Pub Date : 2019-10-01DOI: 10.1109/ICARES.2019.8914337
Gafur H.Z. Bahari, A. Syafrudin
The process of testing and verification of satellite components is important to ensure that each sub-system can complete the task that has been designed. Thermal monitoring is important for the camera, therefore thermal measurement has to be accurate because changes in temperature can cause data error. Besides thermal, power requirements are one of the most important parameters in satellite development. This paper aims to conduct thermal and power testing from a data logger. The data logger which is an instrument to read data from time to time. From the test data, it can be seen that the ADC, PCB and Charge Coupled Device temperature at each Image Interface Modules will increase drastically when the camera is on the operation mode. The temperature at each Image Interface Modules increases for about 11.41° C, 13.61° C, 8.21° C and 7.81° C for ADC, PCB, Charge-Coupled Device channel 0 and Charge Coupled Device channel 1 respectively. Barrel temperature does not change significantly when the camera is turned on. Barrel temperature at each Image Interface Modules changes in the range 23C − 24C according to ambient temperature. For power consumption based on line period testing with line period mode using an altitude range of 485 km − 700 km. The initial power needed at an altitude of 485 km is 18.77 W. The power required at the simulation of 700 km altitude is 16.17 W.
卫星部件的测试和验证过程对于确保每个子系统能够完成已设计的任务非常重要。热监测对相机很重要，因此热测量必须准确，因为温度的变化会导致数据误差。除了热能之外，功率需求也是卫星研制中最重要的参数之一。本文的目的是通过数据记录仪进行热和功率测试。数据记录器是一种不时读取数据的仪器。从测试数据可以看出，当相机处于工作模式时，每个图像接口模块上的ADC、PCB和电荷耦合器件温度都会急剧升高。对于ADC、PCB、电荷耦合器件通道0和电荷耦合器件通道1，每个图像接口模块的温度分别升高约11.41°C、13.61°C、8.21°C和7.81°C。相机开机时，机筒温度变化不大。每个图像接口模块的桶温根据环境温度在23℃~ 24℃范围内变化。用于基于线周期测试的功耗，采用线周期模式，海拔范围为485 km ~ 700 km。在海拔485公里处所需的初始功率为18.77瓦。模拟海拔700公里时所需功率为16.17 W。
{"title":"Development Data Logger Software For Thermal and Power Identification Of LAPAN-A4 Satellite Camera","authors":"Gafur H.Z. Bahari, A. Syafrudin","doi":"10.1109/ICARES.2019.8914337","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914337","url":null,"abstract":"The process of testing and verification of satellite components is important to ensure that each sub-system can complete the task that has been designed. Thermal monitoring is important for the camera, therefore thermal measurement has to be accurate because changes in temperature can cause data error. Besides thermal, power requirements are one of the most important parameters in satellite development. This paper aims to conduct thermal and power testing from a data logger. The data logger which is an instrument to read data from time to time. From the test data, it can be seen that the ADC, PCB and Charge Coupled Device temperature at each Image Interface Modules will increase drastically when the camera is on the operation mode. The temperature at each Image Interface Modules increases for about 11.41° C, 13.61° C, 8.21° C and 7.81° C for ADC, PCB, Charge-Coupled Device channel 0 and Charge Coupled Device channel 1 respectively. Barrel temperature does not change significantly when the camera is turned on. Barrel temperature at each Image Interface Modules changes in the range 23C − 24C according to ambient temperature. For power consumption based on line period testing with line period mode using an altitude range of 485 km − 700 km. The initial power needed at an altitude of 485 km is 18.77 W. The power required at the simulation of 700 km altitude is 16.17 W.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130400093","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914352
R. P. Ramadhan, F. H. Manggala, H. Wijanto, H. Mayditia
In this paper, we combine two subsystems of CubeSat which are electrical power system and onboard data handling called power control and data handling (PCDH). A power control and data handling (PCDH) can manage data and power involved monitoring power, sending command, and supplying power in one microcontroller. Other CubeSat generally using two microcontrollers to handle it. By using one microcontroller, It can increase the effectiveness of CubeSat space. The main contribution of this paper is proposed to be the first design of PCDH for CubeSat. Design of PCDH covered GUI scroll, serial port connection, and PCB layer for the control unit. For microcontroller, we use a compact design of DUE Core R3. On the PCDH layer, we provide communication data such as I2C, UART, and GPIO so that another payload can be added if needed. The concern of this PCDH research is to handle CubeSat with reaction wheels payload. The results of this research proved that our PCDH can charge the battery, regulates power, controls the switch, and control the direction and speed of the reaction wheels.
{"title":"Power Control and Data Handling for Cubesat 1U","authors":"R. P. Ramadhan, F. H. Manggala, H. Wijanto, H. Mayditia","doi":"10.1109/ICARES.2019.8914352","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914352","url":null,"abstract":"In this paper, we combine two subsystems of CubeSat which are electrical power system and onboard data handling called power control and data handling (PCDH). A power control and data handling (PCDH) can manage data and power involved monitoring power, sending command, and supplying power in one microcontroller. Other CubeSat generally using two microcontrollers to handle it. By using one microcontroller, It can increase the effectiveness of CubeSat space. The main contribution of this paper is proposed to be the first design of PCDH for CubeSat. Design of PCDH covered GUI scroll, serial port connection, and PCB layer for the control unit. For microcontroller, we use a compact design of DUE Core R3. On the PCDH layer, we provide communication data such as I2C, UART, and GPIO so that another payload can be added if needed. The concern of this PCDH research is to handle CubeSat with reaction wheels payload. The results of this research proved that our PCDH can charge the battery, regulates power, controls the switch, and control the direction and speed of the reaction wheels.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124421174","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914347
Nova Maras Nurul Khamsah, S. Utama, Rise Hapshary Surayuda, P. R. Hakim
It is crucial for Indonesia as an agricultural country to have its own satellite image to be utilized in Indonesia's resources monitoring. LAPAN-A3 satellite data has been studied for earth observation and can be utilized for monitoring paddy fields, built-up areas, forests, rivers, fishponds, shrubs, sea, agricultural lands, and bare soils. But, as a sun-synchronous satellite, LAPAN-A3 has demerit of little revisit time for one specific area. Therefore, off-nadir imaging becomes one essential trait of the satellite to increase target monitoring from 17 times to 71 times in a year. This paper aims to organize the development process of off-nadir strategy in acquiring target image in Indonesia. With two kinds of off-nadir maneuver, inertial pointing maneuver and wheel speed maneuver, LAPAN-A3 satellite can conduct off-nadir imaging up to 34.5° roll angle maneuver. Furthermore, wheel speed maneuver with roll angle and roll rate approach presents the improvement in time efficiency of the maneuver, from 1 hour and 35 minutes executing time in inertial pointing to 25 minutes in wheel speed maneuver, making it become promising candidate for time-constraint off-nadir imaging.
{"title":"The Development of LAPAN-A3 Satellite Off-Nadir Imaging Mission","authors":"Nova Maras Nurul Khamsah, S. Utama, Rise Hapshary Surayuda, P. R. Hakim","doi":"10.1109/ICARES.2019.8914347","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914347","url":null,"abstract":"It is crucial for Indonesia as an agricultural country to have its own satellite image to be utilized in Indonesia's resources monitoring. LAPAN-A3 satellite data has been studied for earth observation and can be utilized for monitoring paddy fields, built-up areas, forests, rivers, fishponds, shrubs, sea, agricultural lands, and bare soils. But, as a sun-synchronous satellite, LAPAN-A3 has demerit of little revisit time for one specific area. Therefore, off-nadir imaging becomes one essential trait of the satellite to increase target monitoring from 17 times to 71 times in a year. This paper aims to organize the development process of off-nadir strategy in acquiring target image in Indonesia. With two kinds of off-nadir maneuver, inertial pointing maneuver and wheel speed maneuver, LAPAN-A3 satellite can conduct off-nadir imaging up to 34.5° roll angle maneuver. Furthermore, wheel speed maneuver with roll angle and roll rate approach presents the improvement in time efficiency of the maneuver, from 1 hour and 35 minutes executing time in inertial pointing to 25 minutes in wheel speed maneuver, making it become promising candidate for time-constraint off-nadir imaging.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128326964","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914344
Kamirul, P. R. Hakim, W. Hasbi
This paper describes a modified version of existing statistical-based stripe noise removal designed to recover noisy images without devastating the structure of the image. The proposed algorithm has been tested by using LAPAN-A2 microsatellite imagery. Based on the investigation of corrected images, it is confirmed that the proposed algorithm was capable of giving a satisfying result than that of the existing one. It is also found that the performance of the proposed algorithm is 10.21% better than that of the existing algorithm. This result indicates that the proposed algorithm can be used as data processing tool to address the stripe noise disturbance existed on particular imaging system.
{"title":"An Adaptive Stripe Noise Removal Algorithm for Optical Satellite Imagery","authors":"Kamirul, P. R. Hakim, W. Hasbi","doi":"10.1109/ICARES.2019.8914344","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914344","url":null,"abstract":"This paper describes a modified version of existing statistical-based stripe noise removal designed to recover noisy images without devastating the structure of the image. The proposed algorithm has been tested by using LAPAN-A2 microsatellite imagery. Based on the investigation of corrected images, it is confirmed that the proposed algorithm was capable of giving a satisfying result than that of the existing one. It is also found that the performance of the proposed algorithm is 10.21% better than that of the existing algorithm. This result indicates that the proposed algorithm can be used as data processing tool to address the stripe noise disturbance existed on particular imaging system.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114139785","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914354
R. Hartono, D. Ardianto, S. Salaswati, R. Yatim, A. Syafrudin
A filter is a device or instrument which is able to pass a specific signal and also remove other signals. There are several types of optical filters: bandpass filter, long-pass filter, and short-pass filter. The next microsatellite developed by Satellite Technology Center is LAPAN-A4 Satellite. This satellite brings Medium Resolution Multispectral Imager (MRI) using SLIM4 and also Experiment LAPAN Line Imager Space Application (ELLISA). Moreover, this satellite also brings thermal imager which is called microbolometer, and experiment Short Wave Infrared (SWIR) camera. Especially for spectral band Long Wave Infrared (LWIR) cameras in LAPAN-A4 satellite will be narrowed down to $10.4mu mathrm{m}- 12.5mu mathrm{m}$, therefore a band filter is needed for blocking and passing these wavelengths. The method used to design the optical bandpass filter LWIR microbolometer camera is by determining the required spectral response. The response spectral required refers to the LANDSAT 8 Thermal Infrared Sensors (TIRS) bands 10 and 11 with spectral response $10.60 - 12.51mu mathrm{m}$, Centre Wavelength (CWL) of band 10 and 11 are $10.9mu mathrm{m}$ and $12.0 mu mathrm{m}$, and Full-Width Half-Maximum (FWHM) of both band are 0.6 $mu mathrm{m}$ and $1mu mathrm{m})$), and also determine the substrate filter material to be used. The design results show that, the LWIR bandpass filter has a spectral response of 10.4- $12.5mu mathrm{m}$, CWL $11.45mu mathrm{m}$, and FWHM $2.1mu mathrm{m}, max$ peak transmission is 80.21%, and capable of blocking at wavelengths of $7-10.4 mu mathrm{m}$ and $13-16.5 mu mathrm{m}$, the material used in this design uses Germanium (Ge) because it has a wavelength of $2-16 mu mathrm{m}$ which can work on spectral IR transmission.
滤波器是一种装置或仪器，它可以通过特定的信号，也可以去除其他信号。有几种类型的光学滤波器:带通滤波器、长通滤波器和短通滤波器。卫星技术中心研制的下一颗微卫星是LAPAN-A4卫星。该卫星携带了使用SLIM4的中分辨率多光谱成像仪(MRI)和实验性LAPAN线成像仪空间应用(ELLISA)。此外，该卫星还带来了被称为微测热仪的热成像仪和实验短波红外摄像机。特别是对于LAPAN-A4卫星上的长波红外(LWIR)相机的光谱波段将被缩小到$10.4mu mathrm{m}- 12.5mu mathrm{m}$，因此需要一个波段滤波器来阻挡和通过这些波长。设计光学带通滤波器LWIR微热计相机的方法是通过确定所需的光谱响应。所需的响应光谱参考LANDSAT 8热红外传感器(TIRS)波段10和11，光谱响应为$10.60 - 12.51mu mathrm{m}$，波段10和11的中心波长(CWL)分别为$10.9mu mathrm{m}$和$12.0 mu mathrm{m}$，两个波段的全宽半最大值(FWHM)分别为0.6 $mu mathrm{m}$和$1mu mathrm{m})$，并确定要使用的基片滤光材料。设计结果表明，LWIR带通滤波器的光谱响应为10.4- $12.5mu mathrm{m}$, CWL $11.45mu mathrm{m}$, FWHM $2.1mu mathrm{m}, max$峰值透射率为80.21%, and capable of blocking at wavelengths of $7-10.4 mu mathrm{m}$ and $13-16.5 mu mathrm{m}$, the material used in this design uses Germanium (Ge) because it has a wavelength of $2-16 mu mathrm{m}$ which can work on spectral IR transmission.
{"title":"Design Requirement of LWIR Optical Filter for LAPAN-A4 Satellite","authors":"R. Hartono, D. Ardianto, S. Salaswati, R. Yatim, A. Syafrudin","doi":"10.1109/ICARES.2019.8914354","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914354","url":null,"abstract":"A filter is a device or instrument which is able to pass a specific signal and also remove other signals. There are several types of optical filters: bandpass filter, long-pass filter, and short-pass filter. The next microsatellite developed by Satellite Technology Center is LAPAN-A4 Satellite. This satellite brings Medium Resolution Multispectral Imager (MRI) using SLIM4 and also Experiment LAPAN Line Imager Space Application (ELLISA). Moreover, this satellite also brings thermal imager which is called microbolometer, and experiment Short Wave Infrared (SWIR) camera. Especially for spectral band Long Wave Infrared (LWIR) cameras in LAPAN-A4 satellite will be narrowed down to $10.4mu mathrm{m}- 12.5mu mathrm{m}$, therefore a band filter is needed for blocking and passing these wavelengths. The method used to design the optical bandpass filter LWIR microbolometer camera is by determining the required spectral response. The response spectral required refers to the LANDSAT 8 Thermal Infrared Sensors (TIRS) bands 10 and 11 with spectral response $10.60 - 12.51mu mathrm{m}$, Centre Wavelength (CWL) of band 10 and 11 are $10.9mu mathrm{m}$ and $12.0 mu mathrm{m}$, and Full-Width Half-Maximum (FWHM) of both band are 0.6 $mu mathrm{m}$ and $1mu mathrm{m})$), and also determine the substrate filter material to be used. The design results show that, the LWIR bandpass filter has a spectral response of 10.4- $12.5mu mathrm{m}$, CWL $11.45mu mathrm{m}$, and FWHM $2.1mu mathrm{m}, max$ peak transmission is 80.21%, and capable of blocking at wavelengths of $7-10.4 mu mathrm{m}$ and $13-16.5 mu mathrm{m}$, the material used in this design uses Germanium (Ge) because it has a wavelength of $2-16 mu mathrm{m}$ which can work on spectral IR transmission.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124786894","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914346
Kamirul, P. R. Hakim, R. Madina
During satellite data transmission, several schemes of unavoidable errors may be experienced by the ground receiver. In the case of LAPAN-A2 imagery, those errors account for the presence of byte-missing effect disordering the position of pixel location on received raw data. Processing raw data contaminated by the byte-shifting effect will produce a line-drop pattern covering the original image on a particular line. This work is aimed to develop line-drop correction algorithm applied on three different levels of LAPAN-A2 microsatellite imagery data. A quantitative analysis was also performed on corrected images to determine the most suitable correction method for LAPAN-A2 imagery. In the end, a comparison between the developed method and an existing method has been demonstrated. It is confirmed that the developed method is better than the existing method in terms of producing a better quality of corrected images and performing a faster computational task. The developed method can be used as a solution to avoid data re-transmission to recover clear image data.
{"title":"Line-Drop Error Correction for LAPAN-A2 Microsatellite Imagery","authors":"Kamirul, P. R. Hakim, R. Madina","doi":"10.1109/ICARES.2019.8914346","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914346","url":null,"abstract":"During satellite data transmission, several schemes of unavoidable errors may be experienced by the ground receiver. In the case of LAPAN-A2 imagery, those errors account for the presence of byte-missing effect disordering the position of pixel location on received raw data. Processing raw data contaminated by the byte-shifting effect will produce a line-drop pattern covering the original image on a particular line. This work is aimed to develop line-drop correction algorithm applied on three different levels of LAPAN-A2 microsatellite imagery data. A quantitative analysis was also performed on corrected images to determine the most suitable correction method for LAPAN-A2 imagery. In the end, a comparison between the developed method and an existing method has been demonstrated. It is confirmed that the developed method is better than the existing method in terms of producing a better quality of corrected images and performing a faster computational task. The developed method can be used as a solution to avoid data re-transmission to recover clear image data.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"141 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123301186","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914336
Nadia Rizki Ariyani, Larasmoyo Nugroho
One of the most puzzling phenomena in rocket's flight trajectory is the wobbling maneuver, due to its nature that the sources of wobbling problem could come from multiple factors and all need to be investigated one by one. One of the source problems is the coupling motion mechanism between rolling and pitching that is uncontrolled. This paper presented a tool to address this flight dynamics coupling phenomenon. The tool called Dynamic Model Holder System (MHS) that can reproduce the motion of wobbling while at the same time examining and scrutinizing the source of instability. After undergoing many iterations of conceptual designs, the effort produced a dynamic MHS design that could hasten an instability and another design that could dampen instability. The source of instability is found to be the negative static margin.
{"title":"Conceptual Design Methodology of A 3-DOF Dynamic Model Holder System for Open Subsonic Wind Tunnel","authors":"Nadia Rizki Ariyani, Larasmoyo Nugroho","doi":"10.1109/ICARES.2019.8914336","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914336","url":null,"abstract":"One of the most puzzling phenomena in rocket's flight trajectory is the wobbling maneuver, due to its nature that the sources of wobbling problem could come from multiple factors and all need to be investigated one by one. One of the source problems is the coupling motion mechanism between rolling and pitching that is uncontrolled. This paper presented a tool to address this flight dynamics coupling phenomenon. The tool called Dynamic Model Holder System (MHS) that can reproduce the motion of wobbling while at the same time examining and scrutinizing the source of instability. After undergoing many iterations of conceptual designs, the effort produced a dynamic MHS design that could hasten an instability and another design that could dampen instability. The source of instability is found to be the negative static margin.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"129 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123514295","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914343
A. Tsourdos, Ir. Adhi Dharma Permana, Dew Budiarti, Hyo-Sang Shin, Chang-hun Lee
Developing a flight control system for a 6 degree-of-freedom aircraft remains a considerable task that requires time and effort to gather all the necessary data. In this paper, a policy using reinforcement learning based on Deep Deterministic Policy Gradient (DDPG) is proposed and its application to UAS (Unmanned Aerial System) control is presented. Previous research has shown a slight difficulty in training the DDPG learning agent for a system with multiple agent. A learning strategy is introduced to implicitly guide the learning agent to utilize all three control surfaces and still produce a converging policy. The DDPG learning agent is trained through several training sets to generate the best policy suited to control the aircraft. The final policy as the result of the training procedure is then extracted and tested. This research shows that DDPG can be used to develop the policy for flight control.
{"title":"Developing Flight Control Policy Using Deep Deterministic Policy Gradient","authors":"A. Tsourdos, Ir. Adhi Dharma Permana, Dew Budiarti, Hyo-Sang Shin, Chang-hun Lee","doi":"10.1109/ICARES.2019.8914343","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914343","url":null,"abstract":"Developing a flight control system for a 6 degree-of-freedom aircraft remains a considerable task that requires time and effort to gather all the necessary data. In this paper, a policy using reinforcement learning based on Deep Deterministic Policy Gradient (DDPG) is proposed and its application to UAS (Unmanned Aerial System) control is presented. Previous research has shown a slight difficulty in training the DDPG learning agent for a system with multiple agent. A learning strategy is introduced to implicitly guide the learning agent to utilize all three control surfaces and still produce a converging policy. The DDPG learning agent is trained through several training sets to generate the best policy suited to control the aircraft. The final policy as the result of the training procedure is then extracted and tested. This research shows that DDPG can be used to develop the policy for flight control.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"408 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116518195","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914345
A. A. Bayanuddin, Zylshal, S. Utama
The maneuverability of a satellite to perform nadir and off-nadir offers an excellent opportunity for gathering valuable information in the time of disaster events. This paper aims to compare how LAPAN-A3 spectral quality changed with different acquisition modes. Three scenes of LAPAN-A3 with different acquisition modes ranging from nadir to extreme off-nadir mode were analyzed. Using Sentinel-2A Multispectral Instrument data as the reference, geometric co-registration was performed, and the Root Mean Square Error was kept at maximum (<2.5 pixels). Pseudo-invariant features were selected semi-automatically using threshold values based on the Normalized Difference Vegetation Index and Normalized Difference Water Index. The digital number produced then compared to Sentinel-2A data. Pearson correlation coefficient, as well as linear regression, was calculated for four corresponding bands. Generally, the results show a decreased correlation value between the corresponding datasets as the roll-angle increased. The correlation value went down from 0.623 (Off-Nadir) to 0.497 (Extreme off-nadir) on Near-infrared band.
{"title":"Nadir vs. Off-nadir: Initial Look at LAPAN-A3 Off-nadir Acquisition Mode on its Spectral Quality","authors":"A. A. Bayanuddin, Zylshal, S. Utama","doi":"10.1109/ICARES.2019.8914345","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914345","url":null,"abstract":"The maneuverability of a satellite to perform nadir and off-nadir offers an excellent opportunity for gathering valuable information in the time of disaster events. This paper aims to compare how LAPAN-A3 spectral quality changed with different acquisition modes. Three scenes of LAPAN-A3 with different acquisition modes ranging from nadir to extreme off-nadir mode were analyzed. Using Sentinel-2A Multispectral Instrument data as the reference, geometric co-registration was performed, and the Root Mean Square Error was kept at maximum (<2.5 pixels). Pseudo-invariant features were selected semi-automatically using threshold values based on the Normalized Difference Vegetation Index and Normalized Difference Water Index. The digital number produced then compared to Sentinel-2A data. Pearson correlation coefficient, as well as linear regression, was calculated for four corresponding bands. Generally, the results show a decreased correlation value between the corresponding datasets as the roll-angle increased. The correlation value went down from 0.623 (Off-Nadir) to 0.497 (Extreme off-nadir) on Near-infrared band.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"82 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116035173","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914335
Sonny Dwi Harsono, Rumadi, Rifki Ardinal
LAPAN-A2 Satellite, also known as LAPAN-ORARI, is the second satellite developed by the Indonesian National Institute of Aeronautics and Space (LAPAN), especially by Satellite Technology Center. This satellite was launched in 2015, where one of the missions is to support disaster mitigation through the Automatic Packet Reporting System (APRS). The APRS is a method of transmitting messages, status, and positions - using specially formatted AX.25 packets messages. The critical part of the APRS infrastructure is Digital Repeater (digipeater) and Internet Gateways (iGates). The digipeater is usually used to retransmit data packets for extending coverage. The APRS digipeater of LAPAN-A2 is on 145.825 MHz. The iGate is a type of gateway APRS station that functions to collect packages from the radio and feeds them into a worldwide data streams on the internet. This paper describes the design and implementation of SatGate /iGate YF1ZQA for APRS on the LAPAN-A2 Satellite.
{"title":"Design and Implementation of SatGate / iGate YF1ZQA for APRS on the LAPAN-A2 Satellite","authors":"Sonny Dwi Harsono, Rumadi, Rifki Ardinal","doi":"10.1109/ICARES.2019.8914335","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914335","url":null,"abstract":"LAPAN-A2 Satellite, also known as LAPAN-ORARI, is the second satellite developed by the Indonesian National Institute of Aeronautics and Space (LAPAN), especially by Satellite Technology Center. This satellite was launched in 2015, where one of the missions is to support disaster mitigation through the Automatic Packet Reporting System (APRS). The APRS is a method of transmitting messages, status, and positions - using specially formatted AX.25 packets messages. The critical part of the APRS infrastructure is Digital Repeater (digipeater) and Internet Gateways (iGates). The digipeater is usually used to retransmit data packets for extending coverage. The APRS digipeater of LAPAN-A2 is on 145.825 MHz. The iGate is a type of gateway APRS station that functions to collect packages from the radio and feeds them into a worldwide data streams on the internet. This paper describes the design and implementation of SatGate /iGate YF1ZQA for APRS on the LAPAN-A2 Satellite.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"49 12","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120858201","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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