Overview. Mission Overview Payload and Subsystems Rocket and Subsystems Management

Transcription

1 MIT ROCKET TEAM

2 Overview Mission Overview Payload and Subsystems Rocket and Subsystems Management

3 Purpose and Mission Statement 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. In doing this 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

4 Mission Requirements 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

5 UAV Payload Overview (1) Overview Wing Span: 4.5ft Fuselage Length: 3.75 ft Estimated Weight: 7 lbs Average Flight Speed: 45mph Materials: Wing, tail, and fuselage: Fiberglass around foam core Nose Cone: Polycarbonate Inrunner/Outrunner Pusher Motor with Graupner Foldable Propeller

6 UAV Payload Overview (2) Folding Systems Wing Rotating Mechanism: Spring Loaded Dihedral Hinge: Plastic Hinge Spring Loaded Latch Inside Wing Folding Tail Kevlar/Plastic Hinge Magnetic Locking System

7 Science Mission Directorate Payload The SMD Payload requires recording: Solar UVI Pressure Temperature Relative Humidity This data must be logged at a minimum of 5s intervals At least two still must be captured during descent and three after landing Logged data must be transmitted after landing

8 Payload Electronics The payload shall carry an ArduPilot Mega flight computer with the ArduPilot GPS/IMU navigation system To fulfil the SMD requirements the payload the UAV shall carry HTS3-R1-A, UV2-R1-A and SP1000 sensor boards(primary and secondary) DOSonCHIP and Arduino Uno boards for secondary logging Canon PowerShot A470 digital camera for still capturing To facilitate first person view at the ground station, the UAV will have a CMOS camera and AVS-2400 video transmission board

9 Payload Safety Verification and Testing Plan 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 Separation of testing phases ensures that all systems work properly and safely before increasing level of testing and inherent risk at each phase. A temporary parachute will be installed during UAV testing in case of propeller failure. Each phase will include thorough analysis of data to ensure predetermined safety and success criteria are met. Flight testing of test aircraft and UAV will be to analyze and determine margin of error of flight behavior and acting aerodynamic forces Flight simulation software will analyze UAV patterns and acting forces to ensure staying in safe descent velocities.

10 Rocket Overview (1) 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 Mass (kg) Cost (USD) Propulsion Airframe-Body Airframe-Fairing Avionics/Comm Payload Support Equipment Recovery SUBTOTAL

11 Rocket Overview (2) Key components Motor retention Body tube coupler Nose cone coupler Recovery system bulkhead Avionics package

12 Rocket Airframe and Materials Airframe Carbon fiber: 11 oz weave Aeropoxy 2032/3660 Bulkheads Plywood: fin core, motor centering Stainless steel: motor retention Nylon: recovery/deployment bulkheads 2-part foam: sabot 5 minute epoxy Various Phenolic tubing: motor mount, avionics package Nylon: avionics assembly components Stainless steel: quick links, eye bolts Nomex: chute protectors, deployment bags

13 Rocket Propulsion Design 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 Full-scale Test Motor Cesaroni K510 Similar enough to the L1115 that experience and knowledge is easily transferred 2486 N-s impulse

14 Flight Profile Modeling Battery of simulations with varying wind speeds and launch rail angles Optimal ballast: 3.65 kg All ballast placed at bottom of motor bulkhead gives initial static margin = 1.17 If 0.8 kg of ballast is moved to sabot, static margin = 1.56

15 Rocket Recovery System 3 ft drogue parachute Deployment at apogee Shear 4x 2-56 screws 2.1 g black power charge 9 ft main parachute Deployment at 2500 feet Deployed by sabot Sabot released by charge released locking mechanism

16 Rocket Recovery System Testing Barometric testing Deployment sensing Altitude verification Nose cone release Shear pin failure force Black powder charge Separation distance Charge release locking mechanism Black powder charge Operational verification Locating components Finding emergency locator transmitter

17 UAV Deployment Sabot safely stores UAV during flight Opened by wings unfolding Charge released locking mechanism - releases sabot at 2500 ft UAV oriented nose down inside rocket Autopilot brings UAV into level flight from dive Chute Bag delays opening of main chute Separation of rocket and nose cone prevents UAV entanglement Main Chute Deployment Bag Sabot Drogue Chute Broken Charge Released Locking Mechanism Sabot

18 UAV Deployment Testing After UAV has passed flight testing and gains have been adjusted Electronics unnecessary to testing deployment capability and glide control replaced by ballast Drop Testing Rig 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

19 Avionics and Communication There are four communication streams: Three associated with the UAV One associated with the Rocket UAV communication streams: 72MHz back-up UAV controls 900MHz command uplink / telemetry downlink 2.4GHz Real time video downlink Rocket communication stream: 900MHz telemetry downlink NOTE: the rocket and UAV telemetry downlinks shall be on different channels within the 900MHz band

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

21 Schedule Key Rocket Dates 9/10 Project initiation 11/19 PDR materials due 12/30 Scaled test launch 1/24 CDR materials due 2/20 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

22 Educational Outreach Boston Museum of Science Mid-January MIT Museum: Mid-January MIT Splash Weekend: 21 November MIT Spark Weekend: Mid-March

23 BACK UP SLIDES

24 Flight Computer UVI Sensor Board UVI2-R1-A Humidity/ Temperature/ Solar Board HTS3-R1-A GPS Receiver GS407 U-Blox5 Pressure UVI Temperature Pressure Sensor Board SCP1000 Breakout Humidity Temperature, Solar Flight Computer ArduPilot Mega Position Velocity Inertia Measuring Unit Oilpan Position Humidity, Position, Solar UVI, Temperature, Pressure 16Mb Flash Memory 900MHz Transmitter Internal to ArduPilot Mega Humidity UVI Temperature Solar Pressure Position Xbee Pro 900 Humidity, Position, Solar UVI, Temperature, Pressure

25 Ancillary Boards C-MOS Camera CM-26P Video Data 2.4GHz Transmitter AVS KX171-G2 Video Data Humidity, UVI Temperature Solar, Pressure UVI Sensor Board UVI2-R1-A Humidity/ Temperature/ Solar Board HTS3-R1-A Back-Up Dataloop Board Arduino Uno Micro SD Card Via DOSonCHIP FAT16 FAT32 usd Module Pressure UVI TemperatureHumidity Temperature, Solar Pressure Sensor Board SCP1000 Breakout

26 Rocket Avionics Communication Rocket Telemetr y 900MHz

27 UAV Avionics Communication UAV Controls 72MHZ Comman d/ Telemetry 900MHz Real Time Video 2.4GHz Altitude Velocity Land Here Go Here Temperature UVI Pressure Solar Capture Still