Air-launched Earth-observing Ground Information System

1
Air-launched Earth-observing Ground Information
System
Introduction to AEGIS
Carleton Universitys 4th Satellite Design Team
2
Purpose of Team Design Projects

• Purpose
• For students to gain practical experience
• Through student driven team design
• Through industry contacts
• Types of projects
• Formula SAE
• Aircraft Design
• Multi Simulator
• Micro Turbine
• Mining Vehicle
• Satellite Design

3
Current Market

• Most microsatellites cannot acquire a dedicated
  launch
• Must piggy-back on larger satellites destined for
  the same orbit
• Inconvenient and may hinder mission optimization
• Visible, infrared, microwave and radio spectra
  are used for remote sensing
• The spectra are used for various applications
• Thermal infrared is not exploited to its full
  potential

4
Mission Statement

• To design a rapidly deployable air launched
  microsatellite for the purpose of Earth
  observation"

5
Objectives

• To capture thermal images of Canada, to benefit
  the fields of agriculture, environmental studies,
  and geology
• To develop a rapidly deployable Canadian
  air-launch system for the purpose of launching
  microsatellites
• To develop new technologies for the aerospace
  industry
• Determine new markets made available by these
  technologies
• To demonstrate the capabilities and value of the
  AEGIS team members to the Canadian aerospace
  industry

6
Applications of STK Software

• Mission Analysis (to date)
• Helped determine orbital parameters
• Created ground trace for presentation purposes
• Future Work
• Simulations of orbital drag
• Second iterations of orbital parameters
• Possible visual simulations for presentation
  purposes

7
Applications of STK Software

• Sample ground trace

8
AEGIS Configuration

• Launch Vehicle
• 3 stage rocket capable of launching
  microsatellites into a LEO orbit
• CF-18 launched (deploying rocket at 50,000 ft)
• Al/AP/HTPB Propellant for solid rocket
• Stages 1 and 2 (stage 3 undetermined)

9
AEGIS Configuration

• Microsatellite Bus
• 3-axis stabilized configuration
• Semi-Major Axis 6945 km (Alt 567 km)
• Inclination 97.7 degrees (Sun synchronous)
• Eccentricity 0 (Circular orbit)
• Mission lifetime of 1-2 years
• Passive thermal control system
• Mass - 40 kg
• Power 70 Watts
• Dimensions (0.6m)3
• Dynacon Microwheel 100

10
AEGIS Configuration

• Payload Concept
• The payload applications is a wide range such
  as, soil moisture detection, drought monitoring,
  silica mapping, and possibly forest fire
  detection / mitigation
• Thermal imaging utilizes microbolometer arrays to
  capture images

11
Questions

• If you have any questions or comments, please
  feel free to contact us using the information
  provided below
•  James Huck Doug Staley
• Project Manager Faculty Advisor
• jamesthuck_at_yahoo.ca staleydoug_at_cs.com