The Development of Flight Operations: Improvement of ERAU Cube-Sat’s Ground System Interface and Research of the Satellite’s Orbital Decay Presented by.

Slides:

Advertisements

Similar presentations

GN/MAE155B1 Orbital Mechanics Overview 2 MAE 155B G. Nacouzi.

Advertisements

More Satellite Orbits Introduction to Space Systems and Spacecraft Design Space Systems Design.

Presented By: Capstone Team1 Date: 03/05/2010. Team Information Team Members  Ajay Chand Jasti  Suman Babu Alapati  Vamsi Krishna Guntupalli  Naveen.

Prince William Composite Squadron Col M. T. McNeely Presentation for AGI Users Conference CIVIL AIR PATROL PRESENTS The CAP-STK Aerospace Education Program.

1 Winter Launch Block Modeling and Results MMS Flight Dynamics Team MIWG 8 Feb. 20, 2014.

Global Positioning Systems (GPS) for Precision Farming

Colorado Center for Astrodynamics Research The University of Colorado 1 Computation of Azimuth and Elevation George H. Born These slides describe how to.

Polar – THEMIS Collaboration Opportunities Spacecraft Locations post launch Magnetopause campaign? Conjugate studies with THEMIS Ground Stations C. T.

Brandon A. Jones.

UHM CanSat Team Members: Chris Ho: Team master, software Tyson Fukuyama: Hardware.

Satellite Orbits 인공위성 궤도

Research Supported by NSF Alliance for Graduate Education and Professiorate (AGEP) Coverage Patterns for the Molniya Orbit and Iridium Constellation in.

PRESENTATION BASED ON GPS. Introduction To GPS Introduction To GPS.

Morehead State University Morehead, KY Prof. Bob Twiggs Understanding Orbits Orbit Facts 1.

Continuing Embry- Riddle’s CubeSat Satellite Development Program Presented by Clayton G. Jacobs Embry-Riddle Aeronautical University, Prescott EagleSat.

November 9th, 2011 Dr. Janise McNair, Paul Muri

Róbert Adam.  GLONASS = Global navigation satellite system (Globalnaya Navigatsionnaya Sputnikovaya Sistema)  Radio-based satellite navigation operated.

The Pursuit for Efficient S/C Design The Stanford Small Sat Challenge: –Learn system engineering processes –Design, build, test, and fly a CubeSat project.

Kick off meeting, swarm E2E study, nio #1 8-Sep-15 Development Approach Task 1: Industrial Module –to be used by industry for their system simulation –Output:

Tielong Zhang On behalf of the CGS Team in the Institute of Geology and Geophysics, Chinese Academy of Science Spacecraft System and Payload China Geomagnetism.

Different Coverage Patterns for a Single Satellite and Constellation of Satellites in Real Time with the STK Pedro A. Capó-Lugo Graduate Student Dr. Peter.

Student Satellite Project Tracking, Telemetry & Command UASat Progress Review Tracking, Telemetry and Command (TTC) January 26, 1999 Dana Irvin, Team Leader.

KHU Ground Station Nayoung Yoon KHU, 2010/10/041TRIO-CINEMA.

Near-Real-Time HIRDLS Processing for START08 Vince Dean HIRDLS Science Team Meeting January 30, 2008 Boulder, CO.

Development Progress of the EagleSat GPS Subsystem Presented by Tanner R. Hilken Embry-Riddle Aeronautical University, Prescott GPS Subsystem Lead.

GPS(Global Positioning System) -An Introduction. What is the GPS? Orbiting navigational satellites Transmit position and time data Handheld receivers.

AIAA RM Second ATS at UCCS Polar-Orbiting, Passive, Atmospheric Calibration Spheres (POPACS) Presented by R. Gilbert Moore Director, Project.

GEONS Ground Support System Java 7, JavaFX and the NetBeans Platform supporting NASA Missions Operations.

1 Directed by: Dr. PJ Benfield and Dr. Matt Turner Mentor : Miss Doreen Forsythe.

Why Design Tool? 93 年 10 月 21 日. EPS Course - 2 Simple Problems Close form solution Complex Problems Computer.

MATLAB Environment ELEC 206 Computer Applications for Electrical Engineers Dr. Ron Hayne.

EagleSat Flight Operations

Space platform and Orbits Introduction to Remote Sensing Instructor: Dr. Cheng-Chien LiuCheng-Chien Liu Department of Earth Sciences National Cheng Kung.

System Fundamentals as Facilitating CubeSat Development Marcus Bever EagleSat Systems Engineer Embry-Riddle Aeronautical University.

UNCLASSIFIEDUNCLASSIFIED Lesson 2 Basic Orbital Mechanics A537 SPACE ORIENTATION A537 SPACE ORIENTATION.

Flight Testing Small Satellites Through High Altitude Ballooning Presented by Zach Henney 18 April 2015.

1 Jet Propulsion Laboratory JPL Flight Team Adam Nikolic Josh Ruggiero Bob Hoffman Dusty Terrill.

ASEN 5050 SPACEFLIGHT DYNAMICS Two-Body Motion Prof. Jeffrey S. Parker University of Colorado – Boulder Lecture 3: The Two Body Problem 1.

EagleSat Flight Operations Mo Sabliny Dr. Yale Arizona Space Grant Symposium April 12, 2014.

AGBell -1- Build the A Train Constellation using STK Next we will use global information about the Earth to help define and understand how the A-Train.

ABSTRACT PREDICTIVE TRACKING ALGORITHM Visual Tracking of an Unmanned Aerial Vehicle (UAV) Using GPS Samuel S. Starr Emir Tumen Advisor: Dr. George Pappas.

Structural Design Software TYLER HUTCHISON. Requirements  Develop an interface to generate a text file.  The text file is then passed to one of five.

1 SOARS Matt Edwards Arseny Dolgov John Shelton Johnny Jannetto Galina Dvorkina Nick Driver Eric Kohut Kevin Eberhart Self Organizing Aerial Reconnaissance.

Designing a Communications System for Eagle Lisa Ferguson Dr. Gary Yale, Dr. Ed Post Arizona Statewide Symposium Announcements April 12, 2014.

S. Frey, UCB, THEMIS 1 25th ISSFD, Munich, Germany, Oct.19-23, 2015 ARTEMIS THEMIS ARTEMIS The Revised Concept of the THEMIS and MMS Coordination Sabine.

Categories of Satellites

AAE450 Senior Spacecraft Design Goppert, 1 James Goppert Week 8: March 8 th, 2007 Aerodynamics: Reentry Optimization Dynamics and Control: Communication.

CubeSat Re-Entry Experimental System Testbed C.R.E.S.T. STK 11 This software is an orbital simulator that allows the user to examine the flight path of.

EagleSat-1 Continuing Embry-Riddle’s CubeSat Satellite Development Program

Western University Automatic Response System (ARS) for Real Time Calculation of Earthquake Ground Motions; and Interactive Ground Motion Maps (IGM-maps)

Automata Editor Tool with GEF and EMF

Environment Simulator

Smart Nanosatellite Attitude Propagator ssl.engineering.uky.edu/snap

USNA Next Generation Ground Station

MSU Solar Physics NSF REU Final Presentation

ENG4361 Space Mission Design

ACS UC Berkeley Space Sciences Laboratory

LAUNCH OF GEO STATIONARY SATELLITES

LRO Mission Baseline Ephemeris v10.0

Michael Fusco AZ / NASA Space Grant Scholar

EagleSat-1: Flight Operations

SDO Flight Dynamics Subsystem

How do maps help us model the Earth?

EagleSat 2 – Program Overview

Sun – Earth System Questions

Atmospheric Re-Entry Goal: To re-enter the CubeSat into the atmosphere and survive re-entry and hit the ground without any deceleration from parachute,

PROBA 2 orbits and conditions of EUV observations V. Slemzin P. N

AZ/NASA Space Grant Symposium

EagleSat 2 – Mission and Development Overview

Dissecting Space Debris Events

Presentation transcript:

The Development of Flight Operations: Improvement of ERAU Cube-Sat’s Ground System Interface and Research of the Satellite’s Orbital Decay Presented by Madison Padilla Embry-Riddle Aeronautical University, Prescott EagleSat-1 Flight Operations Team Lead Mentor: Dr. Gary Yale 1

Outline Background Ground system overview Ground system breakdown Graphic user interface (GUI) layout Flight dynamics overview Analysis from Flight Dynamics Questions 2

Background The research and development has been done for the ERAU-Prescott cubesat, known as the EagleSat-1 Technical Objective: To improve and complete the ground system and to calculate and incorporate drag in order to predict the deorbit time of the EagleSat-1 3

Ground System A ground system to provide a Graphical User Interface (GUI) with EagleSat-1 through a serial connection to the Terminal Node Controller (TNC) View, save, observe and process data from EagleSat-1 Send commands to EagleSat-1 Transformational and Interactive Software Architecture Matrix Laboratories (MATLAB) chosen for all ground station software 4

High Level Flowchart 5

Data Flow Diagram 6

1. Time2. GPS 3. Raw Data Output 4. Position and Velocity 5. Data Source 7 1.Time -System Greenwich Mean Time (GMT) -System AZ Time -Satellite GMT -Satellite Mission Time 2. GPS -GPS Lock -State Vector -Latitude and Longitude -Altitude -Number of satellite locks 3. Raw Data Output 4.Position and Velocity -X, Y, Z position -X, Y, Z velocity 5. Data Source -Buttons for real-time or playback -Save and exit

Flight Dynamics Main objective: To calculate and incorporate drag in order to predict the deorbit time on the EagleSat-1 Orbital Predictions: Altitude at apogee: 810 km Altitude at perigee: 450 km Inclination: degrees Mean Local Time of Ascending Node: 13:35 Assumed launch date: January 16, 2017 All flight dynamics analysis is done in Systems Tool Kit 10 (STK) 8

STK Analysis - Coverage Passes over Ground Station (located in AXFAB) 3 to 6 passes per day 2-3 passes within ~1-2 hours, separated by ~8-10 hours Mean coverage time: approximately 10 minutes Example of STK coverage generation file, based upon assumed launch date Place-Embry_Riddle_Aeronautical_University_AZ-To-Satellite-EagleSat1: Access Summary Report Embry_Riddle_Aeronautical_University_AZ-To-EagleSat Access Start Time (UTCG) Stop Time (UTCG) Duration (sec) Dec :31: Dec :46: Dec :12: Dec :24: Dec :04: Dec :09: Dec :39: Dec :53: Dec :19: Dec :33:

Eclipse Times Eclipse Analysis, based upon assumed launch date 01/16/17 Eclipse duration: 8 seconds to 40 minutes Average eclipse duration: 9.18 minutes Example of STK eclipse summary: Start Time (UTCG) Stop Time (UTCG) Duration (sec) Jan :00: Jan :22: Jan :22: Jan :23: … 16 Jan :32: Jan :32: Jan :32: Jan :00:

Questions? 11