useful in making preliminary assessments of the navigation accuracy needed to support such missions. These guidelines are valid for any elliptical orbit, regardless of eccentricity. Although maneuvers required for formation establishment, reconfiguration, and station-keeping require accurate

    更新日期:2020-08-23
  • Relating Position Uncertainty to Maximum Conjunction Probability
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Salvatore Alfano

    The effects of positional uncertainty on the Gaussian probability computation for orbit conjunction are examined and an upper bound determined. Relative motion between two objects is assumed linear for a given encounter with time-invariant position covariance. A method is developed to assess the maximum probability for various satellite sizes, encounter geometries, and covariance sizes and shapes.

    更新日期:2020-08-23
  • A Simple Derivation of the Gauss-Bonet Theorem
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Ranjan Mukherjee,Malcolm D. Shuster

    A simple derivation of the Gauss-Bonet theorem is presented based on the representation of spherical polygons by Euler angles and Rodrigues transposition theorem. This leads to a derivation of the theorem which avoids completely the explicit evaluation of rotation matrices.

    更新日期:2020-08-23
  • MixTeam Scheduling Algorithms: Application to Space-Based Interferometric Observatories
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Venkatesh G. Rao,Pierre T. Kabamba

    Long-baseline interferometric observatories comprising multiple space telescopes in the same circular Earth orbit have been proposed for high-resolution imaging of exosolar planets. In this paper, we describe the novel class of MixTeam scheduling algorithms for such observatories. A range of schedulers within this class was evaluated through simulation. The results indicate that observation schedules

    更新日期:2020-08-23
  • Effects of Orbit Variations and J 2 Perturbations on a Class of Earth-Orbiting Interferometric Observatories
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Islam I. Hussein,Daniel J. Scheeres

    This paper revisits a class of Earth-orbiting interferometric observatories introduced previously and reviews the general procedures to achieve wave-number plane coverage. The effect of eccentric spacecraft trajectories and gravity field J 2 perturbations on wave-number plane coverage are considered. Conditions for complete wave-number plane coverage are found for certain classes of orbit perturbations

    更新日期:2020-08-23
  • Keeping a Spacecraft on the Sun-Earth Line
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Carlos M. Roithmayr,Linda Kay-Bunnell

    Measurements of Earth’s atmosphere as it occults sunlight can be obtained advantageously from a spacecraft placed in the proximity of the Sun-Earth Lagrange point ℒ 2 . Maintaining the condition of continuous solar occultation by all parts of the atmospheric disk requires that the displacement of the spacecraft perpendicular to the Sun-Earth line remains less than 200 km. However, the gravitational

    更新日期:2020-08-23
  • Systematic Identification of Preferred Orbits for Magnetospheric Missions: 1. Single Satellites
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    David P. Stern

    This is a systematic attempt to identify and assess near-equatorial, high-eccentricity orbits best suited for studying the Earth’s magnetosphere, in particular its most dynamic part, the plasma sheet of the magnetotail. The study was motivated by the design needs of a multi-spacecraft “constellation” mission, stressing low cost, minimal active control and economic launch strategies, and both quantitative

    更新日期:2020-08-23
  • Temporary Satellite Capture of Short-Period Jupiter Family Comets from the Perspective of Dynamical Systems
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    K. C. Howell,B. G. Marchand,M. W. Lo

    The Temporary Satellite Capture (TSC) of short-period comets, such as Oterma and Helin-Roman-Crockett, by Jupiter has intrigued astronomers for many years. A widely accepted approach to study TSC is to numerically integrate the equations of motion for the n -body problem using a wide range of initial conditions obtained from the heliocentric two- body problem; then, a search ensues for instances when

    更新日期:2020-08-23
  • Optimal Out-of-Ecliptic Trajectories for Space-Borne Observatories
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Pini Gurfil,N. Jeremy Kasdin

    In this paper novel trajectories that are particularly suitable for space-borne observation missions are introduced. Based on the framework of the spatial circular restricted three-body problem with the Sun and the Earth as the primaries and a special selection of a coordinate system, a family of trajectories with considerable displacements above the ecliptic plane is found. Stability analysis of these

    更新日期:2020-08-23
  • On the Information Dilution Theorem and Its Application to Attitude Determination
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Ilia Rapoport,Itzhack Y. Bar-Itzhack

    The information dilution theorem (IDT), as presented in the literature, shows the difference between the least squares (LS) estimate of the state of an ordinary linear system and the estimate of the state of the same system when a bias is added to it. In the formulation of the IDT it is tacitly assumed that each of the estimators uses the corresponding correct model. However, contrary to the claim

    更新日期:2020-08-23
  • Fuel-Saving Strategies for Dual Spacecraft Interferometry Missions
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Christopher A. Bailey,Timothy W. McLain,Randal W. Beard

    Separated spacecraft interferometry missions will require that spacecraft move in a coordinated fashion to ensure minimal and balanced consumption of fuel. This paper develops strategies for determining interferometry mission plans that result in significant fuel savings over standard approaches. Simulation results demonstrate that valuable reductions in fuel consumption can be realized by combining

    更新日期:2020-08-23
  • Mode and Logic-Based Switching for the Formation Flying Control of Multiple Spacecraft
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Mehran Mesbahi,Fred Y. Hadaegh

    Mode and logic-based switching for formation flying control is motivated and addressed in the context of separated spacecraft optical interferometry. In this venue, we show that logic-based switching is an attractive approach for satisfying multiple performance criteria during the different phases of a representative formation flying mission. Simulation results are provided to demonstrate the viability

    更新日期:2020-08-23
  • Flexible Spacecraft Reorientations Using Gimbaled Momentum Wheels
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Kevin A. Ford,Christopher D. Hall

    We study the reorientations of flexible spacecraft using momentum exchange devices. A new concise form of the equations of motion for a spacecraft with gimbaled momentum wheels and flexible appendages is presented. The derivation results in a set of vector nonlinear first order differential equations with gimbal torques and spin axis torques as the control inputs. Feedback control laws which result

    更新日期:2020-08-23
  • On the Rigid Rotation Concept in n -Dimensional Spaces
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Daniele Mortari

    A general mathematical formulation of the n × n proper orthogonal matrix, that corresponds to a rigid rotation in n -dimensional real Euclidean space, is given here. It is shown that a rigid rotation depends on an angle (principal angle) and on a set of (n ‒ 2) principal axes. The latter, however, can be more conveniently replaced by only two orthogonal directions that identify the plane of rotation

    更新日期:2020-08-23
  • Average and Maximum Revisit Time Trade Studies for Satellite Constellations Using a Multiobjective Genetic Algorithm
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Edwin A. Williams,William A. Crossley,Thomas J. Lang

    Recently, versions of the Genetic Algorithm (GA) have successfully generated low-Earth orbit sparse coverage satellite constellations that appear to outperform traditionally developed constellations. The objective of these constellations was to minimize the maximum revisit time over a latitude band of interest. However, many constellation designers are also concerned with the average revisit time,

    更新日期:2020-08-23
  • Moon Assisted Out of Plane Maneuvers of Earth Spacecraft
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    C. Circi,F. Graziani,P. Teofilatto

    This paper compares the usual Hohmann and bielliptic geostationary transfer orbits with lunar assisted transfers. It turns out that lunar assisted transfers are more economical for any inclination greater than the Moon orbit inclination. The lunar assisted transfers based on traditional flyby are analyzed: these are characterized by high values of the Keplerian apogee distance x a. Reducing such distance

    更新日期:2020-08-23
  • An Analytical Theory for Orbit Determination
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    George H. Born,David B. Goldstein,Blair Thompson

    The QuikScat spacecraft was launched in June 1999 and is currently measuring vector winds over the global oceans with a spatial resolution of 25 km and a temporal resolution of one day. The University of Colorado is responsible for mission operations, including production of the ephemeris used to produce the science data records. The navigation solutions from the onboard Motorola Vice Roy receiver

    更新日期:2020-08-23
  • Orbit Determination at a Single Ground Station Using Range Rate Data
    J. Astronaut. Sci. (IF 2.775) Pub Date : 2020-08-23
    Daniel Coyle,Henry J. Pernicka

    The solution of the spacecraft orbit determination problem is highly dependent upon the type of tracking data available at the ground station. Many algorithms exist for different types and combinations of tracking data. Well-funded tracking stations are typically able to supply six or more observed parameters simultaneously, enabling explicit solution of the orbit determination problem. The low-cost

    更新日期:2020-08-23
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