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Journal articles on the topic 'Nanosatellites – Control systems'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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1

Wang, Yu, Oleg V. Denisov, and Liliana V. Denisova. "Simulation of the thermal control system of nanosatellite using the loop heat pipes under the orbital flight conditions." RUDN Journal of Engineering Researches 22, no. 1 (August 27, 2021): 23–35. http://dx.doi.org/10.22363/2312-8143-2021-22-1-23-35.

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One of the key problems in the development of nanosatellites is to provide a given temperature range for the operation of the on-board computer. The constantly increasing information load leads to the need to use more advanced processors with high thermal design power (TDP). The indicated thermal regime of processors can be achieved using remote heat removal systems - miniature loop heat pipes. Using a model of nanosatellite as an example, a thermal control system with miniature loop heat pipes is designed. The simulation was carried out in the Siemens NX program in the elliptical and geostationary orbits of the Earth. The cooling schemes of the processor with a thermal power of 15 W using one and two loop heat pipes are considered. Calculations showed that the use of loop heat pipes can reduce the processor temperature to acceptable values. The anisotropy of the thermal conductivity coefficient in the reinforcement plane of the composite material of the nanosatellite case can have a significant effect on the temperature of the processor. This opens up prospects for the use of anisotropic composite materials to ensure the thermal regime of the nanosatellite.

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2

Modenini, Dario, Anton Bahu, Giacomo Curzi, and Andrea Togni. "A Dynamic Testbed for Nanosatellites Attitude Verification." Aerospace 7, no. 3 (March 18, 2020): 31. http://dx.doi.org/10.3390/aerospace7030031.

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To enable a reliable verification of attitude determination and control systems for nanosatellites, the environment of low Earth orbits with almost disturbance-free rotational dynamics must be simulated. This work describes the design solutions adopted for developing a dynamic nanosatellite attitude simulator testbed at the University of Bologna. The facility integrates several subsystems, including: (i) an air-bearing three degree of freedom platform, with automatic balancing system, (ii) a Helmholtz cage for geomagnetic field simulation, (iii) a Sun simulator, and (iv) a metrology vision system for ground-truth attitude generation. Apart from the commercial off-the-shelf Helmholtz cage, the other subsystems required substantial development efforts. The main purpose of this manuscript is to offer some cost-effective solutions for their in-house development, and to show through experimental verification that adequate performances can be achieved. The proposed approach may thus be preferred to the procurement of turn-key solutions, when required by budget constraints. The main outcome of the commissioning phase of the facility are: a residual disturbance torque affecting the air bearing platform of less than 5 × 10−5 Nm, an attitude determination rms accuracy of the vision system of 10 arcmin, and divergence of the Sun simulator light beam of less than 0.5° in a 35 cm diameter area.

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3

Phylonin, Oleg, Igor Belokonov, and Peter Nikolaev. "Traffic Control Systems of Nanosatellites in the Zone of the International Space Station." Procedia Engineering 185 (2017): 380–87. http://dx.doi.org/10.1016/j.proeng.2017.03.319.

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4

Veres, S. M., S. B. Gabriel, D. Q. Mayne, and E. Rogers. "Analysis of Formation Flying Control of a Pair of Nanosatellites." Journal of Guidance, Control, and Dynamics 25, no. 5 (September 2002): 971–74. http://dx.doi.org/10.2514/2.4971.

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5

Ferrer, Tomás, Sandra Céspedes, and Alex Becerra. "Review and Evaluation of MAC Protocols for Satellite IoT Systems Using Nanosatellites." Sensors 19, no. 8 (April 25, 2019): 1947. http://dx.doi.org/10.3390/s19081947.

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Extending the internet of things (IoT) networks to remote areas under extreme conditions or for serving sometimes unpredictable mobile applications has increased the need for satellite technology to provide effective connectivity. However, existent medium access control (MAC) protocols deployed in commercial satellite networks were not designed to offer scalable solutions for the increasing number of devices predicted for IoT in the near future, nor do they consider other specific IoT characteristics. In particular, CubeSats—a low-cost solution for space technology—have the potential to become a wireless access network for the IoT, if additional requirements, including simplicity and low demands in processing, storage, and energy consumption are incorporated into MAC protocol design for satellite IoT systems. Here we review MAC protocols employed or proposed for satellite systems and evaluate their performance considering the IoT scenario along with the trend of using CubeSats for IoT connectivity. Criteria include channel load, throughput, energy efficiency, and complexity. We have found that Aloha-based protocols and interference cancellation-based protocols stand out on some of the performance metrics. However, the tradeoffs among communications performance, energy consumption, and complexity require improvements in future designs, for which we identify specific challenges and open research areas for MAC protocols deployed with next low-cost nanosatellite IoT systems.

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Pirat, Camille, Finn Ankersen, Roger Walker, and Volker Gass. "$\mathcal{H}_{\infty}$ and $\mu$ -Synthesis for Nanosatellites Rendezvous and Docking." IEEE Transactions on Control Systems Technology 28, no. 3 (May 2020): 1050–57. http://dx.doi.org/10.1109/tcst.2019.2892923.

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7

Söken, Halil Ersin. "An Attitude Filtering and Magnetometer Calibration Approach for Nanosatellites." International Journal of Aeronautical and Space Sciences 19, no. 1 (March 2018): 164–71. http://dx.doi.org/10.1007/s42405-018-0020-8.

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8

Belokonov, I. V., I. A. Timbai, and P. N. Nikolaev. "Analysis and Synthesis of Motion of Aerodynamically Stabilized Nanosatellites of the CubeSat Design." Gyroscopy and Navigation 9, no. 4 (October 2018): 287–300. http://dx.doi.org/10.1134/s2075108718040028.

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9

Yoon, Hyosang, Kathleen M. Riesing, and Kerri Cahoy. "Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes." Journal of Guidance, Control, and Dynamics 40, no. 9 (September 2017): 2272–88. http://dx.doi.org/10.2514/1.g002649.

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10

Groesbeck, Daniel S., Kenneth A. Hart, and Brian C. Gunter. "Simulated Formation Flight of Nanosatellites Using Differential Drag with High-Fidelity Rarefied Aerodynamics." Journal of Guidance, Control, and Dynamics 42, no. 5 (May 2019): 1175–84. http://dx.doi.org/10.2514/1.g003871.

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11

Latachi, Ibtissam, Tajjeeddine Rachidi, Mohammed Karim, and Ahmed Hanafi. "Reusable and Reliable Flight-Control Software for a Fail-Safe and Cost-Efficient Cubesat Mission: Design and Implementation." Aerospace 7, no. 10 (October 10, 2020): 146. http://dx.doi.org/10.3390/aerospace7100146.

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While there is no rigorous framework to develop nanosatellites flight software, this manuscript aimed to explore and establish processes to design a reliable and reusable flight software architecture for cost-efficient student Cubesat missions such as Masat-1. Masat-1 is a 1Unit CubeSat, developed using a systems engineering approach, off-the-shelf components and open-source software tools. It was our aim to use it as a test-bed platform and as an initial reference for Cubesat flight software development in Morocco. The command and data handling system chosen for Masat-1 is a system-on-module-embedded computer running freeRTOS. A real-time operating system was used in order to simplify the real-time onboard management. To ensure software design reliability, modularity, reusability and extensibility, our solution follows a layered service oriented architectural pattern, and it is based on a finite state machine in the application layer to execute the mission functionalities in a deterministic manner. Moreover, a client-server model was elected to ensure the inter-process communication and resources access while using uniform APIs to enhance cross-platform data exchange. A hierarchical fault tolerance architecture was also implemented after a systematic assessment of the Masat-1 mission risks using reliability block diagrams (RBDs) and functional failure mode, effect and criticality analysis (FMECA).

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12

Verma, Vijay Kumar, Rajeev Kumar Ranjan, Pallav Prince, Bhargav Appasani, Nicu Bizon, and Phatiphat Thounthong. "A New Active Control Driver Circuit for Satellite’s Torquer System Using Second Generation Current Conveyor." Electronics 10, no. 8 (April 11, 2021): 911. http://dx.doi.org/10.3390/electronics10080911.

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In this article a new active control driver circuit is designed using the second-generation current conveyor for the satellite’s torquer system. The torquer plays an important role in the attitude control of the satellite. Based on the magneto-meter data, the satellite’s microprocessor calculates the required current for the torque and sends a reference command. A close loop control system is designed, which generates the desired output current. The parameters of the controller are optimized using a variant of the well-known evolutionary algorithm, the genetic algorithm (GA). This variant is known as the segmented GA. The controller is experimentally implemented using the commercially available integrated circuit, the AD844. The error between the experimental and simulation results has RMS values in range of 0.01–0.16 A for the output current and 0.41–0.6 V for the output voltage. It has mean value of 0.01 A for the output current and has mean values in the range of 0.33–0.48 V for the output voltage. It has standard deviation of 0.01 A for the output current and standard deviations in the range of 0.24–0.35 V for the output voltage. Thus, there is a close match between the simulation and experimental results, validating the design approach. These designs have many practical applications, particularly for nanosatellites powered by photovoltaic panels.

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Castillo, Joel A., Jorge Flores-Troncoso, Rigoberto Jáuregui, Jorge Simón, and José L. Alvarez-Flores. "Signal Conditioning Stage in S-Band Communication Subsystem for CubeSat Applications." Electronics 10, no. 14 (July 7, 2021): 1627. http://dx.doi.org/10.3390/electronics10141627.

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This work presents the design, performance evaluation, manufacture, and characterization of an RF front-end signal conditioning chain on a substrate that achieves the best performance at S-band frequencies and complies with the dimensions of the international standard for CubeSat-type nanosatellites. In this development, the signal conditioning chains were carried out on the high-frequency substrates RO4350B, CuClad 250, and RT/duroid 5880, considering scattering parameters in a small-signal regime. Concerning the power output, after the filtering and amplifying stages, the conditioning chain delivered 2 watts at 2.25 GHz. Moreover, up to 40 dB gain was achieved, and a good impedance matching at −20 dB for both input and output ports was observed. The numerical simulations and experimental results showed that an RO4350B substrate allows the smallest design dimensions, and these comply with the dimensions of the CubeSat standard. The manufactured RF front-end signal conditioning chain on RO4350B requires an area of 95 mm2, and it is ready to be used in a proof-of-concept space mission in a CubeSat.

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Mudereri, B. T., T. Dube, E. M. Adel-Rahman, S. Niassy, E. Kimathi, Z. Khan, and T. Landmann. "A COMPARATIVE ANALYSIS OF PLANETSCOPE AND SENTINEL SENTINEL-2 SPACE-BORNE SENSORS IN MAPPING STRIGA WEED USING GUIDED REGULARISED RANDOM FOREST CLASSIFICATION ENSEMBLE." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-2/W13 (June 4, 2019): 701–8. http://dx.doi.org/10.5194/isprs-archives-xlii-2-w13-701-2019.

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<p><strong>Abstract.</strong> Weeds are one of the major restrictions to sustaining crop productivity. Weeds often outcompete crops for nutrients, soil moisture, solar radiation, space and provide platforms for breeding of pests and diseases. The ever-growing global food insecurity triggers the need for spatially explicit innovative geospatial technologies that can deliver timely detection of weeds within agro-ecological systems. This will help pinpoint maize fields to be prioritized for weed control. Satellite remote sensing offers incomparable opportunities for precision agriculture, ecological applications and vegetation characterisation, with vast socioeconomic benefits. This work compares and evaluates the strength of Sentinel-2 (S2) satellite with the constellation of Dove nanosatellites i.e. PlanetScope (PS) data in detecting and mapping Striga (<i>Striga hermonthica</i>) weed within intercropped maize fields in Rongo sub-county in western Kenya. We applied the S2 and PS derived spectral data and vegetation indices in mapping the Striga occurrence. Data analysis was implemented, using the Guided Regularised Random Forest (GRRF) classifier. Comparatively, Sentinel-2 demonstrated slightly lower Striga detection capacity than PlanetScope, with an overall accuracy of 88% and 92%, respectively. The results further showed that the VNIR (Blue, Green Red and NIR) and the Atmospheric resistance Vegetation Index (ARVI) were the most fundamental variables in detecting and mapping Striga presence in maize fields. Findings from this work demonstrate that Sentinel-2 data has the capability to provide spatial explicit near real-time field level Striga detection &ndash; a previously daunting task with broadband multispectral sensors.</p>

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15

Li, Junquan, Mark Post, Thomas Wright, and Regina Lee. "Design of Attitude Control Systems for CubeSat-Class Nanosatellite." Journal of Control Science and Engineering 2013 (2013): 1–15. http://dx.doi.org/10.1155/2013/657182.

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We present a satellite attitude control system design using low-cost hardware and software for a 1U CubeSat. The attitude control system architecture is a crucial subsystem for any satellite mission since precise pointing is often required to meet mission objectives. The accuracy and precision requirements are even more challenging for small satellites where limited volume, mass, and power are available for the attitude control system hardware. In this proposed embedded attitude control system design for a 1U CubeSat, pointing is obtained through a two-stage approach involving coarse and fine control modes. Fine control is achieved through the use of three reaction wheels or three magnetorquers and one reaction wheel along the pitch axis. Significant design work has been conducted to realize the proposed architecture. In this paper, we present an overview of the embedded attitude control system design; the verification results from numerical simulation studies to demonstrate the performance of a CubeSat-class nanosatellite; and a series of air-bearing verification tests on nanosatellite attitude control system hardware that compares the performance of the proposed nonlinear controller with a proportional-integral-derivative controller.

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16

Bilal, Mohd, Ria Vijayan, and Klaus Schilling. "SDRE Control with Nonlinear J2 Perturbations for Nanosatellite Formation Flying." IFAC-PapersOnLine 52, no. 12 (2019): 448–53. http://dx.doi.org/10.1016/j.ifacol.2019.11.284.

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17

Hajiyev, Chingiz, and Demet Cilden-Guler. "Gyroless Nanosatellite Attitude Estimation in Loss of Sun Sensor Measurements." IFAC-PapersOnLine 51, no. 30 (2018): 89–94. http://dx.doi.org/10.1016/j.ifacol.2018.11.254.

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18

Hajiyev, Chingiz, Halil Ersin Soken, and Demet Cilden Guler. "Q-Adaptation of SVD-aided UKF Algorithm for Nanosatellite Attitude Estimation." IFAC-PapersOnLine 50, no. 1 (July 2017): 8273–78. http://dx.doi.org/10.1016/j.ifacol.2017.08.1399.

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19

Li, Junquan, Mark Post, and Regina Lee. "Real-Time Nonlinear Attitude Control System for Nanosatellite Applications." Journal of Guidance, Control, and Dynamics 36, no. 6 (November 2013): 1661–71. http://dx.doi.org/10.2514/1.59023.

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20

Zhong, R., and Z. H. Zhu. "Optimal Control of Nanosatellite Fast Deorbit Using Electrodynamic Tether." Journal of Guidance, Control, and Dynamics 37, no. 4 (July 2014): 1182–94. http://dx.doi.org/10.2514/1.62154.

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21

Cilden-Guler, Demet, and Chingiz Hajiyev. "UD Factorization Based Non-Traditional Attitude Estimation of Nanosatellite with Rate Gyros FDI." IFAC-PapersOnLine 51, no. 30 (2018): 95–100. http://dx.doi.org/10.1016/j.ifacol.2018.11.255.

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22

Aati, Saif, and Jean-Philippe Avouac. "Optimization of Optical Image Geometric Modeling, Application to Topography Extraction and Topographic Change Measurements Using PlanetScope and SkySat Imagery." Remote Sensing 12, no. 20 (October 18, 2020): 3418. http://dx.doi.org/10.3390/rs12203418.

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The volume of data generated by earth observation satellites has increased tremendously over the last few decades and will increase further in the coming decade thanks in particular to the launch of nanosatellites constellations. These data should open new avenues for Earth surface monitoring due to highly improved spectral, spatial and temporal resolution. Many applications depend, however, on the accuracy of the image geometric model. The geometry of optical images, whether acquired from pushbroom or frame systems, is now commonly represented using a Rational Function Model (RFM). While the formalism has become standard, the procedures used to generate these models and their accuracies are diverse. As a result, the RFM models delivered with commercial data are commonly not accurate enough for 3-D extraction, subpixel registration or ground deformation measurements. In this study, we present a methodology for RFM optimization and demonstrate its potential for 3D reconstruction using tri-stereo and multi-date Cubesat images provided by SkySat and PlanetScope, respectively. We use SkySat data over the Morenci Mine, Arizona, which is the largest copper mine in the United States. The re-projection error after the RFM refinement is 0.42 pix without using ground control points (GCPs). Comparison of our Digital Elevation Model (DEM with ~3 m GSD) with a reference DEM obtained from an airborne LiDAR survey (with ~1 m GSD) over stable areas yields a standard deviation of the elevation differences of ~3.9 m. The comparison of the two DEMs allows detecting and measuring the topographic changes due to the mine activity (excavation and stockpiles). We assess the potential of PlanetScope data, using multi-date DOVE-C images from the Shisper glacier, located in the Karakoram (Pakistan), which is known for its recent surge. We extracted DEMs in 2017 and 2019 before and after the surge. The re-projection error after the RFM refinement is 0.38 pix without using GCPs. The accuracy of our DEMs (with ~9 m GSD) is evaluated through comparison with the SRTM DEM (GSD ~30 m) and with a DEM (GSD ~2 m) calculated from Geoeye-1 (GE-1) and World-View-2 (WV-2) stereo images. The standard deviation of the elevation differences in stable areas between the PlanetScope DEM and SRTM is ~12 m, and ~7 m with the GE-1&WV-2 DEM. The mass transfer due to the surge is clearly revealed from a comparison of the 2017 and 2019 DEMs. The study demonstrates that, with the proposed scheme for RFM optimization, times series of DEM extracted from SkySat and PlanetScope images can be used to measure topographic changes due to mining activities or ice flow, and could also be used to monitor geomorphic processes such as landslides, or coastal erosion for example.

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Cilden-Guler, Demet, Zerefsan Kaymaz, and Chingiz Hajiyev. "Are External Magnetic Disturbances Suppressed by Magnetometer Noise when Estimating a Nanosatellite’s Rotational Motion?" IFAC-PapersOnLine 53, no. 2 (2020): 14888–93. http://dx.doi.org/10.1016/j.ifacol.2020.12.1948.

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24

Yun-Ze Li, Kok-Meng Lee, and Jun Wang. "Analysis and Control of Equivalent Physical Simulator for Nanosatellite Space Radiator." IEEE/ASME Transactions on Mechatronics 15, no. 1 (February 2010): 79–87. http://dx.doi.org/10.1109/tmech.2009.2016957.

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25

Belokonov, I. V., I. A. Timbai, and E. V. Barinova. "Design Parameters Selection for CubeSat Nanosatellite with a Passive Stabilization System." Gyroscopy and Navigation 11, no. 2 (April 2020): 149–61. http://dx.doi.org/10.1134/s2075108720020029.

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26

Lee, Kwang-Hyun, SeongMin Lim, Dong-Hyun Cho, and Hae-Dong Kim. "Development of Fault Detection and Identification Algorithm Using Deep learning for Nanosatellite Attitude Control System." International Journal of Aeronautical and Space Sciences 21, no. 2 (February 6, 2020): 576–85. http://dx.doi.org/10.1007/s42405-019-00235-9.

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27

Psiaki, Mark L. "Nanosatellite Attitude Stabilization Using Passive Aerodynamics and Active Magnetic Torquing." Journal of Guidance, Control, and Dynamics 27, no. 3 (May 2004): 347–55. http://dx.doi.org/10.2514/1.1993.

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McInnes, Colin R. "Simple Analytic Model of the Long-Term Evolution of Nanosatellite Constellations." Journal of Guidance, Control, and Dynamics 23, no. 2 (March 2000): 332–38. http://dx.doi.org/10.2514/2.4527.

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Gantel, Laurent, Quentin Berthet, Emna Amri, Alexandre Karlov, and Andres Upegui. "Fault-Tolerant FPGA-Based Nanosatellite Balancing High-Performance and Safety for Cryptography Application." Electronics 10, no. 17 (September 3, 2021): 2148. http://dx.doi.org/10.3390/electronics10172148.

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With the growth of the nano-satellites market, the usage of commercial off-the-shelf FPGAs for payload applications is also increasing. Due to the fact that these commercial devices are not radiation-tolerant, it is necessary to enhance them with fault mitigation mechanisms against Single Event Upsets (SEU). Several mechanisms such as memory scrubbing, triple modular redundancy (TMR) and Dynamic and Partial Reconfiguration (DPR), can help to detect, isolate and recover from SEU faults. In this paper, we introduce a dynamically reconfigurable platform equipped with configuration memory scrubbing and TMR mechanisms. We study their impacts when combined with DPR, providing three different execution modes: low-power, safe and high-performance mode. The fault detection mechanism permits the system to measure the radiation level and to estimate the risk of future faults. This enables the possibility of dynamically selecting the appropriate execution mode in order to adopt the best trade-off between performance and reliability. The relevance of the platform is demonstrated in a nano-satellite cryptographic application running on a Zynq UltraScale+ MPSoC device. A fault injection campaign has been performed to evaluate the impact of faulty configuration bits and to assess the efficiency of the proposed mitigation and the overall system reliability.

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Romero, Alessandro Gerlinger, and Luiz Carlos Gadelha De Souza. "Stability Evaluation of the SDRE Technique based on Java in a CubeSat Attitude and Orbit Control Subsystem." WSEAS TRANSACTIONS ON SYSTEMS 20 (January 29, 2021): 1–8. http://dx.doi.org/10.37394/23202.2021.20.1.

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In 2013, the STRaND (University of Surrey and Surrey Satellite Technology Ltd) and the PhoneSat (NASA) programs attracted the attention of the aerospace community applying commercial off-the-shelf smartphones in CubeSats. Both programs deployed CubeSats using smartphones based on Google's Android, in which application development is mainly based on Java programming language. Some of these CubeSats had actuators, e.g., STRaND-1 had three reaction wheels mounted in an orthogonal configuration to provide three-axis control, whereas PhoneSat 2.0 beta had magnetorquers to de-tumble the spacecraft. Taking into account a CubeSat that runs Android operating system (based on a smartphone), it is natural to evaluate the attitude and orbit control subsystem (AOCS) based on Java. Elsewhere, we shown State-Dependent Riccati Equation (SDRE) is a feasible non-linear control technique that can be applied in such CubeSats using Java. Moreover, we shown, through simulation using a Monte Carlo perturbation model, SDRE provides better performance than the PID controller, a linear control technique. In this paper, we tackle the next fundamental problem: stability. We evaluate stability from two perspectives: (1) parametric uncertainty of the inertia tensor and (2) a Monte Carlo perturbation model based on a uniform attitude probability distribution. Through the combination of these two perspectives, we grasp the stability properties of SDRE in a broader sense. In order to handle the uncertainty appropriately, we combine SDRE with H∞. The Nanosatellite Constellation for Environmental Data Collection (CONASAT), a CubeSat from the Brazilian National Institute for Space Research (INPE), provided the nominal parameters for the simulations. The initial results of the simulations shown that the SDRE controller is stable to ± 20% uncertainty in the inertia tensor for attitudes uniformly distributed and angular velocity up to 0.15 radians/second.

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Rawashdeh, Samir A. "Attitude Analysis of Small Satellites Using Model-Based Simulation." International Journal of Aerospace Engineering 2019 (April 15, 2019): 1–11. http://dx.doi.org/10.1155/2019/3020581.

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CubeSats, and small satellites in general, being small and relatively light, are sensitive to disturbance torques in the orbital environment. We developed a simulation tool that includes models of the major environmental torques and small satellite experiences in low Earth orbit, which allows users to study the attitude response for a given spacecraft and assist in the design of attitude control systems, such as selecting the magnet strength when using passive magnetic stabilization or designing the shape of the spacecraft when using aerodynamic attitude stabilization. The simulation tool named the Smart Nanosatellite Attitude Propagator (SNAP) has been public in precompiled form and widely used since 2010; this paper accompanies the release of SNAP’s source code with the inclusion of new models for aerodynamic torque and other new features. Details on internal models are described, including the models for orbit propagation, Earth’s magnetic field, gravity gradient torque, spacecraft shape modelling and aerodynamic torque, permanent magnetic dipole torque, and magnetic hysteresis. A discussion is presented on the significance of aerodynamic torque and magnetic hysteresis on a magnetically stabilized 3-unit CubeSat in the orbit of the International Space Station, from which many small satellites are deployed.

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32

Hu, Yuandong, Zhengliang Lu, Wenhe Liao, and Xiang Zhang. "Differential Aerodynamic Force-Based Formation Control of Nanosatellites Using Yaw Angle Deviation." Journal of Guidance, Control, and Dynamics, September 16, 2021, 1–15. http://dx.doi.org/10.2514/1.g006141.

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33

Douglas, Ewan S., Kevin Tracy, and Zachary Manchester. "Practical Limits on Nanosatellite Telescope Pointing: The Impact of Disturbances and Photon Noise." Frontiers in Astronomy and Space Sciences 8 (August 13, 2021). http://dx.doi.org/10.3389/fspas.2021.676252.

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Accurate and stable spacecraft pointing is a requirement of many astronomical observations. Pointing particularly challenges nanosatellites because of an unfavorable surface area–to-mass ratio and a proportionally large volume required for even the smallest attitude control systems. This work explores the limitations on astrophysical attitude knowledge and control in a regime unrestricted by actuator precision or actuator-induced disturbances such as jitter. The external disturbances on an archetypal 6U CubeSat are modeled, and the limiting sensing knowledge is calculated from the available stellar flux and grasp of a telescope within the available volume. These inputs are integrated using a model-predictive control scheme. For a simple test case at 1 Hz, with an 85-mm telescope and a single 11th magnitude star, the achievable body pointing is predicted to be 0.39 arcseconds. For a more general limit, integrating available star light, the achievable attitude sensing is approximately 1 milliarcsecond, which leads to a predicted body pointing accuracy of 20 milliarcseconds after application of the control model. These results show significant room for attitude sensing and control systems to improve before astrophysical and environmental limits are reached.

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Ballard, Christopher G., Kurt S. Anderson, and Leik Myrabo. "Flight Dynamics and Simulation of Laser Propelled Lightcraft." Journal of Computational and Nonlinear Dynamics 4, no. 4 (August 24, 2009). http://dx.doi.org/10.1115/1.3187214.

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A seven degree-of-freedom (7DOF) dynamic model was developed to provide insight into the flight behavior of Type 200 and other related lightcraft, and to serve as a research tool for developing future engine-vehicle configurations for laser launching of nanosatellites (1–10+kg). Accurate engine, beam, and aerodynamics models are included to improve the predictive capability of the 7DOF code. The aerodynamic forces of lift, drag, and aerodynamic pitching moment were derived from FLUENT® computational fluid dynamics predictions, and calibrated against limited existing wind tunnel data. To facilitate 7DOF model validation, simulation results are compared with video analysis of actual flights under comparable conditions. Despite current limitations of the 7DOF model, the results compared well with experimental flight trajectory data.

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