Catalogue Search | MBRL
Are you sure you want to remove the book from the shelf?
{{itemTitle}}
334
result(s) for
"Space vehicles Tracking."
Sort by:
Radio science techniques for deep space exploration
\"Radio signals are used to communicate information between robotic space missions throughout the solar system and stations on Earth. These signals are altered in their electromagnetic properties between transmission and reception due to propagation effects caused primarily by intervening media as well as forces acting on the spacecraft. When observed for their scientific potential, such alternations can provide very valuable information about the nature and environment of the planetary bodies or solar system targets under exploration. This also applies to signals transmitted from one spacecraft and received at another, in the case of multi-spacecraft missions. The media that the radio links propagate through include planetary atmospheres, ionospheres, rings, plasma tori, cometary material, or the solar corona. The Doppler shift to the frequency of the signals caused by the relative motion between the spacecraft and ground stations, or any transmitter-receiver combination, can contain scientific information about the gravitational forces acting on the spacecraft resulting from the bulk mass, density distribution, and global interior structure of the planets or moons, among other effects\"-- Provided by publisher.
BOOK
Navigation and Tracking in Space: Analysis and Algorithms
This book focuses on the navigation and tracking of artificial space objects, with emphasis on modelling the dynamics in a wide range of space missions, including: earth-orbiting satellite missions, launch and re-entry missions as well as interplanetary missions. The book guides you in designing suitable estimation algorithms for each type of mission. It also helps you in addressing non-linearity in designing navigation algorithms for space missions, and walks you through the process for choosing estimators for navigation and tracking of space vehicles. You’ll find specific details on earth-orbiting satellite tracking and navigation that helps you determine precise orbit, and will understand how to get navigation and tracking results using the Least Square Estimation and the Extended Kalman Filter (EKF) for simulated observations. You also learn how to address tracking performance of spacecraft in interplanetary trajectories that are affected by a diverse set of problems, such low signal power, intermittent observations, observations at low rate and delays. Techniques for designing navigation and tracking algorithms to address these problems are delineated. The book also provides in-depth coverage of multi-object tracking, relevant data association and estimation algorithms in the Situational Space Awareness context. MATLAB /Simulink based software is provided for simulation and simulated data set. This is an excellent reference and practical tool for professionals in the field of Guidance, Navigation and Control, along with researchers and advanced students in the field of space vehicle navigation, tracking, guidance and control.
eBook
In short. Episode 109, Space operations
Episode 109 - Ground Control: As a rocket blasts off from French Guiana controllers at the European Space Operations Centre in Germany commence a complex schedule of tasks known as the Launch and Early Orbit Phase.
Streaming Video
Event-triggered adaptive predefined-time anti-unwinding attitude tracking control for spacecraft
This paper addresses the problem of predefined-time attitude tracking control for rigid spacecraft subject to external disturbances and unknown inertia parameters. First, a predefined-time non-singular sliding surface is designed to ensure that the closed-loop system converges within a predefined time. Second, to tackle the unwinding problem inherent in quaternion-based modeling, a potential function is introduced in the controller design to guarantee anti-unwinding performance even outside the sliding surface. The proposed controller not only suppresses chattering but also ensures both anti-unwinding behavior and predefined-time convergence. Then, an event-triggered mechanism is developed to reduce communication burden while avoiding Zeno behavior. The proposed control method can make the attitude tracking error converge to an arbitrary predefined residual set. Finally, simulation results verify the effectiveness of the proposed method.
Journal Article
In-orbit demonstration of an iodine electric propulsion system
Propulsion is a critical subsystem of many spacecraft
1
–
4
. For efficient propellant usage, electric propulsion systems based on the electrostatic acceleration of ions formed during electron impact ionization of a gas are particularly attractive
5
,
6
. At present, xenon is used almost exclusively as an ionizable propellant for space propulsion
2
–
5
. However, xenon is rare, it must be stored under high pressure and commercial production is expensive
7
–
9
. Here we demonstrate a propulsion system that uses iodine propellant and we present in-orbit results of this new technology. Diatomic iodine is stored as a solid and sublimated at low temperatures. A plasma is then produced with a radio-frequency inductive antenna, and we show that the ionization efficiency is enhanced compared with xenon. Both atomic and molecular iodine ions are accelerated by high-voltage grids to generate thrust, and a highly collimated beam can be produced with substantial iodine dissociation. The propulsion system has been successfully operated in space onboard a small satellite with manoeuvres confirmed using satellite tracking data. We anticipate that these results will accelerate the adoption of alternative propellants within the space industry and demonstrate the potential of iodine for a wide range of space missions. For example, iodine enables substantial system miniaturization and simplification, which provides small satellites and satellite constellations with new capabilities for deployment, collision avoidance, end-of-life disposal and space exploration
10
–
14
.
The successful in-orbit operation of an electric space propulsion system based on iodine, rather than the more expensive and difficult-to-store xenon, is demonstrated.
Journal Article
Persistence-Weighted Performance Metric for PID Gain Optimization in Optical Tracking of Unknown Space Objects
Optical tracking of unknown space objects requires both spatial accuracy and temporal stability to enable high-resolution identification through narrow field-of-view sensors. Traditional performance indices such as RMS error and persistence time (PT) have been used for controller tuning, but they each capture only a subset of the requirements for successful optical identification. This paper proposes a new composite metric, the Persistence-Weighted Tracking Index (PWTI), which combines spatial precision and segment-level continuity into a single measure. The metric assigns a frame-level score based on positional error and accumulates weighted scores over the longest continuous in-threshold segment. Using PWTI as the optimization objective, a genetic algorithm (GA) is employed to tune the PID gains of a frame-by-frame offset correction controller. Comparative simulations under various observation scenarios demonstrate that the PWTI-based approach outperforms RMS- and PT-based tuning methods in both alignment accuracy and consistency. The results validate the proposed metric as a more suitable performance indicator for optical identification tasks involving unknown or uncataloged targets.
Journal Article
Enhanced attitude tracking control of spacecraft via inner and outer loop sliding mode design
The significance of spacecraft in modern aerospace and technology is indisputable, with attitude control systems (ACS) playing a vital role in ensuring mission accuracy and safety. This study presents a dual-loop sliding mode variable structure control approach for spacecraft attitude regulation, leveraging integral sliding mode control (SMC) to design robust switching functions. The outer loop generates the angular velocity command ω c by tracking the desired attitude angle θ , while the inner loop ensures accurate torque control based on this command. The control architecture comprises an inner velocity loop and an outer position loop, with the inner loop deliberately designed to converge faster, ensuring overall system stability. Numerical simulations validate the proposed strategy’s effectiveness and highlight its potential for real-world aerospace applications.
Journal Article
Finite-time attitude tracking control for spacecraft based on backstepping method with input saturation
In this paper, the finite-time attitude tracking control problem for spacecraft based on the backstepping method is addressed. Firstly, a finite-time controller is designed, which can provide robustness for external disturbance by employing an improved adaptation law. Secondly, a novel finite-time controller with input saturation is proposed by introducing the hyperbolic function and auxiliary system to guarantee the control torques below a predetermined value. The above two controllers are continuous, thus, they are chattering-free. Finally, simulation results are presented to illustrate the effectiveness of the control strategies.
Journal Article
An improved adaptive IMM-CKF method for tracking hypersonic glide vehicles via space-based radars
This paper proposes an improved adaptive IMM method for tracking glide vehicles to address the limitations of traditional algorithms, including fixed transition probability matrices, low model selection confidence and large tracking errors. Within the IMM framework, a constant acceleration model, a J2 perturbation model, and a current statistical model were integrated, and the cubature Kalman filter algorithm was employed for tracking hypersonic glide vehicles. To adaptively update the transition probability matrix, three mechanisms are introduced: (1) monitoring changes in model probabilities to detect trends in model dynamics; (2) analyzing variations in model likelihood functions to identify model transition phases; (3) employing a decision window to determine model stabilization periods. Simulation show that the proposed method significantly outperforms classical algorithms, achieving increase in position accuracy by 14.5 and 11.1%, and in velocity accuracy by 19.1 and 8.7%, compared with CKF and IMM-CKF, respectively. Furthermore, it reduces model distribution entropy, enhancing model selection performance, and providing support for space-based radar target tracking applications.
Journal Article