Lenoir-Rhyne University Preliminary Design Review 625 7th Ave NE, Hickory, NC 28601
- Team Summary - Launch Vehicle Design - Recovery System - Payload Lander and Door Deployment - Design Rover - Safety - Project Plan
Name Douglas Knight, Ph.D Charles Cooke, Ph.D Joseph Johnson Visiting Assistant Professor Graduate Student & Professional Title Professor of Physics of Physics Assistant at NCSU Position in LRRT Mentor Adult Educator Adult Educator Juan Hernandez Brett Haas Jackson Cook Jake Robinson Eric Carranza Spencer Furches Nikki Williams Aaron Kennedy John Amodeo Prashil Dulal Tales Miranda Kaleb Davis Angel Martin Carles Lobo Claire Neibergall Jeremy Wagner
- Team Summary - Launch Vehicle Design - Recovery System - Payload Lander - Design Rover - Safety - Project Plan
• Increased rocket length of 92” (233.7 cm). • Increased consistent diameter of approximately 6.14” (15.6 cm). • The drogue parachute has decreased to 12” in diameter. • Fins changed and the design for them will consist of a slight increased root chord of 10.75” (27.3 cm), a tip chord of 3.5” (8.9 cm), a slight decrease height of 6” (15.2 cm), a decreased sweep length of 6” (15.2 cm) and the sweep angle of the leading edge of the fins have decreased to 45 degrees.
I. The rockets overall length will be 92” (233.7 cm) with a consistent diameter of approximately 6.14” (15.6 cm) II. Nose cone as designed is 8” (20.3 cm) long and has a power series shape III. Dimensions for these fins are a height of 0.472” (1.2 cm), a length of 18.5” (47 cm), a sweep length of zero, and the sweep angle will be zero as well. Four fins will be constructed for our fin can at the base of the rocket IV. Design for them will consist of a root chord of 10.75” (27.3 cm), tip chord of 3.5” (8.9 cm), height of 6” (15.2 cm), sweep length of 6” (15.2 cm) and the sweep angle of the leading edge of the fins are 45 degrees V. Motors being used for simulation are Aerotech K1000T and Cesaroni K660
Airframe Structural Ease of Safety Precautions Price Total Material Strength Fabrication to User 34 Kraft Phenolic 7 10 8 9 ● The decision matrix results indicate that using kraft phenolic as the 25 Fiberglass 9 7 4 5 airframe is the best alternative. This 30 Carbon Fiber 10 8 6 6 material scored higher in all areas except for structural strength. Furthermore, to justify each airframe material, a pros and cons and table is provided Airframe Pros Cons Material Kraft Relatively inexpensive, easy to work with, and Relatively low strength, can be Phenolic minimal safety precaution to the user. brittle, will absorb water
Fin ● Through this decision matrix Structural Strength Ease of Fabrication Performance Total Style we find that Clipped Delta fins 23 Trapezoidal 7 8 8 Scored Higher. 25 Clipped Delta 8 9 8 ● Pros and cons, further explains 21 Elliptical 7 7 7 our justification for fin style Fin Pros Cons Design Clip Has higher fuel efficiency at subsonic Due to the shape of these fins, they are more Delta speeds and a higher aspect ratio. susceptible to impact damage.
• fins will have a root chord of 10.75” and a tip chord of 3.5”. • The height of the fins will be 6” with a sweep length of 6” and a sweep angle of 45 degrees. • These clipped deltas will be through the wall fins that extend 1.4” from the airframe within the launch vehicle. • Fins are made from ¼” fiberglass
Nose Cone Structural Ease of • Power series shall be used for the launch Performance Total Style Strength Fabrication Vehicle, identified by decision matrix 22 Ogive 7 7 8 Power 24 8 7 9 • Power series shape allows the team to Series utilize the necessary amount of space 23 Ellipsoid 9 6 8 needed for the rover electronics. Nose Cone Pros Cons • Pros and cons table justified our Style decision These type of nose cones provide If the launch vehicle reaches a greater altitude and plenty of supersonic speed then this nose cone inner space when it comes to would not be as ideal as a nose cone Power Series flying large rockets. It also • Since the nose cone is 3D printed the that has a more pointed shape, which provides the least amount of drag could spread the heat generated at this choice of polymer is Acrylonitrile when compared to the other speed over a larger area. designs. Butadiene Styrene (ABS).
• Nose cone is made from ABS material and 3D printed • The length of the nose cone is calculated to be 8” long with a base diameter of 6.12” wide. • Shoulders of the nose cone has a diameter of 5.9”, a length of 2.5”, and a thickness of 0.25”.
• We have chosen two different motors, an Aerotech K1000T and a Cesaroni K660. • We are proposing two different motors due to possible acquisition issues with motors that could occur going forward.
Fin Can Section Component Weight (lbs.) Component Weight (lbs.) Fin can sections is 10.75 lbs. Kraft Phenolic Clipped Delta 1.62 1.77 Airframe Fins Set Drogue Parachute Motor & Negative 0.323 5.9 Parachute & avionics bay weigh 5.44 lbs. Shock Cord Retention Parachute & Avionic Bay Section Component Weight (lbs.) Component Weight (lbs.) Payload section weighs 9.31 lbs. Kraft Phenolic Main Parachute 1.17 0.323 Airframe Shock Cord Main Parachute 0.776 Upper Bulkhead 0.327 Total mass of 25.5 lbs. Trackers, Altimeter Bay 0.441 Altimeters, and 1.51 Coupler Sleds Payload Section Rover Kraft Phenolic 0.993 Deployment 2.67 Airframe Electronics Nose Cone Nose Cone 0.726 0.34 Bulkhead Payload tube 0.441 Payload Bulkhead 0.327 Coupler Payload Parachute 0.325 Rover 3.00
Performance Predictions OpenRocket Simulations Aerotech K1000T Cesaroni K660 Weight (lbs) with Motor 25.6 24.1 Max Acceleration (ft/s^2) 294 291 Rail Exit Velocity (ft/s) 59.5 67.8 Maximum Velocity (ft/s) 611 571 Velocity at Deployment (ft/s) 85.3 172.5 Altitude Deployment of 4178.1 4252.5 Drogue Parachute (ft) Altitude Deployment of Main 800 800 Parachute (ft)
Descent Velocity Launch Vehicle Kinetic Energy at Mass (lb) After Dual Section Landing (ft-lbs) Deployment (ft/s) 13.4 45.1 Fin Can & AV 16.19 Bay 20.4 60.2 Payload Lander 9.13
• We see our drift calculations from 0 - Drift Calculations 20 mph, and the team notes that these Wind Speed Fin Can & AV Bay drift calculations are significantly 0 mph 0 ft lower. We are currently looking for a 5 mph 153 ft different alternative to find proper 10 mph 305 ft results for these drift calculations. 15 mph 450 ft 20 mph 591 ft
Vehicle Requirements Verification Requirements Verification Plan Status Method The apogee of the launch vehicle will be Will be verified The launch vehicle must reach an apogee tested once we have a full scale model. The before and after within 100 ft of the target apogee of Inspection results of this model will be used to alter the full scale flight, 4100 ft. mass to better reach the target apogee. January 2019 A secure motor during flight due to the Will be verified The motor retention system must motor retention system will be verified after before and after successfully secure the motor during Inspection the flight of the full scale model to full scale flight, flight determine its success January 2019 Verification of the these systems not Will be verified The LR Lander Payload System and sustaining damage will be confirmed after a before and after avionics bay touch the ground without Inspection full scale flight. Based on results we will full scale flight, sustaining any damage alter the recovery system for a safer descent January 2019
- Team Summary - Launch Vehicle Design - Recovery System - Payload Lander - Design Rover - Safety - Project Plan
• Landing legs were changed from 22” in length to 18.5”. • Angle of the landing legs was undecided during the proposal, the current angle is now decided to be at 30 degrees. • A linear actuator acting as a latch for deploying the door was initially proposed, this system will be replaced with two servo motors with hooks that will secure the door closed. • Previously a method for deploying the rover from the rover ramp was undetermined, the current system to be used utilizes a stationary hook in the rear and a rotating hook to release the rover in the front.
• The 12” drogue parachute will be attached to a 50 ft shock cord that is connected to the aft bulkhead of the avionics bay and the motor mount of the fin can section. • the 96” main parachute will be attached to a 30 ft shock cord that is connected to the fore bulkhead of the avionics bay. • The Payload parachute is 48” and will be attached to a 25 ft shock cord that is connected to the aft bulkhead of the payload section.
● The shock chords that we will be utilizing will be ½” Tubular Nylon Webbing. ● For the ½” size that will be used, there is a thickness of .06 to .09 of an inch with breaking strength of roughly 2000 pounds. ● The melting point of this material is 380 degrees Fahrenheit. Therefore, this implies that the material can withstand the heat from the energetic charge caused by dual deployment
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