Air-launched Earth-observing Ground Information System Carleton University’s 4 th Satellite Design Team Introduction to AEGIS

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