NUSTA RS NASA Student Launch MAV Challenge 2016 Critical Design Review 15 Janurary2015 Northwestern University | 2145 Sheridan Road | Evanston, IL 60201

Launch Vehicle OverviewLaunch Vehicle Overview Requirements: 5280 foot apogee Sealing of vehicle Safe Recovery Specifications: Length: 106 in Diameter: 98 mm Mass: 18.2 lbs Stability: 4.25 cal

Materials Fiberglass Body tube, bulkheads Centering Rings Fins Nylon (1) 60” Main parachute (1) 12” drogue parachute Shock Cord Kevlar Recovery harness Steel Quick links Welded eyebolts Nomex Deployment bag Parachute Protectors Adhesive RocketPoxy West Systems

Key FeaturesKey Features Fins Trapeziodal Three fins Thickness: 0.125” Nose Cone Ogive design 24 inches long

Motor Cesaroni Technology K570 Exit rail velocity of 73.8 ft/s lbft-sec total impulse Thrust to weight ratio: 7.1:1 54 mm diameter

Recovery Apogee Deployment Drogue charges go off Drogue deploys Pieces tethered 700 feet deployment: Main parachute charges go off Main deploys with all pieces tethered Dual Deployment Main Altimeter: Missile Works RRC 3 Redundant Raven 3 Black Powder ejection charges

Mass StatementMass Statement Nose Cone: 556g Payload Section: 1007g Body Tube: 573g Eye bolts and coupler: 321g Payload: 113g Upper Body Section: 1578 g Body Tube: 859g 60” Parachute: 340g Eye bolts and hardware: 113g Shock Cord: 265g Avionics Bay: 494.7g Body Tube: 53.7g Coupler: 271g Avionics Hardware: 170g Booster: 4542g Body Tube: 1468g Trapezoidal Fin set: 341g Motor Mount (including motor): 1994g 3 x Centering Ring: 134.7g 12” Parachute: 55g Epoxy, Reinforcing: 200g Shock Cord + Hardware: 349g The total mass of the launch vehicle is 8258 grams (18.2 pounds). There is a margin of 160 grams before the projected altitude goes below the projected altitude.

Kinetic EnergiesKinetic Energies Launch Vehicle SectionMassTerminal VelocityKinetic Energy Drogue configuration (12” parachute) 7.225kg = slugs m/s = ft/s 950 J = 701 ft-s Payload/Nosecone (60” parachute) 7.225kg = slugs 3.14 m/s = ft/s J = ft-s

Wind DriftWind Drift Wind Drift Simulations 0 mph5 mph10 mph15 mph20 mph 6.5 feet470 feet1,046 feet1,648 feet2,215 feet

Subscale Launch PredictionsSubscale Launch Predictions

Subscale Launch ResultsSubscale Launch Results Prediction of Launch Actual Raven 3 Altimeter Data

RocketFlight StabilityRocket Flight Stability The design of the rocket is currently overstable to compensate for possible changes in mass of components once fabrication occurs CP (inches)CG (inches)Static Margin Subscale Fullscale

K570 Thrust to weight ratio of 7.1 Rail exit velocity of 45 ft/s

PayloadDesign OverviewPayload Design Overview Magnetically sealed with rare earth magnets: 33.7lb paired with 75.28lb magnetic pull force Polyethylene to cushion and secure payload Bulkhead and aluminum brace for extra support

AGSE InformationAGSE Information Critical FOS: 2.55 to yield Dimensions 1.5 ft. wide ft. high May extend to provide more stable mechanical locking position ft. long May shorten to save mass since rail is longer than necessary 35.6 cubic feet is well below requirement Mass Prediction: 130 lb

AGSE Information – Electronics No changes since PDR except the motor drivers, which now have 15 amp capacity to accommodate the new linear actuators Igniter integration to AGSE by second week of February to allow lift testing

AGSE Information – Payload Retrieval Current base: Lynxmotion AL-5D (right) Mounting position: vertical beam of AGSE Projected specifications: Max. reach: 20” Arm lengths (first and second): 10” Base motor torque: ~500 oz-in Midpoint motor torque: ~300 oz-in Structural component material: carbon fiber Electrical: Arduino Uno R3, Pololu Mini Maestro servo controller Power: Independent, 7.2 V NiMH rechargeable Weight: < 50 oz

Payload Arm: Movement StepsPayload Arm: Movement Steps Rest position: First segment vertical, second placing gripper over payload bay Payload grasp: Both segments extended maximally toward payload Drop position: Identical to rest position; payload dropped into bay Bay closing: Arm moves upward along LV contour to close payload door

Question s?

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