Attitude Control of the CubeSail Solar Sailing Spacecraft Victoria Coverstone, Andy Pukniel University of Illinois at Urbana-Champaign Rod Burton, Dave.

Slides:



Advertisements
Similar presentations
Magnetic Force Acting on a Current-Carrying Conductor
Advertisements

UNIT 6 (end of mechanics) Universal Gravitation & SHM.
BL OOS GG workshop, Pisa / S.Piero a Grado 2/26/2010, Thales Alenia Space Template reference : S-EN INTERNAL THALES ALENIA SPACE COMMERCIAL.
Solar Sail Attitude Control using a Combination of a Feedforward and a Feedback Controller D. Romagnoli, T. Oehlschlägel.
Analysis of a Deorbiting Maneuver of a large Target Satellite using a Chaser Satellite with a Robot Arm Philipp Gahbler 1, R. Lampariello 1 and J. Sommer.
Benoit Pigneur and Kartik Ariyur School of Mechanical Engineering Purdue University June 2013 Inexpensive Sensing For Full State Estimation of Spacecraft.
GN/MAE155B1 Orbital Mechanics Overview 2 MAE 155B G. Nacouzi.
Dr. Andrew Ketsdever Lesson 3 MAE 5595
More Satellite Orbits Introduction to Space Systems and Spacecraft Design Space Systems Design.
ARO309 - Astronautics and Spacecraft Design Winter 2014 Try Lam CalPoly Pomona Aerospace Engineering.
LightSail.
Abstract Since dawn of time humans have aspired to fly like birds. However, human carrying ornithopter that can hover by flapping wings doesn’t exist despite.
Analysis of Rocket Propulsion
Maxwell’s Equations and Electromagnetic Waves
6. Space research and exploration of space increases our understanding of the Earth‘s own environment, the Solar System and the Universe. 4. Rapid advances.
ATMOSPHERIC REENTRY TRAJECTORY MODELING AND SIMULATION: APPLICATION TO REUSABLE LAUNCH VEHICLE MISSION (Progress Seminar Presentation - 2) K. Sivan (Roll.
U N C L A S S I F I E D Operated by the Los Alamos National Security, LLC for the DOE/NNSA IMPACT Project Drag coefficients of Low Earth Orbit satellites.
PREPARED BY: JANAK GAJJAR SD1909.  Introduction  Wind calculation  Pressure distribution on Antenna  Conclusion  References.
Attitude Determination and Control
Karla Vega University of California, Berkeley Attitude Determination and Control 6/9/2015.
Mechanics Exercise Class Ⅲ
February 24, Final Presentation AAE Final Presentation Backstepping Based Flight Control Asif Hossain.
Feasibility of Demonstrating PPT’s on FalconSAT-3 C1C Andrea Johnson United States Air Force Academy.
Chapter 10 More on angular momentum and torque In chapter 9 we described the rotational motion of a rigid body and, based on that, we defined the vector.
1 Short Summary of the Mechanics of Wind Turbine Korn Saran-Yasoontorn Department of Civil Engineering University of Texas at Austin 8/7/02.
Jarred Morales and Cody Beckemeyer Advisior: Dr. Junkun Ma ET 483.
Integrated Orbit and Attitude Control for a Nanosatellite with Power Constraints Bo Naasz Matthew Berry Hye-Young Kim Chris Hall 13th Annual AAS/AIAA Space.
1 Project Name Solar Sail Project Proposal February 7, 2007 Megan Williams (Team Lead) Eric Blake Jon Braam Raymond Haremza Michael Hiti Kory Jenkins Daniel.
1 Samara State Aerospace University (SSAU) Modern methods of analysis of the dynamics and motion control of space tether systems Practical lessons Yuryi.
Force on Floating bodies:
Attitude Determination and Control System
Attitude Determination and Control System (ADCS)
Give the expression for the velocity of an object rolling down an incline without slipping in terms of h (height), M(mass), g, I (Moment of inertia) and.
Precision Control Autonomous Systems for NEO Mission Design Karl Williams Matthew Zimmer.
10. Satellite Communication & Radar Sensors
Effect of Structure Flexibility on Attitude Dynamics of Modernizated Microsatellite.
Biomechanics Examines the internal and external forces acting on the human body and the effects produced by these forces Aids in technique analysis and.
Guidance, Navigation and Controls Subsystem Winter 1999 Semester Review.
Slide 1 Satellite Drag Modeling using Direct Simulation Monte Carlo (DSMC) Piyush M. Mehta and Craig A. McLaughlin The University of Kansas Acknowledgement:
MAE 4262: ROCKETS AND MISSION ANALYSIS
ADCS Review – Attitude Determination Prof. Der-Ming Ma, Ph.D. Dept. of Aerospace Engineering Tamkang University.
1 PHY Lecture 5 Interaction of solar radiation and the atmosphere.
Convection in Flat Plate Boundary Layers P M V Subbarao Associate Professor Mechanical Engineering Department IIT Delhi A Universal Similarity Law ……
Torque on a Current Loop
Spring 2002 Lecture #17 Dr. Jaehoon Yu 1.Conditions for Equilibrium 2.Center of Gravity 3.Elastic Properties of Solids Young’s Modulus Shear Modulus.
Aerodynamic forces on the blade, COP, Optimum blade profiles
Fuzzy Controller for Spacecraft Attitude Control CHIN-HSING CHENG SHENG-LI SHU Dept. of Electrical Engineering Feng-Chia University IEEE TRANSACTIONS ON.
Introduction to On-Orbit Thermal Environments
Aerodynamic Design of a Light Aircraft
TRIO-CINEMA 1 UCB, 2/08/2010 ACS Dave Auslander, Dave Pankow, Han Chen, Yao-Ting Mao, UC Berkeley Space Sciences Laboratory University of California, Berkeley.
Theory of Turbine Cascades P M V Subbarao Professor Mechanical Engineering Department Its Group Performance, What Matters.……
THE TSIOLKOVSKY ROCKET EQUATION
KUFASAT STUDENTS’ SATELLITE
Design of Port Injection Systems for SI Engines
Environment Simulator
Smart Nanosatellite Attitude Propagator ssl.engineering.uky.edu/snap
Aerodynamic Attitude Control for CubeSats
Lunar Trajectories.
MSU Solar Physics NSF REU Final Presentation
Dynamic Controllers for Wind Turbines
Virginia CubeSat Constellation
Kletskous Magnetic Stabilization
Energy in EM Waves: The Poynting Vector
ADCS, Attitude determination and control system
Attitude Determination and Control Preliminary Design Review
Attitude Determination Overview
IlliniSat-3 Power Board
Rocketry Trajectory Basics
First Order Inhomogeneous ODEs to Study Thermofluids
W L CG Dynamics Moment of Inertia LabRat Scientific © 2018.
Presentation transcript:

Attitude Control of the CubeSail Solar Sailing Spacecraft Victoria Coverstone, Andy Pukniel University of Illinois at Urbana-Champaign Rod Burton, Dave Carroll CU Aerospace ISSS 2010 New York

CubeSail Mission Overview Low cost solar sailing demonstration. Goal is to deploy 20 m 2 (80mm x 250m) of film between 2 nanosatellites. Deployment is to occur into a sun-synchronous terminator orbit above 800km altitude along the local vertical. Gravity-gradient aids in deployment and provides sail stiffening. Secondary payload opportunities are used to reduce cost. Validation of the dynamical and performance models and subsequent advancement of the TRL will likely lead to secondary demonstration followed by possible full-scale UltraSail experiment.

Research Motivation Consider two reasons for slow emergence of solar sailing technology: Challenges associated with stowage and deployment of large sails and stiffening structure (booms, masts, stays, etc.) High risk combined with high launch costs associated with investment in a poorly-characterized technology.

Technical Approach Stowage and deployment based on the UltraSail concept Sail material is stored in long strips wound onto motorized reels 3-axis stabilized satellite on each blade tip control the deployment and attitude Risk and cost reduction is achieved through IlliniSat-2 bus and secondary launch opportunities IliniSat-2 bus provides: Active 3-axis ACS achieved via magnetic torque actuation Deployable antenna and associated communication hardware C&DH capable of supporting wide range of payloads Power generation and management system Complete bus fits into 10x10x10cm volume IlliniSat-2 Bus Payload

55 Operational Sequence

Initial Detumbling and Stabilization Initial detumbling and stabilization is posed as a Linear Quadratic problem. Two operational modes: detumbling and tracking. Cost function depends on the mode and is either: the time to reduce angular body rates on all 3 axis below a threshold of 0.1 º/sec or the accumulated Euler angle error for values above 5º (figure below) Desired performance is achieved with GA-selected Q and R matrices.

Attitude Control Simulator Matlab-based simulator is used to test performance. Satellite DynamicsLQRMagnetic Torquers + T GG T AD Duty Cycle Direction Torque Typical single run Euler angles and rates are shown below.

Robustness Testing Results The attitude control simulator is run 1000 times with randomly varying ICs to ensure the selected penalty matrices are robust and the spacecraft can stabilize from any attitude and worst predicted rates of 5º/sec on all axis.

Modeling of External Forces Solar Radiation Pressure force model includes effects of: Reflection, absorption, and re-radiation The non-ideal parameters are given as: Aerodynamic Drag force is calculated using the method of accommodation coefficients and includes variations due to: Angle of incidence of incoming molecules Major atmospheric constituents at altitude Surface coating material and surface temperature Semi-diffuse reflection model

Aerodynamic Drag Results The Aerodynamic Drag force is computed for an undeformed sail in 2 ways: accommodation coefficient method classical method of constant coefficient of drag, C d, of 2.2 Interestingly, the classical method underestimates the magnitude of the force for all but high angles of incidence. In order to match the force computed using the accommodation coefficient method, C d must be varied between 0.9 and 2.9 in the classical equation.

Steady-State Shape of the Sail Steady-state deformations of the sail are computed by including forces due to: Solar Radiation Pressure Aerodynamic Drag Gravity-Gradient The sail is assumed to be traveling in a sun-synchronous terminator orbit. Sail is oriented with its edge to the orbital velocity direction. Deviation away from the local vertical is ignored and only out-of-plane deflection is considered. The governing equations can be written as:

Steady-State Shape of the Sail Deflections due to Solar Radiation Pressure are relatively small. Maximum out-of-plane deflection is approximately 18 m. Final angle away from the local vertical are approximately 15º.

Out-of-plane deformations along the sail length for varying pitch angles

Conclusions Optimization of Q and R matrices for the LQR controller with Genetic Algorithms provides good performance, robust results. Classical treatment of Aerodynamic Drag with constant coefficient of drag underestimates the force exerted on the sail. Equivalent coefficient of drag (specific to the CubeSail geometry and deployment orbit) varies between 0.9 and 2.9. Out-of-plane, steady-state sail deformation due to solar radiation pressure are relatively small as compared to the sail length.

Future Work Steady-state shape of the sail with a linearly-varying pitch (twist) along its length is studied. Non-linear gravity-gradient deployment dynamics in the presence of aerodynamic drag and solar radiation pressure is examined.

In-plane deformations along the sail length for varying pitch angles

Tension along the sail length for varying pitch angles

Questions?