scholarly journals Hardware in the Loop Testing of Microsatellite Components

2021 ◽  
Author(s):  
Sarah Hardacre
Keyword(s):  
Kalman Filter ◽  
Hardware In The Loop ◽  
Small Satellite ◽  
Test Bed ◽  
Robust Controller ◽  
Satellite Systems ◽  
Helmholtz Coils ◽  
Space Agency ◽  
Satellite Sensors ◽  
And Control

The desire to bring space travel to a wider range of missions and uses has driven the market to using smaller and thus more affordable satellite systems. The Canadian Space Agency is completing the design and construction of a small satellite named QuickSat, which will utilize a magnetometer as one of its attitude and orbit determination instruments. A test bed comprised of three pairs of Helmholtz coils was used for hardware in the loop testing of the magnetometer. Testing was initially completed to prove the capabilities of the test bed, and then was completed to demonstrate the capabilities of the flight qualified magnetometer. The three pairs of Helmholtz coils were driven by data calculated from a spherical harmonic model of the Earth's magnetic field The coils were controlled using a robust controller and the magnetometer was used to drive the B-dot control law in the QuickSat simulation. The Ryerson Attitude and Control Experiment (RACE), which is a small satellite sized platform, free to spin about one axis on a near frictionless air bearing, was utilized to develop and test a system to deal with redundancy of satellite sensors. The possibility of missing, noisy or erroneous output during flight requires that a filter be applied to a satellite's flight code to determine with accuracy the attitude and orbit of the spacecraft. It was thus decided that a Kalman Filter be applied to RACE. The Kalman filter was applied to the RACE simulation successfully and initial hardware testing was carried out.

Hardware in the Loop Testing of Microsatellite Components

2021 ◽  
Author(s):  
Sarah Hardacre
Keyword(s):  
Kalman Filter ◽  
Hardware In The Loop ◽  
Small Satellite ◽  
Test Bed ◽  
Robust Controller ◽  
Satellite Systems ◽  
Helmholtz Coils ◽  
Space Agency ◽  
Satellite Sensors ◽  
And Control

The desire to bring space travel to a wider range of missions and uses has driven the market to using smaller and thus more affordable satellite systems. The Canadian Space Agency is completing the design and construction of a small satellite named QuickSat, which will utilize a magnetometer as one of its attitude and orbit determination instruments. A test bed comprised of three pairs of Helmholtz coils was used for hardware in the loop testing of the magnetometer. Testing was initially completed to prove the capabilities of the test bed, and then was completed to demonstrate the capabilities of the flight qualified magnetometer. The three pairs of Helmholtz coils were driven by data calculated from a spherical harmonic model of the Earth's magnetic field The coils were controlled using a robust controller and the magnetometer was used to drive the B-dot control law in the QuickSat simulation. The Ryerson Attitude and Control Experiment (RACE), which is a small satellite sized platform, free to spin about one axis on a near frictionless air bearing, was utilized to develop and test a system to deal with redundancy of satellite sensors. The possibility of missing, noisy or erroneous output during flight requires that a filter be applied to a satellite's flight code to determine with accuracy the attitude and orbit of the spacecraft. It was thus decided that a Kalman Filter be applied to RACE. The Kalman filter was applied to the RACE simulation successfully and initial hardware testing was carried out.

Modeling, Hardware-in-the-Loop Simulations and Control Design for Small-Scale Vertical Axis Wind Turbines

2016 ◽  
Author(s):  
A. O. Onol ◽  
U. Sancar ◽  
A. Onat ◽  
S. Yesilyurt
Keyword(s):  
Control Design ◽  
Vertical Axis ◽  
Power Coefficient ◽  
Hardware In The Loop ◽  
Cfd Model ◽  
Test Bed ◽  
Cfd Simulations ◽  
Vertical Axis Wind Turbines ◽  
Overall Performance ◽  
And Control

In this study, we present a methodology for the assessment of overall performance for vertical axis wind turbines (VAWT) with straight blades. Salient features of our approach include a validated computational fluid dynamics (CFD) model and a hardware-in-the loop (HIL) test-bed. The two-dimensional, time-dependent CFD model uses the k-ε turbulence model and is coupled with the dynamics of the rotor involving friction and generator torques. The power coefficient curve for the rotor is obtained from the CFD simulations by varying the generator torque over time, and then used in the HIL test-bed that consists of an electrical motor, a gearbox, a permanent magnet synchronous generator, and an electronic load. In this setup, the VAWT rotor is mimicked by the electrical motor based on a power coefficient curve obtained from CFD simulations. Effects of the electrical conversion and control design on the overall performance of the VAWT are studied in the HIL setup. Additionally, a simple non-linear control (SNC) algorithm that mimics a model predictive controller and two different adaptations of the maximum power point tracking (MPPT) algorithm with fixed and variable step-sizes are designed and implemented in HIL simulations. According to results, the generator has a profound effect on the overall power output and the efficiency of the turbine; and the SNC and MPPT algorithms perform satisfactorily under step wind conditions.

Design and Implementation of Small Satellite Flexible Test Bed

2010 ◽  
Vol 40-41 ◽  
pp. 748-753
Author(s):  
Zhi Lin Zhu
Keyword(s):  
Software Architectures ◽  
Small Satellite ◽  
Test Bed ◽  
Telemetry Data ◽  
Dynamic Configuration ◽  
Small Satellites ◽  
Satellite Systems ◽  
And Performance ◽  
Design Ideas ◽  
Ground Part

This paper analyzes the character and performance of the synthesized test bed on ground of small satellites. By studying several small satellite systems, the hardware and software architectures of flexible test bed are presented. The design ideas of the on-board part and the ground part of small satellite are given. The dynamic configuration for communication request/reply relation, the definition and resolution of the telemetry data signals are mainly discussed. The design and corresponding implementation are proven very effectively on the development of three small satellite systems.

scholarly journals Scalable co-optimization of morphology and control in embodied machines

2018 ◽  
Vol 15 (143) ◽  
pp. 20170937 ◽  
Author(s):  
Nick Cheney ◽  
Josh Bongard ◽  
Vytas SunSpiral ◽  
Hod Lipson
Keyword(s):  
Embodied Cognition ◽  
Initial Conditions ◽  
Control Policy ◽  
Sensorimotor Control ◽  
Body Plan ◽  
The Body ◽  
Test Bed ◽  
Local Optima ◽  
Close Coupling ◽  
And Control

Evolution sculpts both the body plans and nervous systems of agents together over time. By contrast, in artificial intelligence and robotics, a robot's body plan is usually designed by hand, and control policies are then optimized for that fixed design. The task of simultaneously co-optimizing the morphology and controller of an embodied robot has remained a challenge. In psychology, the theory of embodied cognition posits that behaviour arises from a close coupling between body plan and sensorimotor control, which suggests why co-optimizing these two subsystems is so difficult: most evolutionary changes to morphology tend to adversely impact sensorimotor control, leading to an overall decrease in behavioural performance. Here, we further examine this hypothesis and demonstrate a technique for ‘morphological innovation protection’, which temporarily reduces selection pressure on recently morphologically changed individuals, thus enabling evolution some time to ‘readapt’ to the new morphology with subsequent control policy mutations. We show the potential for this method to avoid local optima and converge to similar highly fit morphologies across widely varying initial conditions, while sustaining fitness improvements further into optimization. While this technique is admittedly only the first of many steps that must be taken to achieve scalable optimization of embodied machines, we hope that theoretical insight into the cause of evolutionary stagnation in current methods will help to enable the automation of robot design and behavioural training—while simultaneously providing a test bed to investigate the theory of embodied cognition.

Development of Hardware In-the-Loop Simulation System for Testing Operation and Control Functions of Microgrid

2010 ◽  
Vol 25 (12) ◽  
pp. 2919-2929 ◽  
Author(s):  
Jin-Hong Jeon ◽  
Jong-Yul Kim ◽  
Hak-Man Kim ◽  
Seul-Ki Kim ◽  
Changhee Cho ◽  
...  
Keyword(s):  
Simulation System ◽  
Hardware In The Loop ◽  
Control Functions ◽  
And Control

Development of Appropriate Power Distribution Design for Can-Sized satellite (canSAT)

2021 ◽  
Vol 02 (02) ◽  
Author(s):  
Devina Cristine Marubin ◽  
◽  
Sim Sy Yi ◽  
Keyword(s):  
Power System ◽  
Data Acquisition ◽  
Power Supply ◽  
Communication System ◽  
Power Distribution ◽  
Low Cost ◽  
Small Satellite ◽  
Power Budget ◽  
Space Agency ◽  
Rules Set

Can-Sized satellite (canSAT) is a small satellite that is used for educational purpose. CanSAT offer student to build their satellites with their creativity which make the learning process more effective. In Malaysia, SiswaSAT is held by the Malaysia Space Agency for students in different categories to participate and build their satellites according to rules set and it should be a low-cost project. CanSAT can be divided into few parts which are communication system, onboard data acquisition, ground control station and power system. The power system is one of the important and heaviest subsystems, it needed to supply power, but weight and size are one of the main concerned as the canSAT should not exceed the required weight and selecting power supply that is matched with the overall power budget that has small size and lightweight is challenging. Therefore, the power supply selection should consider this detail. The power distribution design should be able to supply an appropriate amount of current and voltage to the components according to their specification. This study aims to develop and test the proposed prototype which is named ScoreSAT able to provide data and have enough power supply for the whole operation. Therefore, an initiative to develop the appropriate power distribution design for canSAT is taken to overcome the problem of the power system. Moreover, each subsystem needs to be tested by obtaining the results from the onboard data acquisition and transmit the data using the communication system before integrating into the power system. ScoreSAT prototype needs to carry the system that is mounted inside, thus the space inside the prototype needs to be fully utilized for the whole system to fit in. ScoreSAT completes the mission by obtaining data acquisition during the operation.

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