1. Project Λscension

2. Vehicle Dimensions
• Weight: 19.6 Ib
• Length: 112.5 in (9 ft. 4.5 in)
• Diameter: 6 in
• Fin Semi-Span: 6 in

3. Key Design Features

4. Key Design Features
Payload Containment Device

5. Key Design Features
Piston Parachute Deployment

6. Key Design Features
Piston Parachute Deployment

7. Launch Vehicle Interfaces

8. Final Motor Choice

9. AeroTech K1275R Thrust Curve

10. Mass Statement
Pad Weight (lbs)
8 ft. rail exit velocity
(ft./s)
Thrust-to-Weight
Ratio
Simulated Altitude
(ft. AGL)
24.1 83 14.5 4280
29.0 75 12.1 3355
30.6 73 11.4 3090

11. Static Stability Margin
Center of Gravity (inches from nose): 67.9
Center of Pressure (inches from nose): 89.7
Stability Margin (diameters): 3.6

12. Parachutes
Parachute Size (in) Harness
Harness
Length (ft.)
Descent Rate
(ft./s)
Drogue 30
5/8" tubular
nylon
9 50
Payload 42 3 20
Main 72 15 20

13. Kinetic Energy

14. Predicted Drift

15. Test Plans

16. Subscale Test Flight
Friends of Amateur Rocketry site
Mojave Desert

17. Subscale Vehicle Summary
• Length: 72 in
• Diameter: 4 in
• Stability: 3.2 caliber
• Pad Weight: 7.9 lbs.
• Motor: AeroTech J350W

18. Subscale Test Flight
Launch Conditions
Date: 12/20/2014
Location: Friends of Amateur Rocketry site,
Mojave Desert
Weather: dry, overcast
Temp: 45 F
Wind: calm (3 – 5 mph)
Launch angle: 5 degrees

19. Subscale Recovery
Missile Works RRC2+ altimeters

20. Subscale Recovery
• 24” elliptical drogue
• 48” elliptical main

21. Subscale Flight Results
• Stable Flight
• Successful Recovery
• 3314 ft. simulated altitude
• 2726 ft. reported by RRC2+ altimeter

22. Piston Ejection Ground Test

23. Piston Ejection Ground Test

24. Status of Requirements Verification
Launch Vehicle Requirements Status
The vehicle shall deliver the payload to 3000 ft. AGL. In progress
The vehicle shall carry a commercially available altimeter for official scoring, and a back-up altimeter. Complete
The altimeter shall report the altitude in a series of beeps. Complete
The vehicle shall be designed to be recoverable and reusable. Complete
The vehicle shall have a maximum of four independent sections. Complete
The vehicle shall be limited to a single stage. Complete
The vehicle must be able to remain in a launch-ready configuration for at least one hour. In progress
The vehicle must be capable of being prepped for launch in less than two hours. In progress
The vehicle must have a dual-deploy recovery system. Complete
At landing each independent section shall not exceed a kinetic energy of 75 ft-lb. Complete
The on-the-pad cost of the launch vehicle and AGSE shall not exceed $5000. Complete

25. AGSE Design Overview

26. AGSE Design Overview

27. AGSE Design Overview

28. AGSE Design Overview

29. AGSE Design Overview
Wheel spindle shaft will sit tightly in an opening in the spindle. A 10-
24 screw and washer /lock nut will be used to provide additional
support and friction. The spindle will be attatched to the motor with
10-24 screws, allowing the wheel to be turned by the motor

30. AGSE Dimensions

31. AGSE Design Overview
Pan/Tilt Servos
Servo connections
Pixy connection
to Arduino ISCP
connection
Lens and
Reset Button

32. AGSE Design Overview
HS-422
Gripper
HS 645
Wrist Servo
HS-755 Elbow
Servo
C-Brackets HS-805 BB Shoulder
Servo

33. AGSE Integration