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

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Our mission

Use a rocket to rapidly deploy a UAV capable of

completing search and rescue type missions with the use

• f 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

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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

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Overview

• Wing Span: 54”
• Fuselage Length: 45”
• Estimated Weight: 7 lbs.
• Average Flight Speed: 55 mph

Materials:

• Fiberglass
• Plain Weave Carbon Fiber
• 6061-T6 Aluminum (Primary internal

components)

• ¼” plywood
• Polycarbonate (nosecone window)

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Deployed UAV with transparent fiberglass

Folding Systems

Wing Rotating Mechanism: 6061-T6 Al Stronger springs Dihedral Hinge:

• 6061-T6 Al
• ¼” plywood bulkheads and spacers
• Folding Tail
• Wood inserts inside

stabilizers and fuselage

• Magnets as locking

mechanism

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Wing rotator location

Dihedral hinge

Empennage

• Requirements:
• Launch rocket to 5280 ft
• Deploy UAV at 2500 ft
• Concept
• Solid rocket motor
• Carbon fiber airframe
• Redundant flight computers
• Sabot deployment
• Dual deployment recovery

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Mass (kg) Cost (USD) Propulsion 4.40 552.00 Airframe-Body 3.65 455.09 Airframe-Fairing 1.01 27.00 Avionics/Comm 0.99 947.38 Payload Support Equipment 1.82 152.24 Recovery 2.19 434.60 SUBTOTAL 14.07 2568.31

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

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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

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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

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3 ft drogue parachute

• Rocketman Enterprises Inc
• Ballistic Mach I

14 ft main parachute

• Rocketman Enterprises Inc
• Standard Recovery System

• !!
• ""
• #
• "

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Main Chute Deployment Bag

Sabot Sabot Drogue Chute Broken Charge Released Locking Mechanism

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Drop Testing Rig

• After UAV has passed flight testing and gains

have been adjusted

• 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

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

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Top down view

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UAV Location Target Waypoint

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Cruise settings Control Waypoint Commands

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Current Cruise Setting Sensor Data

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

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

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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

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

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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

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

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

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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

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CMOS camera and

AVS-2400 video transmission board to provide first person view

Canon PowerShot A470

digital camera for still capturing

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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

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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

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