Relevant bibliographies by topics / Autonomous satellite navigation

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Autonomous satellite navigation'

Author: Grafiati
Published: 4 June 2021
Last updated: 18 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Autonomous satellite navigation.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Autonomous satellite navigation"

1

Gao, Youtao, Tanran Zhao, Bingyu Jin, Junkang Chen, and Bo Xu. "Autonomous Orbit Determination for Lagrangian Navigation Satellite Based on Neural Network Based State Observer." International Journal of Aerospace Engineering 2017 (2017): 1–10. http://dx.doi.org/10.1155/2017/9734164.

Full text
Abstract:
In order to improve the accuracy of the dynamical model used in the orbit determination of the Lagrangian navigation satellites, the nonlinear perturbations acting on Lagrangian navigation satellites are estimated by a neural network. A neural network based state observer is applied to autonomously determine the orbits of Lagrangian navigation satellites using only satellite-to-satellite range. This autonomous orbit determination method does not require linearizing the dynamical mode. There is no need to calculate the transition matrix. It is proved that three satellite-to-satellite ranges are needed using this method; therefore, the navigation constellation should include four Lagrangian navigation satellites at least. Four satellites orbiting on the collinear libration orbits are chosen to construct a constellation which is used to demonstrate the utility of this method. Simulation results illustrate that the stable error of autonomous orbit determination is about 10 m. The perturbation can be estimated by the neural network.
APA, Harvard, Vancouver, ISO, and other styles
2

Wang, Haihong, Zhonggui Chen, Jinjun Zheng, and Haibin Chu. "A New Algorithm for Onboard Autonomous Orbit Determination of Navigation Satellites." Journal of Navigation 64, S1 (October 14, 2011): S162—S179. http://dx.doi.org/10.1017/s0373463311000397.

Full text
Abstract:
Autonomous orbit determination of a navigation constellation is the process by which the orbit parameters of navigation satellites are autonomously calibrated onboard the satellites without the need for external aids. It commonly uses a satellite onboard data processing unit and a filtering method to process the measurements of inter-satellite ranges. The onboard data processing unit is the main module of autonomous navigation systems. In this paper, the two main factors that affect the accuracy of autonomous orbit determination for a navigation constellation are discussed first, and then a distributed onboard algorithm for autonomous orbit determination of navigation satellites is proposed. This method is based on a long-term ephemeris prediction and is suitable for the satellite hardware capability. The main feature of this method is that both the distributed computing method and an onboard analytical state transition matrix are used to process inter-satellite range measurements. One of the main advantages of this approach is high-speed computing since the amount of calculations needed is significantly less than that of the centralised computing method and those distributed methods that need to use an onboard numerical integrator. Another advantage of this approach is that the use of the onboard analytical state transition matrix algorithm can save a great amount of resources for both ground-to-satellite data transmissions and data storage units in satellites’ hardware. This could result in substantial cost reduction for space missions. Finally, a simulation method used for testing the proposed algorithm is presented. Results of tests over a period of 90 days show that the user range error of autonomous orbit determination derived from the proposed method is less than three metres.
APA, Harvard, Vancouver, ISO, and other styles
3

YongZhi, Wen, Zhang ZeJian, and Wu Jie. "High-Precision Navigation Approach of High-Orbit Spacecraft Based on Retransmission Communication Satellites." Journal of Navigation 65, no. 2 (March 12, 2012): 351–62. http://dx.doi.org/10.1017/s0373463311000671.

Full text
Abstract:
Many countries have presented new requirements for in-orbit space services. Space autonomous rendezvous and docking technology could speed up the development of in-orbit spacecraft and reduce the threat of increasing amounts of space debris. The purpose of this paper is to provide real-time high-precision navigation data for high-orbit spacecraft, thus reducing the cost of ground monitoring for high-orbit spacecraft autonomous rendezvous operations, and to provide technical support for high-orbit spacecraft in-orbit services. This paper proposes a new high-orbit spacecraft autonomous navigation approach, based on a communication satellite transmitting ground navigation signals. It proposes an overall navigation system design, sets up the system information integration model and analyses the precision of the navigation system by simulation research. Through simulation of this navigation method, the positional precision of a spacecraft at an altitude of 40 000 km, can be within 2·6 m with a velocity precision of 0·0011 m/s. The transponding satellite navigation method greatly reduces the development costs by using communication satellites in high-orbit spacecraft navigation instead of launching special navigation satellites. Moreover, the signals of transponding satellite navigation are generated on the ground, which is very convenient and cost-effective for system maintenance. In addition, placing atomic clocks on the ground may also help improve the clock accuracy achieved. In this study, the satellite-based navigation method is for the first time applied in high-orbit spacecraft navigation. The study's data could improve the present lack of effective high-orbit spacecraft navigation methods and provide strong technical support for autonomous rendezvous and docking of high orbital spacecraft, as well as other application fields.
APA, Harvard, Vancouver, ISO, and other styles
4

Hua, Bing, Zhiwen Zhang, Yunhua Wu, and Zhiming Chen. "Autonomous navigation algorithm based on AUKF filter about fusion of geomagnetic and sunlight directions." International Journal of Intelligent Computing and Cybernetics 11, no. 4 (November 12, 2018): 471–85. http://dx.doi.org/10.1108/ijicc-07-2017-0087.

Full text
Abstract:
Purpose The geomagnetic field vector is a function of the satellite’s position. The position and speed of the satellite can be determined by comparing the geomagnetic field vector measured by on board three-axis magnetometer with the standard value of the international geomagnetic field. The geomagnetic model has the disadvantages of uncertainty, low precision and long-term variability. Therefore, accuracy of autonomous navigation using the magnetometer is low. The purpose of this paper is to use the geomagnetic and sunlight information fusion algorithm to improve the orbit accuracy. Design/methodology/approach In this paper, an autonomous navigation method for low earth orbit satellite is studied by fusing geomagnetic and solar energy information. The algorithm selects the cosine value of the angle between the solar light vector and the geomagnetic vector, and the geomagnetic field intensity as observation. The Adaptive Unscented Kalman Filter (AUKF) filter is used to estimate the speed and position of the satellite, and the simulation research is carried out. This paper also made the same study using the UKF filter for comparison with the AUKF filter. Findings The algorithm of adding the sun direction vector information improves the positioning accuracy compared with the simple geomagnetic navigation, and the convergence and stability of the filter are better. The navigation error does not accumulate with time and has engineering application value. It also can be seen that AUKF filtering accuracy is better than UKF filtering accuracy. Research limitations/implications Geomagnetic navigation is greatly affected by the accuracy of magnetometer. This paper does not consider the spacecraft’s environmental interference with magnetic sensors. Practical implications Magnetometers and solar sensors are common sensors for micro-satellites. Near-Earth satellite orbit has abundant geomagnetic field resources. Therefore, the algorithm will have higher engineering significance in the practical application of low orbit micro-satellites orbit determination. Originality/value This paper introduces a satellite autonomous navigation algorithm. The AUKF geomagnetic filter algorithm using sunlight information can obviously improve the navigation accuracy and meet the basic requirements of low orbit small satellite orbit determination.
APA, Harvard, Vancouver, ISO, and other styles
5

Liao, Shilong, Zhaoxiang Qi, and Zhenghong Tang. "A Differential Measurement Method for Solving the Ephemeris Observability Issues in Autonomous Navigation." Journal of Navigation 68, no. 6 (May 25, 2015): 1133–40. http://dx.doi.org/10.1017/s0373463315000417.

Full text
Abstract:
The autonomous navigation of navigation and positioning systems such as the Global Positioning System (GPS) and other Global Navigation Satellite Systems (GNSS) was motivated to improve accuracy and survivability of the navigation function for 180 days without ground contact. These improvements are accomplished by establishing inter-satellite links in the constellation for pseudo-range observations and communications between satellites. But observability issues arise for both ephemeris and clock since the pseudo-range describes only the relative distance between satellites. A differential measurement method is proposed to measure the rotation of the constellation as a whole for the first time. The feasibility of the proposed method is verified by simulations.
APA, Harvard, Vancouver, ISO, and other styles
6

Baohua, Li, Lai Wenjie, Chen Yun, and Liu Zongming. "An Autonomous Navigation Algorithm for High Orbit Satellite Using Star Sensor and Ultraviolet Earth Sensor." Scientific World Journal 2013 (2013): 1–7. http://dx.doi.org/10.1155/2013/237189.

Full text
Abstract:
An autonomous navigation algorithm using the sensor that integrated the star sensor (FOV1) and ultraviolet earth sensor (FOV2) is presented. The star images are sampled by FOV1, and the ultraviolet earth images are sampled by the FOV2. The star identification algorithm and star tracking algorithm are executed at FOV1. Then, the optical axis direction of FOV1 at J2000.0 coordinate system is calculated. The ultraviolet image of earth is sampled by FOV2. The center vector of earth at FOV2 coordinate system is calculated with the coordinates of ultraviolet earth. The autonomous navigation data of satellite are calculated by integrated sensor with the optical axis direction of FOV1 and the center vector of earth from FOV2. The position accuracy of the autonomous navigation for satellite is improved from 1000 meters to 300 meters. And the velocity accuracy of the autonomous navigation for satellite is improved from 100 m/s to 20 m/s. At the same time, the period sine errors of the autonomous navigation for satellite are eliminated. The autonomous navigation for satellite with a sensor that integrated ultraviolet earth sensor and star sensor is well robust.
APA, Harvard, Vancouver, ISO, and other styles
7

Albukerque, J., J. L. Lair, B. Govin, G. Muller, P. Riant, D. Berton, and D.-F. Godart. "Autonomous Satellite Navigation Using Optico-Inertial Instruments." IFAC Proceedings Volumes 18, no. 4 (June 1985): 183–88. http://dx.doi.org/10.1016/s1474-6670(17)60887-5.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Popov, Sergey, Vladimir Zaborovsky, Leonid Kurochkin, Maksim Sharagin, and Lei Zhang. "Method of Dynamic Selection of Satellite Navigation System in the Autonomous Mode of Positioning." SPIIRAS Proceedings 18, no. 2 (April 12, 2019): 302–25. http://dx.doi.org/10.15622/sp.18.2.302-325.

Full text
Abstract:
Today, the list of applications that require accurate operational positioning is constantly growing. These tasks include: tasks of managing groups of Autonomous mobile robots, geodetic tasks of high-precision positioning, navigation and monitoring tasks in intelligent transport systems. Satellite navigation systems are a data source for operational positioning in such tasks. Today, global and local satellite navigation systems are actively used: GPS, GLONASS, BeiDou, Galileo. They are characterized by different completeness of satellite constellation deployment, which determines the accuracy of operational positioning in a particular geographical point, which depends on number of satellites available for observation, as well as the characteristics of the receiver, landscape features, weather conditions and the possibility of using differential corrections. The widespread use of differential corrections at the moment is not possible due to the fact that number of stable operating reference stations is limited - the Earth is covered by them unevenly; reliable data networks necessary for the transmission of differential corrections are also not deployed everywhere; budget versions of single-channel receivers of the navigation signal are widely used, which do not allow the use of differential corrections. In this case, there is a problem of operational choice of the system or a combination of satellite positioning systems, providing the most accurate navigation data. This paper presents a comparison of static and dynamic methods for selecting a system or a combination of satellite positioning systems that provide the most accurate definition of the object's own coordinates when using a single-channel receiver of navigation signals in offline mode. The choice is made on the basis of statistical analysis of data obtained from satellite positioning systems. During the analysis, the results of post-processing of data obtained from satellite navigation systems and refined with the use of differential corrections of navigation data were compared.
APA, Harvard, Vancouver, ISO, and other styles
9

Gao, Youtao, Junkang Chen, Bo Xu, and Jianhua Zhou. "Research on the Effectiveness of Different Estimation Algorithm on the Autonomous Orbit Determination of Lagrangian Navigation Constellation." International Journal of Aerospace Engineering 2016 (2016): 1–8. http://dx.doi.org/10.1155/2016/8392148.

Full text
Abstract:
The accuracy of autonomous orbit determination of Lagrangian navigation constellation will affect the navigation accuracy for the deep space probes. Because of the special dynamical characteristics of Lagrangian navigation satellite, the error caused by different estimation algorithm will cause totally different autonomous orbit determination accuracy. We apply the extended Kalman filter and the fading–memory filter to determinate the orbits of Lagrangian navigation satellites. The autonomous orbit determination errors are compared. The accuracy of autonomous orbit determination using fading-memory filter can improve 50% compared to the autonomous orbit determination accuracy using extended Kalman filter. We proposed an integrated Kalman fading filter to smooth the process of autonomous orbit determination and improve the accuracy of autonomous orbit determination. The square root extended Kalman filter is introduced to deal with the case of inaccurate initial error variance matrix. The simulations proved that the estimation method can affect the accuracy of autonomous orbit determination greatly.
APA, Harvard, Vancouver, ISO, and other styles
10

Zhang, Lei, and Bo Xu. "A Universe Light House — Candidate Architectures of the Libration Point Satellite Navigation System." Journal of Navigation 67, no. 5 (March 12, 2014): 737–52. http://dx.doi.org/10.1017/s0373463314000137.

Full text
Abstract:
In view of the shortcomings of existing satellite navigation systems in deep-space performance, candidate architectures which utilise libration point orbits in the Earth-Moon system are proposed to create an autonomous satellite navigation system for lunar missions. Three candidate constellations are systematically studied in order to achieve continuous global coverage for lunar orbits: the Earth-Moon L1,2 two-satellite constellation, the Earth-Moon L2,4,5 three-satellite constellation and the Earth-Moon L1,2,4,5 four-satellite constellation. After a thorough search for possible configurations, the latter two constellations are found to be the simplest feasible architectures for lunar navigation. Finally, an autonomous orbit determination simulation is performed to verify the autonomy of the system and two optimal configurations are obtained in a comprehensive consideration of coverage and autonomous orbit determination performance.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Autonomous satellite navigation"

1

Santiago, Luis. "AUTONOMOUS CONTROLS ALGORITHMFOR FORMATION FLYING OF SATELLITES." Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2641.

Full text
Abstract:
This document describes the design and analysis of the Navigation, Guidance and Control System for the KnightSat project. The purpose for the project is to test and demonstrate new technologies the Air Force would be interested in for research and development. The primary mission of KnightSat is to show how a constellation of satellites can maintain relative position with each other autonomously using the Microwave Electro Thermal (MET) thruster. The secondary mission is to use multiple satellite imagery to obtain 3 dimensional stereo photographs of observable terrain. Formation flying itself has many possible uses for future applications. Selected missions that require imaging or data collection can be more economically accomplished using smaller multiple satellites. The MET thruster is a very efficient, but low thrust alternative that can provide thrust for a very long time, hence provide the low thrust necessary to maintain the satellites at a constant separation. The challenge is to design a working control algorithm to provide the desired output data to be used to command the MET thrusters. The satellites are to maintain a constant relative distance from each other, and use the least amount of fuel possible. If one satellite runs out of fuel before the other, it would render the constellation less useful or useless. Hence, the satellites must use the same amount of fuel in order to maintain an optimal operational duration on orbit.
M.S.
Department of Mechanical, Materials and Aerospace Engineering;
Engineering and Computer Science
Aerospace Engineering
APA, Harvard, Vancouver, ISO, and other styles
2

Nolet, Simon 1975. "Development of a guidance, navigation and control architecture and validation process enabling autonomous docking to a tumbling satellite." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/39697.

Full text
Abstract:
Thesis (Sc. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2007.
Includes bibliographical references (p. 307-324).
The capability to routinely perform autonomous docking is a key enabling technology for future space exploration, as well as assembly and servicing missions for spacecraft and commercial satellites. Particularly, in more challenging situations where the target spacecraft or satellite is tumbling, algorithms and strategies must be implemented to ensure the safety of both docking entities in the event of anomalies. However, difficulties encountered in past docking missions conducted with expensive satellites on orbit have indicated a lack of maturity in the technologies required for such operations. Therefore, more experimentation must be performed to improve the current autonomous docking capabilities. The main objectives of the research presented in this thesis are to develop a guidance, navigation and control (GN&C) architecture that enables the safe and fuel-efficient docking with a free tumbling target in the presence of obstacles and anomalies, and to develop the software tools and verification processes necessary in order to successfully demonstrate the GN&C architecture in a relevant environment. The GN&C architecture was developed by integrating a spectrum of GN&C algorithms including estimation, control, path planning, and failure detection, isolation and recovery algorithms.
(cont.) The algorithms were implemented in GN&C software modules for real-time experimentation using the Synchronized Position Hold Engage and Reorient Experimental Satellite (SPHERES) facility that was created by the MIT Space Systems Laboratory. Operated inside the International Space Station (ISS), SPHERES allow the incremental maturation of formation flight and autonomous docking algorithms in a risk-tolerant, microgravity environment. Multiple autonomous docking operations have been performed in the ISS to validate the GN&C architecture. These experiments led to the first autonomous docking with a tumbling target ever achieved in microgravity. Furthermore, the author also demonstrated successful docking in spite of the presence of measurement errors that were detected and rejected by an online fault detection algorithm. The results of these experiments will be discussed in this thesis. Finally, based on experiments in a laboratory environment, the author establishes two processes for the verification of GN&C software prior to on-orbit testing on the SPHERES testbed.
by Simon Nolet.
Sc.D.
APA, Harvard, Vancouver, ISO, and other styles
3

Casadei, Alessandro. "An optical navigation filter simulator for a CubeSat mission to Didymos binary asteroid system." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019. http://amslaurea.unibo.it/17998/.

Full text
Abstract:
AIDA (Asteroid Impact and Deflection Assessment), is a joint NASA-ESA mission that will operate within 65803 Didymos binary system and whose main purpose is to experiment and investigate the kinetic impact technique for the deviation of the asteroid trajectories in space. HERA, the "mother" satellite designed by ESA, will aim to collect data about the chemical-physical composition of the binary system and about the characteristics of the impact between DART, the bullet-satellite realized and run by NASA, and the minor of the two celestial bodies that compose Didymos, which should occur around October 2022. HERA satellite will carry high-level technology onboard, including some CubeSats. This panorama also includes the DustCube mission, a project proposal for a CubeSat, whose main objective is to assist HERA in the acquisition of data. This thesis, as part of the DustCube project, aims at investigating the autonomous navigation of the CubeSat within the Didymos system, in particular through the development of a navigation filter based on optical observables. By making use of images gathered by a couple of infrared cameras, both LoS and range measurements are retrieved and fed to an Extended Kalman Filter. Results show that, even if implementing a reduced dynamical model within the filter, the expected position accuracy is below the requested 10 meters.
APA, Harvard, Vancouver, ISO, and other styles
4

Loizou, John. "An assessment of the autonomous integrity monitoring performance of a combined GPS/Galileo Satellite Navigation System, and its impact on the case for the development of Galileo." Thesis, Cranfield University, 2004. http://hdl.handle.net/1826/1604.

Full text
Abstract:
In 1999 Europe, through the European Commission and the European Space Agency, began detailed definition of a second generation Global Navigation Satellite System (GNSS). This GNSS development programme, known as “Galileo”, was intended to both complement and compete against the existing US Global Positioning System (GPS). Unlike GPS, Galileo is intended to be privately financed, following the initial development investment from the EC and ESA, which implies that Galileo should provide some revenue-earning services. From its earliest inception, the basis of these services has been assumed to be through the provision of Signal Integrity through an Integrity Flag broadcast through the Galileo system– a service which GPS cannot provide without some external system augmentation. This thesis undertakes a critical evaluation of the value of this integrity system in Galileo. This thesis has two parts. The first demonstrates that the conditions required to attract adequate private finance to the Galileo programme are incompatible with the system architecture derived from the early Galileo system studies and taken forward into the system early deployment phase, which includes an Integrity system within Galileo. The second part of this thesis aims to demonstrate that receivers which can combine the signals from GPS and Galileo may offer a free Integrity service which meet the needs of the majority of users, possibly up to the standards required for aviation precision approach. A novel Receiver Autonomous Integrity Monitoring (RAIM) technique is described, using an Errors in Variables/Total Least Squares approach to the detection of inconsistencies in an over-determined set of GNSS signal measurements. The mathematical basis for this technique is presented, along with results which compare the simulated performance of receivers using this algorithm against the expected performance of Galileo’s internal integrity determination system.
APA, Harvard, Vancouver, ISO, and other styles
5

Badger, Stanley. "Autonomous detection, navigation, and propulsion for satellites." Kansas State University, 2009. http://hdl.handle.net/2097/1402.

Full text
Abstract:
Master of Science
Department of Electrical and Computer Engineering
William B. Kuhn
With the increasing number of satellites and space debris in all orbits the need for individual satellites to be able to autonomously detect and determine methods to navigate around them is increasing. Even with continued input and control from a ground station, the ability for a satellite to act to save itself from obstacles not visible from ground stations, or if communications were temporarily lost could be key to saving millions of dollars in hardware as well as improving overall performance and operational lifetimes.
APA, Harvard, Vancouver, ISO, and other styles
6

Ramos, Bosch Pedro. "Improvements in autonomous GPS navigation of Low Earth Orbit satellites." Doctoral thesis, Universitat Politècnica de Catalunya, 2008. http://hdl.handle.net/10803/7019.

Full text
Abstract:
Es defineix un satèl·lit d'òrbita baixa aquell que es troba a una alçada de fins a 2000 km per sobre de la superfície de la Terra. Degut al ràpid decaïment dels objectes propers a la superfície degut al fregament atmosfèric, s'accepta que l'alçada típica per un LEO esta entre 200 i 2000 km.
Aquesta rang d'alçades fa que els LEO siguin utilitzats per un ampli rang d'aplicacions, com a repetidors de comunicacions, sensors remots, determinació gravimètrica i magnetomètrica, altimetria oceànica, determinació atmosfèrica i en operacions de Search and Rescue (Cerca i rescat). El seu posicionament precís és de gran importància per a poder complir correctament amb els seus objectius. En aquest sentit, una gran quantitat de satèl·lits LEO tenen un receptor GPS, que permet fer mesures GPS durant tot el seu recorregut al voltant de la Terra. Aquestes mesures poden ser utilitzades per determinar la trajectòria del satèl·lit. Aquesta operació es fa normalment a terra, després que el satèl·lit hagi transmès totes les mesures que ha pres. La capacitat de fer aquest posicionament en temps real a bord del satèl·lit és una necessitat per algunes aplicacions. El posicionament autònom es molt diferent del que es pot fer a terra, ja que el processador del satèl·lit te grans limitacions en recursos computacionals, per tant els complexos models i càlculs fets en un ordinador normal a terra, son completament excessius per un ordinador espacial. A més, alguns dels models utilitzats en l'estimació de la trajectòria necessiten dades addicionals (com activitat solar, o paràmetres de rotació de la Terra) que no son disponibles en temps real, per tant s'han de fer algunes aproximacions per tal de no necessitar cap d'aquestes dades. Aquesta tesis estudiarà la navegació autònoma amb GPS de satèl·lits LEO, tendència que esta incrementant la seva importància per les aplicacions tan científiques com tecnològiques que se'n poden derivar. La tesi desenvoluparà nous algoritmes i mètodes per obtenir una posició acurada i continua per LEOs. S'han cobert diferent aspectes:
· Mitigació de multipath e interferències. Les reflexions de senyals GPS en l'estructura del satèl·lit crea una distorsió que afecta la distància mesurada. La repetibilitat d'aquests efectes en relació amb l'orientació del satèl·lit pot ser utilitzat per a mitigar el seu impacte en la solució de navegació. S'han desenvolupat tècniques de mitigació de multipath i interferències per receptors d'una i de dos freqüències.
· Models dinàmics de forces. L'alta predictibilitat de la trajectòria d'objectes orbitant la Terra pot ser utilitzat en sinergia amb el GPS per a aconseguir solucions més precises que fent servir únicament GPS. Això s'utilitza normalment en estratègies en postprocess, però te grans requeriments computacionals, i necessita paràmetres no disponibles en temps real. La simplificació d'aquests models, i la supressió de paràmetres no disponibles es necessari per poder aplicar aquesta tècnica de processat en condicions de temps real.
· Maniobres. Els cossos en òrbita al voltant de la Terra no segueixen una trajectòria perfectament predeible. Hi han petites pertorbacions que modifiquen la seva trajectòria a llarg termini, i a més, el fregament atmosfèric frena poc a poc al satèl·lit, disminuint la seva alçada. Això fa necessari una correcció periòdica de la seva trajectòria, realitzat amb petits impulsos del sistema de propulsió del satèl·lit en lo que s'anomena una maniobra. Quan un satèl·lit es troba en una maniobra, deixa de seguir els models de caiguda lliure, per tant la maniobra s'ha de tenir en conte en l'estimació del filtre.
Tots els algoritmes i mètodes dissenyats han sigut testejats amb dades reals de diferents missions: SAC-C, CHAMP, JASON-1 i GRACE. S'han fet servir diversos tests cobrint diferents opcions de parametrització per tal d'avaluar el seu comportament.
Se define un satélite de órbita baja aquel que se encuentra en una altura de hasta 2000 km sobre la superficie terrestre. Debido al rápido decaimiento de los objetos cercanos a la superficie debido al fregamiento atmosférico se acepta que la altura típica para un LEO se sitúa entre 200 y 2000 km.
Este rango de alturas hace que los LEO sean utilizados para un amplio rango de aplicaciones como repetidores de comunicaciones, sensores remotos, determinación gravimétrica y magnetométrica, altimetría oceánica, determinación atmosférica y en operaciones de Search and Rescue (Búsqueda y rescate). Su posicionamiento preciso es de gran importancia para poder cumplir correctamente con sus objetivos. En este sentido, una gran cantidad de satélites LEO disponen de un receptor GPS, que permite realizar medidas GPS durante todo su recorrido alrededor de la Tierra. Estas medidas puede ser utilizadas para determinar la trayectoria del satélite. Esta operación se suele realizar en tierra, después que el satélite haya retransmitido todas las medidas que ha tomado. La capacidad de hacer este posicionamiento en tiempo real a bordo del satélite es una necesidad para algunas aplicaciones. El posicionamiento autónomo es muy diferente al que se puede realizar en tierra, ya que los procesadores de satélites tienen limitaciones en recursos computacionales, y por tanto los complejos modelos y cálculos realizados en un ordenador normal en tierra son excesivos para un ordenador espacial. Además, algunos de los modelos utilizados en la estimación de la trayectoria necesitan datos adicionales (como actividad solar, o parámetros de rotación de la Tierra) que no están disponibles en tiempo real, por lo que hay que realizar algunas aproximaciones para no necesitar ninguno de estos datos. Esta tesis estudiará la navegación autónoma mediante GPS en satélites LEO, tendencia que esta aumentando su importancia por las aplicaciones tanto científicas como tecnológicas que se pueden derivar. La tesis desarrollara nuevos algoritmos y métodos para obtener una posición precisa y continua para LEOs. Se han cubierto diferentes aspectos:
· Mitigación de multipath e interferencias. Las reflexiones de las señales GPS en la estructura del satélite crea una distorsión que afecta la distancia medida. La repetibilidad de estos efectos en relación con la orientación del satélite puede ser utilizado para mitigar su impacto en la solución de navegación. Se han desarrollado técnicas de mitigación de multipath e interferencias para receptores de una o dos frecuencias.
· Modelos dinámicos de fuerzas. La trayectoria de objetos orbitando la Tierra es muy predecible, lo cual puede ser usado en sinergia con GPS para conseguir posiciones más precisas que usando solo GPS. Esto se utiliza normalmente en estrategias en postproceso, pero tiene grandes necesidades computacionales, y requiere de parámetros no disponibles en tiempo real. La simplificación de estos modelos, y la supresión e esos parámetros es necesario para poder aplicar esta técnica de procesado en condiciones de tiempo real.
· Maniobras. Los cuerpos en órbita alrededor de la Tierra no siguen una trayectoria perfectamente predecible. Hay pequeñas perturbaciones que modifican su trayectoria a largo plazo. Además el fregamiento atmosférico frena poco a poco el satélite, reduciendo su altura. Esto hace que sea necesaria una corrección periódica de su trayectoria, realizado en pequeños impulsos por el sistema de propulsión del satélite en lo que se llama una maniobra. Cuando un satélite realiza una maniobra deja de comportarse según los modelos de caida libre, por tanto su maniobra se ha de tener en cuenta en la estimación del filtro. Todos los algoritmos y métodos diseñados han sido testeados con datos reales de diferentes misiones: SAC-C, CHAMP, JASON-1 y GRACE. Se han realizado un amplio abanico de tests cubriendo diferentes opciones de parametrización para evaluar su comportamiento.
Satellites in low Earth orbits (LEO) are generally defined to be up to an altitude of 2000 km above Earth's surface and given the rapid decay of objects on the lower altitude range due to atmospheric drag, it is commonly accepted that a typical LEO height lies between 200 and 2000 km. This altitude range makes LEO satellites useful for a wide range of applications such as communication transponders, remote sensing, gravimetric and magnetometric sounding, ocean altimetry, atmospheric retrieval and Search and Rescue alarm operations. Its accurate positioning is of great importance in the successful accomplishment of their objectives. In this sense, most LEO satellites have a GPS receiver, which allows to collect GPS measurements in its full revolution around the Earth. These measures can be used to precisely estimate the trajectory of the spacecraft. This operation is normally done on ground, after the satellite was able to downlink all the data it collected. The capacity to do this positioning in real-time onboard the satellite is a necessity for some of the applications, and would also allow a faster science product delivery.
This autonomous positioning is very different that the one that can be done on ground, as the satellite processor has large limitations in computational resources, so the complex models and calculus done in a normal computer on ground are completely unaffordable for the onboard processor. Besides, some of the models used in the trajectory estimation need some additional data (such as solar activity, or Earth rotation parameters) that are not available in real-time, so some approximations must be done to cope with these lack of data. This thesis will deepen into the study of autonomous GPS navigation of LEO satellites, a trend that is increasing its importance for their applications in both science and technological fields. It will develop new algorithms and methods in order to provide accurate and continuous positions for the satellites. Different aspects have been covered:
· Multipath and interference mitigation. Reflections of GPS signals in the spacecraft structure cause a distress that affects the measured distance. On the other hand, some spacecraft have more than one GPS antenna on its payload. This creates a cross-talk interference that also affects the measures. The repeatability of these effects in relation to the attitude of the spacecraft can be used to mitigate its impact into the final navigation solution. Multipath mitigation techniques have been developed for both single- and dual-frequency receivers.
· Dynamic force models. The high predictability of the trajectory of Earth orbiters is used in conjunction to GPS measurements to provide a more accurate solution than GPS standalone positions. This is a widely used technique in postprocessing strategies, but has high computational requirements and needs parameters not available in real-time. The simplifications of these models, along with the suppression of the parameters not available in an onboard environment is necessary to use these kind of positioning by a satellite processing in real-time conditions.
· Maneuver handling. Earth orbiters do not follow a fully predictable orbit, some low-order perturbations modifies its trajectory on the long term, and atmospheric drag slowly brakes the satellite, decreasing its altitude. This makes necessary a periodic correction of its trajectory.
This is done by short impulses produced by the satellite propulsion systems in what is called a maneuver. When a spacecraft is in a maneuver, it no longer follows the free-flight dynamic models, so this should be taken into account in the estimation filter. All the algorithms and methods have been tested with real data from different missions: SAC-C, CHAMP, JASON-1 and GRACE. Several test cases covering a wide range of days and parametrization options have been done in order to assess its performance.
APA, Harvard, Vancouver, ISO, and other styles
7

Nagarajan, N. "Autonomous Orbit Estimation For Near Earth Satellites Using Horizon Scanners." Thesis, Indian Institute of Science, 1994. http://hdl.handle.net/2005/155.

Full text
Abstract:
Autonomous navigation is the determination of satellites position and velocity vectors onboard the satellite, using the measurements available onboard. The orbital information of a satellite needs to be obtained to support different house keeping operations such as routine tracking for health monitoring, payload data processing and annotation, orbit manoeuver planning, and prediction of intrusion in various sensors' field of view by celestial bodies like Sun, Moon etc. Determination of the satellites orbital parameters is done in a number of ways using a variety of measurements. These measurements may originate from ground based systems as range and range rate measurements, or from another satellite as in the case of GPS (Global Positioning System) and TDUSS (Tracking Data Relay Satellite Systems), or from the same satellite by using sensors like horizon sensor^ sun sensor, star tracker, landmark tracker etc. Depending upon the measurement errors, sampling rates, and adequacy of the estimation scheme, the navigation accuracy can be anywhere in the range of 10m - 10 kms in absolute location. A wide variety of tracking sensors have been proposed in the literature for autonomous navigation. They are broadly classified as (1) Satellite-satellite tracking, (2) Ground- satellite tracking, (3) fully autonomous tracking. Of the various navigation sensors, it may be cost effective to use existing onboard sensors which are well proven in space. Hence, in the current thesis, the Horizon scanner is employed as the primary navigation sensor-. It has been shown in the literature that by using horizon sensors and gyros, a high accuracy pointing of the order of .01 - .03 deg can be achieved in the case of low earth orbits. Motivated by such a fact, the current thesis deals with autonomous orbit determination using measurements from the horizon sensors with the assumption that the attitude is known to the above quoted accuracies. The horizon scanners are mounted on either side of the yaw axis in the pitch yaw plane at an angle of 70 deg with respect to the yaw axis. The Field Of View (FOV) moves about the scanner axis on a cone of 45 deg half cone angle. During each scan, the FOV generates two horizon points, one at the space-Earth entry and the other at the Earth-space exit. The horizon points, therefore, lie• on the edge of the Earth disc seen by the satellite. For a spherical earth, a minimum of three such horizon points are needed to estimate the angular radius and the center of the circular horizon disc. Since a total of four horizon points are available from a pair of scanners, they can be used to extract the satellite-earth distance and direction.These horizon points are corrupted by noise due to uncertainties in the Earth's radiation pattern, detector mechanism, the truncation and roundoff errors due to digitisation of the measurements. Owing to the finite spin rate of the scanning mechanism, the measurements are available at discrete time intervals. Thus a filtering algorithm with appropriate state dynamics becomes essential to handle the •noise in the measurements, to obtain the best estimate and to propagate the state between the measurements. The orbit of a low earth satellite can be represented by either a state vector (position and velocity vectors in inertial frame) or Keplerian elements. The choice depends upon the available processors, functions and the end use of the estimated orbit information. It is shown in the thesis that position and velocity vectors in inertial frame or the position vector in local reference frame, do result in a simplified, state representation. By using the f and g series method for inertial position and velocity, the state propagation is achieved in linear form. i.e. Xk+1 = AXK where X is the state (position, velocity) and A the state transition matrix derived from 'f' and 'g' series. The configuration of a 3 axis stabilised spacecraft with two horizon scanners is used to simulate the measurements. As a step towards establishing the feasibility of extracting the orbital parameters, the governing equations are formulated to compute the satellite-earth vector from the four horizon points generated by a pair of Horizon Scanners in the presence of measurement noise. Using these derived satellite-earth vectors as measurements, Kalman filter equations are developed, where both the state and measurements equations are linear. Based on simulations, it is shown that a position accuracy of about 2 kms can be achieved. Additionally, the effect of sudden disturbances like substantial slewing of the solar panels prior and after the payload operations are also analysed. It is shown that a relatively simple Low Pass Filter (LPF) in the measurements loop with a cut-off frequency of 10 Wo (Wo = orbital frequency) effectively suppresses the high frequency effects from sudden disturbances which otherwise camouflage the navigational information content of the signal. Then Kalman filter can continue to estimate the orbit with the same kind of accuracy as before without recourse to re-tuning of covariance matrices. Having established the feasibility of extracting the orbit information, the next step is to treat the measurements in its original form, namely, the non-linear form. The entry or exit timing pulses generated by the scanner when multiplied by the scan rate yield entry or exit azimuth angles in the scanner frame of reference, which in turn represents an effective measurement variable. These azimuth angles are obtained as inverse trigonometric functions of the satellite-earth vector. Thus the horizon scanner measurements are non-linear functions of the orbital state. The analytical equations for the horizon points as seen in the body frame are derived, first for a spherical earth case. To account for the oblate shape of the earth, a simple one step correction algorithm is developed to calculate the horizon points. The horizon points calculated from this simple algorithm matches well with the ones from accurate model within a bound of 5%. Since the horizon points (measurements) are non-linear functions of the state, an Extended Kalman Filter (EKF) is employed for state estimation. Through various simulation runs, it is observed that the along track state has got poor observability when the four horizon points are treated as measurements in their original form, as against the derived satellite-earth vector in the earlier strategy. This is also substantiated by means of condition number of the observability matrix. In order to examine this problem in detail, the observability of the three modes such as along-track, radial, and cross-track components (i.e. the local orbit frame of reference) are analysed. This difficulty in observability is obviated when an additional sensor is used in the roll-yaw plane. Subsequently the simulation studies are carried out with two scanners in pitch-yaw plane and one scanner in the roll-yaw plane (ie. a total of 6 horizon points at each time). Based on the simulations, it is shown that the achievable accuracy in absolute position is about 2 kms.- Since the scanner in the roll-yaw plane is susceptible to dazzling by Sun, the effect of data breaks due to sensor inhibition is also analysed. It is further established that such data breaks do not improve the accuracy of the estimates of the along-track component during the transient phase. However, filter does not diverge during this period. Following the analysis of the' filter performance, influence of Earth's oblateness on the measurement model studied. It is observed that the error in horizon points, due to spherical Earth approximation behave like a sinusoid of twice the orbital frequency alongwith a bias of about 0.21° in the case of a 900 kms sun synchronous orbit. The error in the 6 horizon points is shown to give rise to 6 sinusoids. Since the measurement model for a spherical earth is the simplest one, the feasibility of estimating these sinusoids along with the orbital state forms the next part of the thesis. Each sinusoid along with the bias is represented as a 3 state recursive equation in the following form where i refers to the ith sinusoid and T the sampling interval. The augmented or composite state variable X consists of bias, Sine and Cosine components of the sinusoids. The 6 sinusoids together with the three dimensional orbital position vector in local coordinate frame then lead to a 21 state augmented Kalman Filter. With the 21 state filter, observability problems are experienced. Hence the magnetic field strength, which is a function of radial distance as measured by an onboard magnetometer is proposed as additional measurement. Subsequently, on using 6 horizon point measurements and the radial distance measurements obtained from a magnetometer and taking advantage of relationships between sinusoids, it is shown that a ten state filter (ie. 3 local orbital states, one bias and 3 zero mean sinusoids) can effectively function as an onboard orbit filter. The filter performance is investigated for circular as well as low eccentricity orbits. The 10-state filter is shown to exhibit a lag while following the radial component in case of low eccentricity orbits. This deficiency is overcome by introducing two more states, namely the radial velocity and acceleration thus resulting in a 12-state filter. Simulation studies reveal that the 12-state filter performance is very good for low eccentricity orbits. The lag observed in 10-state filter is totally removed. Besides, the 12-state filter is able to follow the changes in orbit due to orbital manoeuvers which are part of orbit acquisition plans for any mission.
APA, Harvard, Vancouver, ISO, and other styles
8

Srivardhan, D. "Autonomous Navigation Using Global Positioning System." Thesis, 2004. http://hdl.handle.net/2005/1137.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

"Improvements in autonomous GPS navigation of Low Earth Orbit satellites." Universitat Politècnica de Catalunya, 2008. http://www.tesisenxarxa.net/TDX-0312109-123420/.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Autonomous satellite navigation"

1

Farrell, James L. GNSS aided navigation & tracking: Inertially augmented or autonomous. Baltimore, Md: American Literary Press, 2007.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

Flight Mechanics Symposium (1999 Goddard Space Flight Center). 1999 Flight Mechanics Symposium: Proceedings of a conference sponsored and held at NASA Goddard Space Flight Center, Greenbelt, Maryland, May 18-28, 1999. Washington, DC: National Aeronautics and Space Administration, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

S, Border J., and Jet Propulsion Laboratory (U.S.), eds. Observation model and parameter partials for the JPL geodetic GPS modeling software "GPSOMC". Pasadena, Calif: National Aeronautics and Space Administration, Jet Propulsion Laboratory, California Institute of Technology, 1988.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

J, Priovolos George, Rhodehamel Harley, George C. Marshall Space Flight Center., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Autonomous integrated GPS/INS navigation experiment for OMV: Phase I feasibility study. [Huntsville, Ala.?]: George C. Marshall Space Flight Center, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

Autonomous integrated GPS/INS navigation experiment for OMV: Phase I feasibility study. [Cleveland, Ohio]: George C. Marshall Space Flight Center, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

1999 Flight mechanics symposium. Greenbelt, Md: The Center, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

P, Lynch John, and Goddard Space Flight Center, eds. 1999 Flight mechanics symposium. Greenbelt, Md: The Center, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Autonomous satellite navigation"

1

Mao, Yue, Xiaoyong Song, Xiaolin Jia, Xianbing Wu, and Yisong Gong. "Analysis on Pulsar Based Inter-Satellite Link Autonomous Navigation." In Lecture Notes in Electrical Engineering, 531–40. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-29187-6_52.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Jia, Weisong, Qiuli Chen, Ying Wu, and Haihong Wang. "Design and Verification of Long-Term Reliable Autonomous Navigation System of Navigation Satellite." In Lecture Notes in Electrical Engineering, 679–90. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3707-3_63.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Wang, Wei, Xurong Dong, Wanke Liu, Ying Liu, Sihui Liu, and Chengeng Su. "Influence of Satellite-to-Ground Link on the Autonomous Navigation of Navigation Constellation." In Lecture Notes in Electrical Engineering, 337–48. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-29175-3_30.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Liang, Xiao-peng, Jun Li, Zhao-hui Wang, and Kong-yang Peng. "Research on Autonomous Navigation of Navigation Constellation Based on X-Ray Pulsars and Satellite-to-Satellite Link." In Proceedings of the 6th International Asia Conference on Industrial Engineering and Management Innovation, 899–910. Paris: Atlantis Press, 2015. http://dx.doi.org/10.2991/978-94-6239-148-2_89.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Yang, Daoning, Gang Li, Ying Liu, Jun Yang, Yinan Meng, and Xianyu Zhang. "Research on Distributed Autonomous Time Reference Maintain Method of Navigation Constellation." In China Satellite Navigation Conference (CSNC) 2017 Proceedings: Volume III, 55–63. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-4594-3_6.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Zhao, Jun, Taogao Dai, and Chen Chen. "A New Method for Multiple Outliers Detection in Receiver Autonomous Integrity Monitoring." In China Satellite Navigation Conference (CSNC) 2016 Proceedings: Volume II, 151–64. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0937-2_13.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Wang, Tengfei, Zheng Yao, and Mingquan Lu. "Carrier Measurements Based Autonomous Spatial Reference Establishment for Ground-Based Positioning Systems." In China Satellite Navigation Conference (CSNC) 2020 Proceedings: Volume III, 538–49. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3715-8_48.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Liu, Peng, and Xi-Yun Hou. "Combined Autonomous Orbit Determination of GEO/IGSO Satellites on the Space-Based Probe." In China Satellite Navigation Conference (CSNC) 2014 Proceedings: Volume III, 241–50. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54740-9_22.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Wang, Haiong, Qiuli Chen, Weisong Jia, and Chengpan Tang. "Research on Autonomous Orbit Determination Test Based on BDS Inter-Satellite-Link on-Orbit Data." In China Satellite Navigation Conference (CSNC) 2017 Proceedings: Volume III, 89–99. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-4594-3_9.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Xiong, Kai, Yuan Zhang, and Yan Xing. "Measurement Selection for Autonomous Satellite Constellation Navigation Using Parallel Extended Kalman Filters." In Lecture Notes in Electrical Engineering, 628–36. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-32-9698-5_70.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Autonomous satellite navigation"

1

Bowyer, Michael, Angelo Bertani, Erik Aitken, and Samir A. Rawashdeh. "Landmark Based Autonomous Snowplow Navigation." In 29th International Technical Meeting of The Satellite Division of the Institute of Navigation (ION GNSS+ 2016). Institute of Navigation, 2016. http://dx.doi.org/10.33012/2016.14622.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Tesler, Mikhail, Anatoliy Shapovalov, and Nikolay Shchetkin. "Possibilities of Autonomous Spacecraft Navigation by Satellite Imagery." In 2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS). IEEE, 2020. http://dx.doi.org/10.23919/icins43215.2020.9133910.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Xu Bo and Bingjun Shao. "Satellite selection algorithm for combined GPS-Galileo navigation receiver." In 2009 4th International Conference on Autonomous Robots and Agents. IEEE, 2009. http://dx.doi.org/10.1109/icara.2000.4803918.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Collins, John, and Robert Conger. "MANS - Autonomous navigation and orbit control for communications satellites." In 15th International Communicatons Satellite Systems Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1127.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Varriale, Enrico, Pablo Corbal�n, Timofei Istomin, and Gian Pietro Picco. "PLaNS: An Autonomous Local Navigation System." In 31st International Technical Meeting of The Satellite Division of the Institute of Navigation (ION GNSS+ 2018). Institute of Navigation, 2018. http://dx.doi.org/10.33012/2018.15898.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Yang, Huixin, Weihua Zhang, and Zhenyu Jiang. "Autonomous Navigation of Satellite Formation for Small Bodies Exploration." In AIAA Guidance, Navigation, and Control (GNC) Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-5249.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

PETERSEN, STEVEN. "Autonomous satellite navigation system using the Global Positioning System." In 26th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-379.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Menggen, Subuda, Pingyuan Cui, and Shengying Zhu. "Networked Mars satellite system design and autonomous navigation analysis." In 2014 26th Chinese Control And Decision Conference (CCDC). IEEE, 2014. http://dx.doi.org/10.1109/ccdc.2014.6852747.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Li, Taohu, Jiansheng Liu, Zhigang Huang, and Honglei Qin. "Observability of HEO Satellite Autonomous Navigation System Using GPS." In 2010 International Conference on Multimedia Technology (ICMT). IEEE, 2010. http://dx.doi.org/10.1109/icmult.2010.5631285.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Xue, Qing, Hongwen Yang, and Jian Wang. "An Angle Estimation to Landmarks for Autonomous Satellite Navigation." In 2016 5th International Conference on Environment, Materials, Chemistry and Power Electronics. Paris, France: Atlantis Press, 2016. http://dx.doi.org/10.2991/emcpe-16.2016.140.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Autonomous satellite navigation"

1

White, R. L., and R. B. Gounley. Satellite Autonomous Navigation with SHAD (Stellar Horizon Atmospheric Dispersion). Fort Belvoir, VA: Defense Technical Information Center, April 1987. http://dx.doi.org/10.21236/ada184988.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Autonomous satellite navigation' for particular source types:
Journal articles
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography