1 / 43

University of South Alabama Launch Society Preliminary Design Presentation

University of South Alabama Launch Society Preliminary Design Presentation. . * The symbol (*) indicates the slides that were changed after the PDR was submitted Revision: 01/24/2014. Vehicle Design Concept. ALTIMETER BAY DESIGN CONCEPT. Triple altimeter tray design concept.

damara
Download Presentation

University of South Alabama Launch Society Preliminary Design Presentation

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. University of South Alabama Launch Society Preliminary Design Presentation . * The symbol (*) indicates the slides that were changed after the PDR was submitted Revision: 01/24/2014.

  2. Vehicle Design Concept

  3. ALTIMETER BAY DESIGN CONCEPT • Triple altimeter tray design concept. • Recovery system altimeter(s) separate from competition scoring altimeter.

  4. PAYLOAD BAY DESIGN CONCEPT

  5. MOTOR BAY DESIGN CONCEPT

  6. LAUNCH VEHICLE VERIFICATION AND TEST PLAN OVERVIEW • The team plans to highlight all vehicle requirements established by NASA and incorporate them into the overall design of the vehicle. • A checklist containing these requirements and their verification status will be created and implemented in the testing of each system and subsystem to verify the vehicle meets these requirements.

  7. LAUNCH VEHICLE VERIFICATION CHECKLIST

  8. Parachute Design • Annular Parachute Design • Gore Construction • Flat Fell Seams

  9. Parachute Testing • Drag Testing Displacement Gauge Wind Gauge Displacement Readout

  10. Data Extraction

  11. Results

  12. RECOVERY DESIGN CONCEPT

  13. Cable Cutters

  14. Dual Deployment System • Single Bay Deployment • Attached Drogue • Bundled Main Parachute • Pyrotechnic Cable Cutters

  15. Material Selection • Materials will be down-selected based on the following criteria: Compressive Strength, Cost, Density, Destructive Interference, Flexural Strength, Manufacturability, and Tensile Strength.

  16. Stages of Flight • Four primary stages of rocket flight • Compression (1) • Tension (2) • Tension (3) • Impact (4) * Slide addedafter PDR was sent to NASA (Minor) Revision: 01/24/2014.

  17. FINITE ELEMENT ANALYSIS: • Finite element analysis is a numerical method for finding solutions to boundary-value problems • FEA analysis will be used to theoretically test rocket components to validate initial selection and provide a minimum criteria for mechanical test to meet. * Slide changed after PDR was sent to NASA (Minor). Revision 01/24/2014. Impact Test on nose cone as it lands, showing magnitude of deformation in inches.

  18. PLAN FOR VEHICLE SAFETY VERIFICATION AND TESTING • Checklistswill be implemented with each subsection of the team rocket to ensure that a complete assembly is done. These checklists will cover the presence of all the components of a system along with the quality of the those parts. • Numberedchecklists will follow an order, requiring a prerequisite (excluding the first checklist), and a signature from the safety officer to continue. • A final checklist will be used to ensure all sections have been verified and the final rocket assembly is complete. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  19. PLAN FOR VEHICLE SAFETY VERIFICATION AND TESTING • NOTE: • If an item on the checklist can not be completed, no further assembly will continue until the issue can be resolved • As sections are finalized, the checklist will improve with more specialized instructions to complete. • The Range Safety Officerwill ultimately decide if the team rocket is flight worthy or if alterations must be made. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  20. PLAN FOR VEHICLE SAFETY VERIFICATION AND TESTING • PLANSfor testing will be created and applied by the team to reduce the risk of injury to a team member and/or damage to the rocket. • Testswill allow the team to verify calculations or that adjustments need to be addressed for further testing. • Safe locationswill be determined to perform the testing, as well as safe distances from which the team can experiment. • Documentationand video records (when applicable) will be taken by a team member to allow for further analysis of the test. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  21. PLAN FOR VEHICLE SAFETY VERIFICATION AND TESTING • Quality Control: • All testing will be performed in the presence of a professional, qualifiedperson, teammember, or mentor. • Testing plans will be reviewed by the safety officer and the team, and only performed when the safety officer has decided the plan is secure. • If a test yields vastly unexpected results, this information will be documented and reviewed. Failure causes will be reviewed and all information regarding the test will be re-verified before another test plan is formed. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  22. STATIC STABILITY MARGIN Simulated Center of Pressure and Center of Gravity Locations

  23. Baseline Motor Selection and Justification Parameters of the down selection in order of priority: • Satisfaction of thrust-weight ratio • Desired altitude with additional mass • Diameter of motor bay • Length of motor bay • Accessibility (CTI, Loki and Aerotech)

  24. Motor Database

  25. Thrust To Weight Ratio, Rail Exit Velocity • Thrust:weight = 11:1 • Satisfies the 5:1 thrust to weight ratio requirement • Exit velocity = 99 ft/sec

  26. Overview of Mathematical Model • Why are rocket flight paths unique? • Monte Carlo simulations can be used to predict a ‘solution space’. • Six differential equations of motion are considered the governing equations of the model. * Slide added after PDR was sent to NASA. Revision: 01/24/2014.

  27. Differential Equations of Motion

  28. The plot shows a comparison of drag force between “in-house” code written by Team South Alabama and free open-source software. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  29. Preliminary Results of PATHFINDER.M Estimated Drag Force at Zero Angle of Attack:

  30. Meteorological Effects: Regression Why use a quintic fit? • Quintic fits offer the ability to capture the necessary inflexion points. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014

  31. Meteorological Effects: Probability Distribution curves to apogee:

  32. Numerical Methods - 4th Order Runge Kutta: • A second order ODE can be decomposed into a system of two first order ODEs [1]: * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  33. Pseudocode: • Pseudo codes are often written to provide structure and efficiency in the process of writing a computer program. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  34. BASELINE PAYLOAD DESIGN

  35. PAYLOAD COMPONENTS ADXL377 High-G Triple-Axis Accelerometer BMP 180 Barometric Pressure/Thermometer XBee-PRO ZB with PCB Antenna Raspberry Pi Camera Board * Slide added after PDR was sent to NASA. Revision: 01/24/2014. Raspberry Pi Model B ADS1115 16-Bit ADC 4 Channel with Programmable Gain Amplifier Human and Environmental Studies Hazard Detection Multi-System Component Triboelectric Charge Detection (No image) LM393+SW18015 Vibration Sensor

  36. Data Handling Algorithms Sensor Data Processing Image Processing * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  37. PAYLOAD VERIFICATION AND TEST PLAN OVERVIEW (PAYLOAD TEAM) • Image Processing • A short range test for the camera, image processing code, and telemetry system will be completed as a line of sight test initially and an enclosed test later. • Long range ground test will follow the same procedure. • Testing aboard a rocket should be completed before the final launch date. • Human and Environmental Studies • Temperature, vibration, barometric pressure, and acceleration sensors will be individually tested and calibrated if necessary. • The software for each sensor will be tested individually then simultaneously. • The system will then be tested with the telemetry system included. • Testing aboard a rocket should be completed before the final launch date. • Triboelectricity • Circuit development is primary goal. • Lab testing is being completed on designed circuits. • A wind tunnel will be used to test the system on the ground. • Testing aboard a rocket should be completed before the final launch date. * Slide changed after PDR was sent to NASA (Minor). Revision: 01/24/2014.

  38. Project Plan (Budget and Finances) Management Plan and Cost of Every Section by Percentages

  39. Project Plan (Financing and Schedule) Financial Plan and Critical Path method

  40. Integration Plan and Telemetry Integration Plan and Telemetry System Technology

  41. Triboelectric Technology Integration Triboelectric Technology Integrated in the Rocket

  42. References

  43. Questions?

More Related