Lenoir-Rhyne University Critical Design Review 625 7th Ave NE, - PowerPoint PPT Presentation

Lenoir-Rhyne University Critical Design Review 625 7th Ave NE, Hickory, NC 28601

AGENDA ● Team Summary ● Launch Vehicle Design ● Recovery System ● Sub-Scale Vehicle ● 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

AGENDA ● Team Summary ● Launch Vehicle Design ● Recovery System ● Sub-Scale Vehicle ● Payload Lander and Door Deployment ● Design Rover ● Safety ● Project Plan

I. The launch vehicle has changed in weight from 25.3 pounds to 27.1 pounds. II. The finzaled motor choice is of the launch vehicle is the Aerotech K1000T

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 the landing legs housing 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 the fins 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. Motor being used for our simulation is an Aerotech K1000T

• The airframe will consist of kraft phenolic material • Working with phenolic is much easier, has minimal health concerns to the user, is lighter in weight and has an inexpensive price.

• LRRT is using a 75 mm threaded AeroPack motor retainer. • This retainer consists of two parts, a threaded base that attaches to the aft centering ring and a threaded ring. • The base is attached using six bolts • threaded metal are inserts inset into the centering ring and epoxied

• Clipped Delta • We chose these fins due to there higher fuel efficiency at subsonic speeds and a higher aspect ratio. • Method of Adhesion

• 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. • 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

• We will be utilizing a power series shape nose cone • This allows the team to utilize the necessary amount of space needed for the rover electronics. • The nose cone will be 3D printed and made of Acrylonitrile 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 6.10” wide. • Shoulders of the nose cone has a diameter of 5.8”, a length of 2.5”, and a thickness of 0.25”.

The motor that we have decided on is the K1000T for our proposed rocket. The K1000T has a diameter of 75 mm, a length of 38.3 cm, a total mass of 5.73 lbs, and a post ignition mass of 2.72 lbs. records the maximum thrust at 1140 N and burnout time of 2.47 second.

Fin Can Section Component Weight (lbs.) Component Weight (lbs.) Fin can sections is roughly Kraft Phenolic Airframe 1.62 Clipped Delta Fins Set 3.52 12.5 lbs. Top & Middle Centering Ring 0.222 Bottom Centering Ring 0.24 Drogue Parachute Shock Cord 0.323 Motor & Negative Retention 5.9 Motor Mount Tube 0.653 Drogue Parachute 0.018 Parachute & avionics bay Parachute & Avionic Bay Section Kraft Phenolic Airframe 1.17 Main Parachute Shock Cord 0.323 weighs roughly 5 lbs. Main Parachute 0.717 Fore Bulkhead 0.327 Altimeter Bay Coupler 0.441 Trackers, Altimeters, and Sleds 1.51 Payload section weighs 9.6 Middle Bulkhead 0.163 Aft Bulkhead 0.327 Payload Section lbs. Kraft Phenolic Airframe 0.989 Rover Deployment Electronics 2.00 Nose Cone 0.749 Nose Cone Bulkhead 0.338 Payload tube Coupler 0.439 Payload Bulkhead 0.325 Total mass of 27.1 lbs. Payload Parachute 0.325 Rover 3.50 Payload Parachute Shock Cord 0.161 Ramp Release Mechanism 0.20 Payload Landing Legs 0.626

Performance Predictions Simulations of K1000T OpenRocket Weight (lbs) with Motor 27.1 Max Acceleration (ft/s^2) 276 Rail Exit Velocity (ft/s) 53.3 Maximum Velocity (ft/s) 578 Velocity at Deployment (ft/s) 139 Altitude Deployment of Drogue 4080 Parachute (ft) Altitude Deployment of Main 800 Parachute (ft)

Descent Velocity After Dual Kinetic Energy at Launch Vehicle Section Mass (lb) Deployment (ft/s) Landing (ft-lbs) Launch Vehicle 27.1 139.0 8137.0 Fin Can & Avionics Bay 17.5 16.0 69.6 Payload Lander 9.6 20.7 64.1

V w * t = D ● Total descent time to be Drift Calculations approximately 65 second Wind Speed Launch Vehicle 0 mph 0 ft 5 mph 325 ft 10 mph 650 ft 15 mph 975 ft 20 mph 1,300 ft

AGENDA ● Team Summary ● Launch Vehicle Design ● Recovery System ● Sub-Scale Vehicle ● Payload Lander and Door Deployment ● Design Rover ● Safety ● Project Plan

• The recovery team has changed the main parachute from 96” to 84” due to weigh change of the launch vehicle.

● Stratalogger CF - Primary Altimeter ● Marsa 54 - Secondary Altimeter

D is defined as the inner diameter of the airframe and L is the length of the avionics bay. As designed the airframe diameter is 5.12 inches and 5.5 inches in length. As a result, the four pressure vent hole size will be approximately .149 inches in diameter. Drilled shall be sanded down to flatten any rigid phenolic.

U-bolt’s shall be used in its full-scale launch vehicle. The U-bolt has length of 2.4375” Height of 3.66”, and has a Diameter of 3.125”

Main Parachute will use a 84” elliptical chute with 30 foot of shock cord • Payload parachute will use 48” with 15 foot of cord • Drogue parachute will be 12” 50 foot of cord

AGENDA ● Team Summary ● Launch Vehicle Design ● Recovery System ● Sub-Scale Vehicle ● Payload Lander and Door Deployment ● Design Rover ● Safety ● Project Plan

Analysis of ⅔ Sub-scale Fin Can Section Component Weight (lbs.) Component Weight (lbs.) Clipped Delta Fins Blue Tube Airframe 0.642 0.485 Set Centering Ring 0.1 Epoxy 0.101 Drogue Parachute Motor & Negative 0.216 0.52 Shock Cord Retention fin can sections weighed 2.13 lbs Motor Mount Tube 0.061 Drogue Parachute 0.04 Parachute & Avionic Bay Section Component Weight (lbs.) Component Weight (lbs.) the parachute & avionics bay weigh 1.59 lbs. Main Parachute Blue Tube Airframe 0.399 0.13 Shock Cord The payload section weighs 1.38 lbs; resulting in Main Parachute 0.19 Trackers, Altimeters, Altimeter Bay a total mass of 5.1 lbs. 0.669 0.202 and Sleds Coupler Payload Section Lander Legs & Blue Tube Airframe 0.555 0.1 Hinges Nose Cone 0.234 Payload Parachute 0.106 Payload tube 0.121 Coupler Payload Bulkhead 0.171

Aerotech H125W Total Impulse 2511.5Ns Motor Launch Mass 0.496 lbs Mass After Ignition 0.174 lbs Simulated Apogee 1643ft

Performance Predictions Aerotech H125W Openrocket Weight (lbs) with Motor 5.1 Max Acceleration (ft/s^2) 204 Rail Exit Velocity (ft/s) 51.8 Maximum Velocity (ft/s) 347 Velocity at Deployment (ft/s) 69.4 Altitude Deployment of Drogue 1643 Parachute (ft) Altitude Deployment of Main 600 Parachute (ft)

Descent Velocity Launch Vehicle Kinetic Energy at Mass (lb) After Dual Section Landing (ft-lbs) Deployment (ft/s) 60.3 288.2 Launch Vehicle 5.1 21.9 20.1 Fin Can & Avionics 2.7 Bay 41.37 63.84 Payload Lander 2.4

V w * t = D ● Total descent time to be Drift Calculations approximately 95 second Wind Speed Launch Vehicle 0 mph 0 ft 5 mph 461 ft 10 mph 922 ft 15 mph 1,383 ft 20 mph 1,841 ft