Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208461
Nazli Can
GNSS (Global Navigation Satellite Systems) are used in many areas of our lives including but not limited to the transportation, agriculture, construction, surface mining, surveying and mapping. Therefore the continuity and accuracy of the data provided by the GNSS is higly important and within this scope the cyber threats should be both technically and legally evaluated. In this article the concept of cyber threat for GNSS is briefly introduced in the first section and relevant legal issues are presented in the second section.
{"title":"Legal issues concerning the cyber security of GNSS","authors":"Nazli Can","doi":"10.1109/RAST.2015.7208461","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208461","url":null,"abstract":"GNSS (Global Navigation Satellite Systems) are used in many areas of our lives including but not limited to the transportation, agriculture, construction, surface mining, surveying and mapping. Therefore the continuity and accuracy of the data provided by the GNSS is higly important and within this scope the cyber threats should be both technically and legally evaluated. In this article the concept of cyber threat for GNSS is briefly introduced in the first section and relevant legal issues are presented in the second section.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"136 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114410754","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208449
R. Kawashima, S. Nakasuka, K. Schilling, Yasuyuki Miyazaki, Sir Martin Sweeting
Long term sustainability is vital to the future space activities. This is a key theme of the discussions in global space forums such as UNCOPUOS. UNISEC in Japan and UNISEC-Global has been facilitating practical space engineering education using nano-satellites. The issues of increasing density of debris in orbit and limited resources of radio frequencies are very relevant to nano-satellite activities at university level. In this paper, firstly UNISEC-Global is introduced, secondly, the concept of space sustainablity is described. Thirdly, UNISEC-Global's contribution to improving awareness of space sustainability among universities across the world is described, and fourthly, innovative technological approaches which may assist in the solution to these problems are introduced, followed by a discussion on the role of UNISEC-Global initiatives in this field.
{"title":"UNISEC-Global challenge: How can UNISEC-Global contribute to long term sustainability of space activities?","authors":"R. Kawashima, S. Nakasuka, K. Schilling, Yasuyuki Miyazaki, Sir Martin Sweeting","doi":"10.1109/RAST.2015.7208449","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208449","url":null,"abstract":"Long term sustainability is vital to the future space activities. This is a key theme of the discussions in global space forums such as UNCOPUOS. UNISEC in Japan and UNISEC-Global has been facilitating practical space engineering education using nano-satellites. The issues of increasing density of debris in orbit and limited resources of radio frequencies are very relevant to nano-satellite activities at university level. In this paper, firstly UNISEC-Global is introduced, secondly, the concept of space sustainablity is described. Thirdly, UNISEC-Global's contribution to improving awareness of space sustainability among universities across the world is described, and fourthly, innovative technological approaches which may assist in the solution to these problems are introduced, followed by a discussion on the role of UNISEC-Global initiatives in this field.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115710049","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208347
Mustafa Teke, Ismail Tevrizoglu, A. F. Oztoprak, C. Demirkesen, Ibrahim S. Acikgoz, S. Gurbuz, Ramazan Kupcu, Bulent Avenoglu
Over the years, rapidly developing satellite technologies have greatly increased the amount and size of data; e.g. high resolution imagery of 31 cm (e.g. World View 3) and even video. As satellites become increasingly more complex and remote sensing capabilities improve, the demands on faster and more accurate data processing to enable the full potential of data exploitation likewise increases. In this light, TÜBlTAK UZAY has developed a satellite image processing and sharing platform, dubbed GEOPORTAL, to provide the software and informatics infrastructure required to facilitate sharing and processing. GEOPORTAL also includes modules enabling critical functions, such as radiometric and geometric correction, as well as other core satellite image processing routines, to serve images in formats ready for research and remote sensing applications.
{"title":"GEOPORTAL: Tübİtak Uzay satellite data processing and sharing system","authors":"Mustafa Teke, Ismail Tevrizoglu, A. F. Oztoprak, C. Demirkesen, Ibrahim S. Acikgoz, S. Gurbuz, Ramazan Kupcu, Bulent Avenoglu","doi":"10.1109/RAST.2015.7208347","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208347","url":null,"abstract":"Over the years, rapidly developing satellite technologies have greatly increased the amount and size of data; e.g. high resolution imagery of 31 cm (e.g. World View 3) and even video. As satellites become increasingly more complex and remote sensing capabilities improve, the demands on faster and more accurate data processing to enable the full potential of data exploitation likewise increases. In this light, TÜBlTAK UZAY has developed a satellite image processing and sharing platform, dubbed GEOPORTAL, to provide the software and informatics infrastructure required to facilitate sharing and processing. GEOPORTAL also includes modules enabling critical functions, such as radiometric and geometric correction, as well as other core satellite image processing routines, to serve images in formats ready for research and remote sensing applications.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"331 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116235579","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208435
C. Hajiyev, Ece Sevim Conguroglu
In this study an integrated Algebraic method/ Extended Kalman fitler (EKF) attitude determination system is presented, in which the 2-vector and EKF algorithms are combined to estimate the attitude angles and angular velocities. As a reference directions for algebraic method, the unit vectors toward the Sun and Earth's Magnetic Field are used. The Euler angles produced 2-vector algorithm and their error variances are provided as input to the EKF. Then the EKF uses this attitude information as the measurements for providing more accurate attitude estimates even when the satellite is in eclipse. The “attitude angle error covariance matrix” calculated for the estimations of the algebraic method are regarded as the measurement noise covariance for the EKF. The parameters of satellite's rotational motion (Euler angles and angular velocities) are estimated using EKF. In comparison to more traditional approaches, this preprocessing step significantly reduces the complexity of filter design by allowing the use of linear measurement equations.
{"title":"Integration of algebraic method and EKF for attitude determination of small information satellites","authors":"C. Hajiyev, Ece Sevim Conguroglu","doi":"10.1109/RAST.2015.7208435","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208435","url":null,"abstract":"In this study an integrated Algebraic method/ Extended Kalman fitler (EKF) attitude determination system is presented, in which the 2-vector and EKF algorithms are combined to estimate the attitude angles and angular velocities. As a reference directions for algebraic method, the unit vectors toward the Sun and Earth's Magnetic Field are used. The Euler angles produced 2-vector algorithm and their error variances are provided as input to the EKF. Then the EKF uses this attitude information as the measurements for providing more accurate attitude estimates even when the satellite is in eclipse. The “attitude angle error covariance matrix” calculated for the estimations of the algebraic method are regarded as the measurement noise covariance for the EKF. The parameters of satellite's rotational motion (Euler angles and angular velocities) are estimated using EKF. In comparison to more traditional approaches, this preprocessing step significantly reduces the complexity of filter design by allowing the use of linear measurement equations.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115107295","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208389
M. Sahin, M. Cihan, M. O. Kaya
This paper contains calculations about propellant slosh for an upper stage rocket. The liquid fuel is modeled by using an equivalent mechanical model, from this point of view the stability of this rocket is examined by means of mass-spring model. In theory, a nonlinear mathematical model is derived and nonlinear feedback control laws are used. Specifications of the Attitude Vernier Upper Module (AVUM) upper stage rocket Vega are chosen for simulations. The results of this study are obtained for first four slosh modes.
{"title":"Model and control problem for space vehicles with propellant slosh","authors":"M. Sahin, M. Cihan, M. O. Kaya","doi":"10.1109/RAST.2015.7208389","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208389","url":null,"abstract":"This paper contains calculations about propellant slosh for an upper stage rocket. The liquid fuel is modeled by using an equivalent mechanical model, from this point of view the stability of this rocket is examined by means of mass-spring model. In theory, a nonlinear mathematical model is derived and nonlinear feedback control laws are used. Specifications of the Attitude Vernier Upper Module (AVUM) upper stage rocket Vega are chosen for simulations. The results of this study are obtained for first four slosh modes.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126826522","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208352
Muhammed Akif Ağca, Emre Baceski, Serhan Gokcebag
Automated image exploitation algorithms requires both computation power and fast disk access. Ordinary hardware or a sequential processing architecture is far from performing with acceptable performance, while dealing with huge satellite imagery data. In this work, a memory centric analytics solution is proposed for performing querying, graph based operations, machine learning and stream processing effectively. A proof of concept experiment was performed in order to demonstrate the effect of memory centric operations on big data. The initial results show that, memory centric analytics has great potential for imagery exploitation.
{"title":"MEMCA for satellite and space data: MEMCA [Memory centric analytics] for satellite and space data","authors":"Muhammed Akif Ağca, Emre Baceski, Serhan Gokcebag","doi":"10.1109/RAST.2015.7208352","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208352","url":null,"abstract":"Automated image exploitation algorithms requires both computation power and fast disk access. Ordinary hardware or a sequential processing architecture is far from performing with acceptable performance, while dealing with huge satellite imagery data. In this work, a memory centric analytics solution is proposed for performing querying, graph based operations, machine learning and stream processing effectively. A proof of concept experiment was performed in order to demonstrate the effect of memory centric operations on big data. The initial results show that, memory centric analytics has great potential for imagery exploitation.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"135 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123449060","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208436
Y. Somov, S. Butyrin, S. Somov, C. Hajiyev
We present method for in-flight signal processing and calibration of a strap-down inertial navigation system (SINS) for the information mini-satellites at low Earth orbit. We have applied the SINS correction based on the signals of a sun-magnetic system and consider the problem at a long-term forecasting of the mini-satellite's orbital motion.
{"title":"Low cost attitude determination system for a LEO information mini-satellite","authors":"Y. Somov, S. Butyrin, S. Somov, C. Hajiyev","doi":"10.1109/RAST.2015.7208436","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208436","url":null,"abstract":"We present method for in-flight signal processing and calibration of a strap-down inertial navigation system (SINS) for the information mini-satellites at low Earth orbit. We have applied the SINS correction based on the signals of a sun-magnetic system and consider the problem at a long-term forecasting of the mini-satellite's orbital motion.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122806107","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208410
Mert Satir, Firat Sik, Emre Turkoz, M. Çelik
For better integration of plasma thrusters into spacecraft and satellites, potential damaging effects of impinging high energy ions on the spacecraft surfaces should be taken into consideration. For analyzing the plume plasma in this regard, retarding potential analyzers (RPA) are used in electric propulsion as one of the most fundamental and widely used diagnostics tools. RPA determines the ion energy distribution of plume plasma which is in the downstream of a thruster. This paper reports on a successful design process of an RPA to be used with BURFIT-80 ion thruster. An in-house developed hybrid Particle-In-Cell Direct Simulation Monte Carlo (PIC-DSMC) code, which is previously applied for ion thruster grid region is implemented to simulate the flow in the RPA. Results are used to validate the effective operation of the RPA. Potential distributions in the RPA are investigated and the calculated currents collected by the collector is compared with an existing experimental study.
{"title":"Design of the retarding potential analyzer to be used with BURFIT-80 Ion thruster and validation using PIC-DSMC code","authors":"Mert Satir, Firat Sik, Emre Turkoz, M. Çelik","doi":"10.1109/RAST.2015.7208410","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208410","url":null,"abstract":"For better integration of plasma thrusters into spacecraft and satellites, potential damaging effects of impinging high energy ions on the spacecraft surfaces should be taken into consideration. For analyzing the plume plasma in this regard, retarding potential analyzers (RPA) are used in electric propulsion as one of the most fundamental and widely used diagnostics tools. RPA determines the ion energy distribution of plume plasma which is in the downstream of a thruster. This paper reports on a successful design process of an RPA to be used with BURFIT-80 ion thruster. An in-house developed hybrid Particle-In-Cell Direct Simulation Monte Carlo (PIC-DSMC) code, which is previously applied for ion thruster grid region is implemented to simulate the flow in the RPA. Results are used to validate the effective operation of the RPA. Potential distributions in the RPA are investigated and the calculated currents collected by the collector is compared with an existing experimental study.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"109 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131232265","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208327
Sefer Ataş, Mehmet Emre Ciflcibasi, Mustafa Kilinc, Osman Koç, Deniz Altm, B. Ozdemir, Alper Yesifyurt
Technological achievements and cutting-edge methods in the last few decades, lead to a new era for aircraft approach and landing systems in parallel. Terrestrial radio-navigation systems used for takeoff, en-route navigation and landing of civilian and military planes in the world, such as VHF omni-directional range, instrument landing systems (ILS), etc. will be modernized with new systems using satellite signals in mid and long term. For en-route navigation and non-precision approach operations stand alone GNSS usage is widely preferred. But for the “precision or precision-like approach and landing” where stand alone GNSS usage is not adequate to provide the performance requirements, GNSS based approach and landing systems namely the ground based augmentation system (GBAS) and satellite based augmentation system (SBAS) stand as the promising technologies. In this paper, a general overview of the SBAS and GBAS systems are given in terms of architecture, operational advantages and the other major application areas with a focus of GNSS usage and the need for the augmentation systems in aviation. In this paper, World roadmap for GNSS based augmentation systems is evaluated among with a short list of “To Do”s for Turkey with a vision for Turkey's roadmap.
{"title":"GNSS based augmentation systems aviation perspective and vision for Turkey","authors":"Sefer Ataş, Mehmet Emre Ciflcibasi, Mustafa Kilinc, Osman Koç, Deniz Altm, B. Ozdemir, Alper Yesifyurt","doi":"10.1109/RAST.2015.7208327","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208327","url":null,"abstract":"Technological achievements and cutting-edge methods in the last few decades, lead to a new era for aircraft approach and landing systems in parallel. Terrestrial radio-navigation systems used for takeoff, en-route navigation and landing of civilian and military planes in the world, such as VHF omni-directional range, instrument landing systems (ILS), etc. will be modernized with new systems using satellite signals in mid and long term. For en-route navigation and non-precision approach operations stand alone GNSS usage is widely preferred. But for the “precision or precision-like approach and landing” where stand alone GNSS usage is not adequate to provide the performance requirements, GNSS based approach and landing systems namely the ground based augmentation system (GBAS) and satellite based augmentation system (SBAS) stand as the promising technologies. In this paper, a general overview of the SBAS and GBAS systems are given in terms of architecture, operational advantages and the other major application areas with a focus of GNSS usage and the need for the augmentation systems in aviation. In this paper, World roadmap for GNSS based augmentation systems is evaluated among with a short list of “To Do”s for Turkey with a vision for Turkey's roadmap.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131362490","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208324
Yusuf Acar, Casatay Yavuzyilmaz, M. Kemal Ozgoren
In this paper, the dynamic behavior of a satellite with an unactuated movable solar panel is examined as governed by two different controllers. This two-body system is dynamically underactuated because it has two outputs of concern, which are the angles of the satellite and the panel, but it has only one actuator, which is the reaction wheel attached to the main body of the satellite. Nevertheless, this system is still stabilizable owing to the spring supported joint of the panel. To describe and discuss the panel-satellite interactions plainly and clearly, a planar dynamic model is preferred. Thus, it has been possible to get an idea quickly about the effects of the stiffness of the panel joint spring and the type of the implemented controller on the attitude control of the satellite. However, a similar study can as well be extended without much difficulty to the general case of a multi-panel satellite with three-dimensional attitude control requirements. In this work, two different controllers are studied by assigning three different values to the stiffness of the spring between the panel and the satellite. With the support of the simulation results, this work has led to the conclusion that, if the spring is stiff enough, it is possible to implement the simple controller that requires feedback only from the satellite motion. On the other hand, if the spring is not very stiff, then it becomes advisable to implement the complicated controller that requires feedback not only from the satellite attitude but also from the relative panel motion, which further requires either extra sensors to use or an observer to implement. In this work, the complicated controller is implemented together with an observer.
{"title":"Control of a planar satellite with an unactuated movable solar panel","authors":"Yusuf Acar, Casatay Yavuzyilmaz, M. Kemal Ozgoren","doi":"10.1109/RAST.2015.7208324","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208324","url":null,"abstract":"In this paper, the dynamic behavior of a satellite with an unactuated movable solar panel is examined as governed by two different controllers. This two-body system is dynamically underactuated because it has two outputs of concern, which are the angles of the satellite and the panel, but it has only one actuator, which is the reaction wheel attached to the main body of the satellite. Nevertheless, this system is still stabilizable owing to the spring supported joint of the panel. To describe and discuss the panel-satellite interactions plainly and clearly, a planar dynamic model is preferred. Thus, it has been possible to get an idea quickly about the effects of the stiffness of the panel joint spring and the type of the implemented controller on the attitude control of the satellite. However, a similar study can as well be extended without much difficulty to the general case of a multi-panel satellite with three-dimensional attitude control requirements. In this work, two different controllers are studied by assigning three different values to the stiffness of the spring between the panel and the satellite. With the support of the simulation results, this work has led to the conclusion that, if the spring is stiff enough, it is possible to implement the simple controller that requires feedback only from the satellite motion. On the other hand, if the spring is not very stiff, then it becomes advisable to implement the complicated controller that requires feedback not only from the satellite attitude but also from the relative panel motion, which further requires either extra sensors to use or an observer to implement. In this work, the complicated controller is implemented together with an observer.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132705487","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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