Mission Updates Payload and Subsystems Updates Rocket and - PowerPoint PPT Presentation

� Mission Updates � Payload and Subsystems Updates � Rocket and Subsystems Updates � Testing Updates � Management Updates 2

Our mission � Use a rocket to rapidly deploy a UAV capable of completing search and rescue type missions with the use of a ground based system requiring little to no UAV flight training. We aim to � Meet NASA’s Science Mission Directorate requirements � Decrease deployment time for UAV missions � Decrease flight skill needed for successful UAV mission � Simplify search and rescue, reconnaissance, and other UAV missions 3

� Launch UAV with rocket � Meet the needs of NASA Science Mission Directorate including: ▪ Gather atmospheric measurements of: pressure, temperature, relative humidity, solar irradiance, and ultraviolet radiation at a frequency no less than once every 5 seconds upon decent, and no less than once every minute after landing. ▪ Take at least two still photographs during decent, and at least 3 after landing. All pictures must be in an orientation such that the sky is at the top of the frame . ▪ All data must be transmitted to ground station after completion of surface operations. ▪ Science payload must carry GPS tracking unit. � Successfully perform model search and rescue/reconnaissance mission 4

Overview Materials: Fiberglass � Wing Span: 54” � Plain Weave Carbon Fiber � Fuselage Length: 45” � 6061-T6 Aluminum (Primary internal � components) Estimated Weight: 7 lbs. � ¼” plywood � Average Flight Speed: 55 mph � Polycarbonate (nosecone window) � Deployed UAV with transparent fiberglass 5

Folding Systems � Wing Rotating Mechanism: � 6061-T6 Al � Stronger springs Wing rotator location � Dihedral Hinge: Dihedral hinge � 6061-T6 Al � ¼” plywood bulkheads and spacers Folding Tail � � Wood inserts inside stabilizers and fuselage � Magnets as locking mechanism Empennage 6

Requirements: � Mass Cost � Launch rocket to 5280 ft (kg) (USD) � Deploy UAV at 2500 ft Propulsion 4.40 552.00 Concept � Airframe-Body 3.65 455.09 � Solid rocket motor Airframe-Fairing 1.01 27.00 Avionics/Comm 0.99 947.38 � Carbon fiber airframe Payload Support � Redundant flight computers Equipment 1.82 152.24 � Sabot deployment Recovery 2.19 434.60 � Dual deployment recovery SUBTOTAL 14.07 2568.31 7

� Loading Conditions � 890 lbf axial launch load � 225 lbf lateral launch load � 430 lbf deployment load � Analysis Performed � Body tube axial, lateral � Bulkhead deployment � Motor retention � Sabot stringer 8

� Rocket Motor – Cesaroni L1115 � Requires much less ground support than hybrid motor that was originally considered � 4908 N-s impulse - more than enough to reach target altitude given mass estimates � 4.7 Thrust-to-Weight ratio � Rail exit velocity (8 ft launch rail): 52 ft/s � Full-scale Test Motor – Cesaroni K1085 � Changed to adequately simulate launch levels � 1125 N-s impulse 9

� Mass estimates have decreased since PDR � Battery of simulations with varying wind speeds and launch rail angles � Optimal Ballast: 6.25 kg � All ballast placed at stage separation gives initial static margin = 2.08 10

� 3 ft drogue parachute � Rocketman Enterprises Inc � Ballistic Mach I � 14 ft main parachute � Rocketman Enterprises Inc � Standard Recovery System 11

������� ������������������������������� • ������������������������� • ����������������������������������� ������������������� !!��� • ������������������������������������ • ����������������������������"�����������������"� • ������#���� ���������������������������� • ��������������������������������������"��������������������� • Drogue Main Chute Chute Sabot Deployment Bag Broken Charge Sabot Released Locking Mechanism 12

� After UAV has passed flight testing and gains have been adjusted Drop Testing Rig � Electronics unnecessary to testing deployment capability and glide control replaced by ballast � Unpowered � No LiPo makes a potential crash safer � UAV in Sabot dropped from tethered balloon platform � 200 ft high � Radio controlled release � Sabot opens and UAV deployed as in real launch � UAV glides down under autopilot � Sabot descends under drogue 13

� Communication streams � Back-up UAV Controls: 72MHz � UAV command uplink / telemetry downlink: 900MHz � UAV real time video downlink: 2.4GHz � Hardware � ArduPilot Mega with IMU and MediaTek GPS to stabilise and control UAV � XBee Pro 900 to provide two-way telemetry/command link with groundstation � HTS3-R1-A and UV2-R1-A provide sensor data for SMD requirements 14

Top down view 15

Target Waypoint UAV Location 16

Waypoint Cruise settings Commands Control 17

Current Cruise Setting Sensor Data 18

Avionics Main parachute Assembly and sabot Nose cone Motor UAV assembly enclosed within Main chute and Drogue parachute sabot recovery system bulkhead 19

� The UAV and subsystems will be tested in three phases to minimize risk: � Phase 1: Ground Testing � Phase 2: Test Aircraft (commercially available RC) � Phase 3: UAV Testing � Ensures safe and proper function of systems throughout testing. � Thorough analysis of between phases � Flight testing of UAV to analyze and determine margin of error of flight behavior 20

� Goal � Test stability of our design � Specifications � ½ scale in size � Not ½ scale in weight due to safety concerns � Same (scaled) CG and CP locations as predicted for full scale rocket � Resulted in similar predicted static margin to full scale rocket � Aerotech H128 � MAWD for maximum altitude measurement � 778 feet- 50 feet more than Rocksim prediction 21

� Complete avionics system from ‘test aircraft’ integrated with UAV � Test autonomous flying capabilities � Drop tests from a tethered balloon to simulate UAV deployment � Simulated missions performed 22

� Structural Qualification � Tube crush/bending tests � Bulkhead bull tests � Nose cone release � Shear pin failure force � Black powder charge � Separation distance � Barometric testing � Charge release locking mechanism � Black powder charge � Operational verification � UAV Deployment testing � Locating components � Finding emergency locator transmitter 23

Key Payload Dates Key Rocket Dates 9/10 Project initiation 9/10 Project initiation 12/1 Stability analysis completed 11/19 PDR materials due 12/5 Prototype without folding 12/30 Scaled test launch mechanisms completed 1/24 CDR materials due 12/10 Test launch with only vital 2/15 Balloon Deployment Test electronics 2/30 Full-Scale test launch 2/1 Prototype with folding mechanisms completed 3/21 FRR Materials Due 2/20 Full-Scale test launch 4/14 Competition launch 24

� MIT Splash Weekend November 21 � Boston Museum of Science February 5 � MIT Museum May 1 � MIT Spark Weekend March 12 25

� Arduino Uno to process data and interface between sensor boards and non-volatile storage media � HTS3-R1-A, UV2-R1-A and SP1000 provide sensor data for SMD requirements � SD Card interface board to provide non- volatile data storage 27

� CMOS camera and AVS-2400 video transmission board to provide first person view � Canon PowerShot A470 digital camera for still capturing 28

� � Ensure flight computer works as expected in manual mode � Test telemetry system with groundstation software � Test fidelity and reliability of back up logging board � Test usable range of the real-time video system 29

�������� �� �������������������������������������������������������������������������������������������������������������������������������� �������������������������� ��

� Test autonomous flying capabilities including: � Straight and level flight � Waypoint tracking � Landing � Test flight computer with primary sensors for SMD attached � Back-up sensor board, visual system integrated in later flights 30