Presentation Transcript

1. University of Colorado Boulder NASA Student Launch 2013-14 Critical Design Review
2. Table of Contents Vehicle Design Subscale Results Recovery System Design Hazard Camera Liquid Sloshing Aerodynamic Analysis Schedule Budget Questions
3. Vehicle Design Overview
4. Vehicle Design Overview Vehicle Name: HYDRA (HYdrodynamics, hazard Detection, Research for Aerodynamics) Carbon Fiber Airframe High stiffness to weight ratio Total Length: 154in Diameter: 3.9” Wet Mass: 32.1 lb Static Stability Margin: 6.4 Target Altitude: 6,000 ft
5. Final Motor Selection Final Motor Selection: Cessaroni L1720-WT Max/Avg .Thrust: 473/398 lbf T/W Ratio: 12.4 Rail size: 12 ft 1515 rail Rail Exit Velocity: 93.1 ft/s
6. Stability Margin Static Stability Margin: ~6-8
7. Mass Statement
8. Mass Statement Current Wet Mass: 32.1 lb Potential mass growth: ~2.5 lb Expected Weight: 33 lb Mass Margin: +/- 2.5lb This will keep the team near their target altitude of 6000ft.
9. Subscale Results
10. Subscale Results Total Length: 99.5 in Diameter: 54 mm Wet Mass: 9lb Static Stability Margin: 6.4 Motor: Cesaroni K-360 Projected Altitude: 9216 ft
11. Subscale Results Static Stability Margin: ~6-10
12. Subscale Results
13. Recovery System
14. Parachute Design Elliptical cupped Simple design 8 ft. diameter main parachute Descent Rate: 18 ft/s 3 ft. diameter drogue parachute Descent Rate: 50 ft/s Example of elliptical cupped parachute
15. Manufacturing Pattern cut from 1.9 ounce rip stop nylon Sewed with rolled hem seam and Dual Duty XP Heavy Nylon Thread Reinforced with 1” tubular nylon which continue to become shroud lines.
16. Chute Testing Chutes will be dropped off tall building with a small mass attached to determine drag coefficient. Strength test of seams will be done using a strength tester.
17. Electronics Bay Motor section Parachute Placement/Deployment First section Middle section Main will deploy between first section and electronics bay Drogue will deploy between middle section and motor section Trigged by two black powder charges each deployment
18. Kinetic Energy (ft-lbf)
19. Recovery attachments Two 25ft sections of 1” tubular Kevlar shock cord and one 1ft One for each chute and one for payload integration Chutes attached by high strength (2,500lbf)swivel and 3/8” quick link to shock cord Shock cord attached to bulkhead assemblies using quick links. Bulkheads are made of ¼” birch aircraft plywood.
20. Avionics Using Raven Featherweight altimeters 1st event (drogue deployment) at apogee 2nd event (main deployment) at 1,000 ft. AGL Redundant altimeter is also a Raven Wiring for Raven3 Featherweight
21. Vehicle Drift (0 mph)
22. Vehicle Drift (5 mph)
23. Vehicle Drift (10 mph)
24. Vehicle Drift (15 mph)
25. Vehicle Drift (20 mph)
26. Hazard Camera Payload
27. Hazard Camera (HazCam) Payload Overview Scans ground looking for Hazards Image is taken and sent to Raspberry Pi Raspberry Pi analyzes image and looks for Hazard When hazard is found, it is transmitted to ground station All footage is saved onboard for post-launch analysis Drawing of Nosecone-HazCam Assembly
28. HazCam Payload - Block Diagram HazCam connects to Comm System via USB to Arduino Board Uses cost effective and easy-to-use Raspberry Pi hardware
29. HazCam Payload - Design Used to process image Handles transmission to Xbee transmitter Built by makers of Raspberry Pi, comes with fully built library Capable of HD video
30. HazCam/GPS-CommSystem Integration Placed within nosecone Mounted on Fiberglass Sled Secured in place with 8-32 all-thread Hazard Camera is at top of nosecone Clear acrylic lid on top of nosecone
31. HazCam Algorithm - Current State
32. HazCam Algorithm - Future Work Increase Speed Translate to C Reduce False Positives
33. Liquid Sloshing Payload
34. Liquid Sloshing Overview Tests a new method for mitigating liquid sloshing in fuel tank in microgravity Fuel contained in flexible bag in pressurized container Acceleration data and camera videos recorded by Raspberry Pi on SD card Data processed post-flight
35. Experiment Design and Analysis Control tank: water free to move about tank Experimental tank: water confined to flexible bag in pressurized tank Tanks isolated by electronics bay Acceleration data measured Data verified by video data Two launches: full scale and competition for greater sample size and less error
36. Liquid Sloshing Design Overall Dimensions: 17” long, 3.9” diameter Placed in middle body tube of rocket just above drogue parachute Bulkheads bolted into rocket body hold payload in place Two tanks: control and experiment, separated by electronics bay Accelerometer mounted to outside of experimental tanks LEDs light up coupler tubes for camera
37. Electronics Overview Data from camera and accelerometer processed by Raspberry Pi microcomputer Data stored on SD card for post-flight analysis Raspberry Pi powered by 5V USB charger, camera and accelerometer powered through Pi LEDs powered by 2x 9V batteries in electronics bay
38. Liquid Sloshing Integration Payload built utilizing coupler tubes and bulkheads that are similar to avionics bay Payload is bolted into rocket body tube through ½” bulkheads
39. Testing Plan Pressure test acrylic tank to ensure 4:1 pressurization safety factor Drop test to ensure payload survival in case of parachute failure Accelerometer test to confirm it can withstand 13g liftoff accelerations Systems integration testing to ensure proper component interfacing and wiring logic
40. Aerodynamic AnalysisPayload
41. Aerodynamic Analysis Overview Payload to satisfy requirement 3.2.2.2 – Aerodynamic analysis of protuberances during flight Goals: To determine drag of different shaped protuberances through pressure measurement To correlate and verify experimental data with CFD results
42. Aerodynamic Analysis Design Three mock “SRBs” are attached to the rear of the rocket Each SRB has a different geometry Pressure distribution over each SRB is measured
43. Scientific Overview By measuring the pressure distribution over each protuberance, a drag force can be obtained Knowing the drag force as a function of the velocity of the rocket will allow for calculations The velocity of the rocket can be used as an input for CFD analysis to compare predicted and experimental results
44. Electronics Isolation of systems Managed data flow Hardware filters of analog signals
45. Aerodynamic Analysis Integration Mounted to rocket utilizing a rail system Each SRB is an independent apparatus Easy to assemble and dissasemble
46. Aerodynamic Analysis Testing Structural testing Static pressure testing Data recording Circuit design Sensor communication Dynamic pressure testing Filtering Noise levels Leaks in pressure measurement system
47. Requirements Verification
48. Structures and Aerodynamics
49. Propulsion and Guidance
50. Avionics and Recovery
51. Ground Ops
52. Project Plan
53. Schedule
54. Budget
55. Educational Outreach Status Completed 1 Event Reached over 90 middle-school students 2 more activities scheduled this month 1 scheduled in April On target to reach goal of working with 200 students
56. Questions?