Flight Readiness Review University of Illinois at Urbana-Champaign - PowerPoint PPT Presentation

Flight Readiness Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1

Overview Illinois Space Society 2

Launch Vehicle Summary Javier Brown Illinois Space Society 3

Flight Profile Illinois Space Society 4

Current Launch Vehicle Design 3) Nose cone separation and parachute deployment at 1000 feet 1) Ejection charge at apogee Nose cone Upper body tube 2) Drogue deployment at apogee Coupler Booster tube Illinois Space Society 5

Vehicle - Major Dimensions Total Length: 130’’  Total Mass: 43.5 lb.  Nosecone: 30’’  Upper Airframe: 48’’   Payload Bay: 14’’  Avionics Coupler: 16’’  Booster Frame: 48’’  Outer Diameter: 6’’  Root Chord (Fins): 12’’ Illinois Space Society 6

Vehicle - Mass Statement  Mass of rocket increased due to heavier nosecone and ballast – Heaver nosecone required ~1 lb of ballast in top centering ring for stability Mass Breakdown Subsystem Mass (lbm) Structures 17.62 Recovery 8.32 Motor 9.32 Rover 2.02 Platform 3.42 Total 40.7 Illinois Space Society 7

Vehicle - Stability  Stability @ liftoff: 2.48 calibers  Current CP location: 97.064’’  Static CG location: 81.974’’  Ballast utilized just above top most centering ring to guarantee and ideally stabilized vehicle. Illinois Space Society 8

Vehicle - Propulsion Motor: L1420R-P  Diameter: 2.95’’ (75 mm)  Max thrust: 374 lbf  Total impulse: 1038 lbf ･ s  Burn time: 3.18 s  T/W ratio: 8.49  Off-rail speed: 61.4 ft/s 3 8 ’’ Aircraft grade ⁄  plywood centering rings  RMS 75/5120 Casing Illinois Space Society 9

Airframe - Recovery  U-Bolt connections for strength  1/4”-20 T-nuts/Bolts for “permanent” attachments  Two rotary switches  Parachutes  Main: Iris Ultra 96”  Drogue: Fruity Chutes Elliptical 18”  1/2” Tubular Kevlar shock cord  Redundant altimeters  1 TeleMetrum altimeter for altitude and location tracking  1 StratoLogger altimeter for altitude tracking Illinois Space Society 10

Nosecone - Recovery  U-Bolt connections for strength  Two rotary switches  Parachute  Nosecone: SkyAngle 40’’ 1/2” Tubular Kevlar shock cord  Redundant altimeters  1 Telemetrum altimeter for altitude and location tracking  1 StratoLogger altimeter for altitude tracking Illinois Space Society 11

Ejection Charges  Number of shear pins based on section weights, accelerations, and shear pin maximum forces  Black powder charges calculated with pressures and forces applied to the bulkhead Joint and Shear Pin Properties Joint Max Mass Max # of Shear Pins Accelerati Above Shear Required on Joint Force [lbm] [lbf] 1 8.17g 22.92 407 4 2 32g 8.25 264 5 3 32g 10.33 331 6 Amount of Black Powder Needed Joint Grams of # of Shear Diameter Length Area Force Pressure FFFFG Black Pins [in] [in] [in^2] [lbf] [psi] Powder 1 4 5.973 21 28.02 280 9.9992 3.0 2 5 5.829 22 26.69 350 12.96 4.5 3 5.973 14 28.02 420 14.98 3.0 6 Illinois Space Society 12

Vehicle Verification Plan  Full vehicle verification plan found in FRR  Major verification tasks – Verified aerodynamics and construction procedure with subscale creation and flight – Increased simulation accuracy – Small-scale and large-scale testing of components – Verified vehicle design and manufacturing during fullscale test flight Illinois Space Society 13

Kinetic Energy  Predictions determined using OpenRocket.  Terminal Velocities – Nosecone – 14.92 ft/s – Upper Airframe and Booster Frame 1 st separation: • Drogue – 103/85 ft/s • Main – 14.97 ft/s  Kinetic Energies – Booster Frame – 50.25 ft ･ lbf – Avionics Coupler – 11.67 ft ･ lbf – Upper Airframe w/ Payload – 40.81 ft ･ lbf – Nosecone – 14.95 ft ･ lbf  All kinetic energies are within specified threshold of 75 ft ･ lbf Illinois Space Society 14

Drift Predictions  Predictions determined using OpenRocket. All predictions are well within the stipulated threshold of 2640 ft. Drift in 0 mph Drift in 5 mph Drift in 10 mph Drift in 15 mph Drift in 20 mph Section​ winds (ft )​ winds (ft)​ winds (ft)​ winds (ft)​ winds (ft)​ Booster and 9.3​ 590​ 1041.4​ 1614.3​ 2335.32​ Upper Airframe​ 9.3​ 349.1​ 791.1​ 1430​ 2117​ Nosecone​ Illinois Space Society 15

Computational Fluid Dynamics  CFD performed to verify integrity of pressure readings for nosecone altimeters  Full 3D simulation done with ANSYS  Results show that pressure at nosecone shoulder is very close to pressure along body Illinois Space Society 16

Full Scale Test Flight  Launched on February 17 th , 2018 in Princeton, IL  Launch, ascent, and descent was successful – Ineffective deployment of nosecone parachute – Damage to nosecone shoulder and threaded rod  Altimeters successfully reported data Illinois Space Society 17

Figure of StratoLogger vs OpenRocket  Nosecone and coupler avionics data match well – Further proof of integrity of nosecone pressure reading  Actual flight data over-performed compared to OpenRocket predictions – Motor over- performance – Overestimated mass Illinois Space Society 18

Full Scale Test Flight – Ground Track  TeleMetrum GPS location superposed onto Google Earth ground image  Drift distance of 2137 ft., which is below competition requirement of 2500 ft. Illinois Space Society 19

Damages to Nosecone  Hard impact to shoulder and bulkhead of nosecone  Fiberglass shoulder severely cracked  Protruding end of threaded rod bent  Bulkhead alignment to nosecone compromised Illinois Space Society 20

Damages to Body Tube  Minor delamination on surface of blue tube – Caused by snow packed into section from parachute dragging section on ground  Most fraying near rotary switch cutout  Slight swelling and warping near tips – Makes fit with nosecone slightly difficult Illinois Space Society 21

Deployable Rover Payload Ryan Noe and Destiny Fawley Illinois Space Society 22

Payload Requirements  NASA Student Launch Requirements: – Teams will design a custom rover that will deploy from the internal structure of the launch vehicle. – At landing, the team will remotely activate a trigger to deploy the rover from the rocket. – After deployment, the rover will autonomously move at least 5ft. (in any direction) from the launch vehicle. – The rover will deploy a set of solar panels once it has traveled the 5ft. Required by the competition.  Internal Team Requirements: – Upon landing, the orientation mechanism must be able to rotate the rover to a position in which it can properly deploy. – After the rover has deployed the solar panels, the Arduino will receive readings from the solar panels. – 5 lb. limit – 5.95” diameter x 14.5” length Illinois Space Society 23

Payload Overview Rover Orientation Mechanism Illinois Space Society 24

Rover Design Iterations Version 1 (Proposal) Version 2 (PDR) Final Design Version 3 (CDR) Illinois Space Society 25

Wheel Design Iteration  Windmill wheels  Five point wheels – Less jarring – Optimized grip – Improved servo mount Illinois Space Society 26

Rover Overview  Miniaturized Off-Road Remote Terrain Explorer (MORRTE)  Consists of 3 segments attached with steel axles  All 3D-printed components  Each segment is specific to certain electronics Front Segment Middle Segment Back Segment Illinois Space Society 27

Front Segment of the Rover  2 solar cells  Two, five point wheels  Two servo motors  Servo-driven hinge  Orientation system latching loop  Electronics: – SD Card Reader – Power Boost – 3.7V Li-ion Battery Illinois Space Society 28

Middle Segment of the Rover  Camera and camera cover mounted on bridge  2 servo motors  2, 5 point wheels  Electronics: – Arduino Micro – MPU 6050 – HC-12 Illinois Space Society 29

Back Segment of the Rover  6V NiCd battery  Servo connection panel  Safety bridge  2 servo motors  2, 5 point wheels  Orientation system latching loop Illinois Space Society 30

Rover Prototyping First Round of Prototyping Final Round of Prototyping Prototyping Changes Rover segment • modifications Wheel modifications • Bridge designs • Solar cells • hinge/bridge assembly Camera mount • Illinois Space Society 31

Orientation System Overview  System to ensure rover leaves airframe upright  Bulkhead screwed to Upper Airframe  Platform rotated by servo motor  Controlled by Arduino Micro system Illinois Space Society 32

Orientation System Design Iterations Version 1 (Proposal) Version 2 (PDR) Final Design Version 3 (CDR) Illinois Space Society 33