MSD I TEAM PROJECT 16250 REV. B S ELF -P OWERED A UTONOMOUS A QUATIC V EHICLE (SPAAV)
A utonomous H elicopter N avigation S ystem 2010
description
Transcript of A utonomous H elicopter N avigation S ystem 2010
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AUTONOMOUS HELICOPTER NAVIGATION SYSTEM 2010
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AHNS Project Aim
The Autonomous Helicopter Navigation System 2010 is focused on developing a helicopter system capable of autonomous control, navigation and localising within a GPS denied environment.
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Contents
Overview of the Project Airframe and Hardware On-board Flight Computer State Estimation Ground Control Station Control Architecture Hardware Mounting System Project Summery
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PROJECT OVERVIEWMichael Hamilton- 06219314
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High Level Objectives
Michael Hamilton- 06219314
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High Level Objectives
A platform should be developed and maintained to facilitate flight and on board hardware integration.
Michael Hamilton- 06219314
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High Level Objectives
The system should be capable of determining its position with the aid of image processing within an indoor environment to an appropriate time resolution.
Michael Hamilton- 06219314
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High Level Objectives
A method of estimating the states of the helicopter system should be designed and implemented. The resolution of the estimations should facilitate their employment in the control system design.
Michael Hamilton- 06219314
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High Level Objectives
An autopilot system should be developed to enable sustained indoor autonomous hovering flight. The control system should be designed to enable future ingress and egress manoeuvre to longitudinal and hovering flight.
Michael Hamilton- 06219314
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High Level Objectives
A ground control station that supports appropriate command and system setting inputs and data display and logging should be developed. The design should be derived from previous AHNS developments and enable future ground station developments.
Michael Hamilton- 06219314
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Project Virtual Demonstration
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Systems Engineering Approach
Michael Hamilton- 06219314
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Work Breakdown Structure
High Level Objective Document
WP-SY-01
System Requirements Document
WP-SY-02
Project Management Plan Document
WP-SY-03
Airframe Trade Study
WP-PL-01
Flight Computer Trade StudyWP-AP-01
Preliminary Design Document
WP-SY-04
Acquire & Construct Airframe
WP-PL-02
Acquire Flight ComputerWP-AP-02
Acquire Camera
WP-LO-01
Acquire Platform ElectronicsWP-PL-03
Camera Bench Test ReportWP-LO-02
Design Computer Vision System
WP-LO-03
Airframe RC Test Report
WP-PL-04
Flight Computer Bench Test Report
WP-AP-04
Design Control System
WP-AP-03
Electronics Test Report
WP-PL-05
Integrate Computer Vision with Camera HardwareWP-LO-04
Design Ground Control Station
WP-CG-01
Design State EstimationWP-SE-01
Design Wireless Communications
WP-CO-01
Integrate Onboard Hardware into Enclosure
WP-PL-06
Integrate Electronics Enclosure onto Airframe
WP-PL-07
Wireless Communications Test Report
WP-CO-02
Augmented Flight Test Report
WP-SY-05
Station Keeping Test Report
WP-SY-06
Ground Control Station Test Report
WP-CG-02
Complete all Test Reports
WP-SY-07
Complete Operation Manuel
WP-SY-08
Verification of Success
WP-SY-09
Demonstration
WP-SY-10
Presentation
WP-SY-11
Traceability Matrix
WP-SY-12
High Level Objective Document
WP-SY-01
System Requirements Document
WP-SY-02
Project Management Plan Document
WP-SY-03
Airframe Trade Study
WP-PL-01
Flight Computer Trade StudyWP-AP-01
Preliminary Design Document
WP-SY-04
Acquire & Construct Airframe
WP-PL-02
Acquire Flight ComputerWP-AP-02
Acquire Camera
WP-LO-01
Acquire Platform ElectronicsWP-PL-03
Camera Bench Test ReportWP-LO-02
Design Computer Vision System
WP-LO-03
Airframe RC Test Report
WP-PL-04
Flight Computer Bench Test Report
WP-AP-04
Design Control System
WP-AP-03
Electronics Test Report
WP-PL-05
Integrate Computer Vision with Camera HardwareWP-LO-04
Design Ground Control Station
WP-CG-01
Design State EstimationWP-SE-01
Design Wireless Communications
WP-CO-01
Integrate Onboard Hardware into Enclosure
WP-PL-06
Integrate Electronics Enclosure onto Airframe
WP-PL-07
Wireless Communications Test Report
WP-CO-02
Augmented Flight Test Report
WP-SY-05
Station Keeping Test Report
WP-SY-06
Ground Control Station Test Report
WP-CG-02
Complete all Test Reports
WP-SY-07
Complete Operation Manuel
WP-SY-08
Verification of Success
WP-SY-09
Demonstration
WP-SY-10
Presentation
WP-SY-11
Traceability Matrix
WP-SY-12
STAGE 1: Definition and ResearchSTAGE 2: Design and DevelopmentSTAGE 3: Component Testing
STAGE 4: Integration and Testing
STAGE 5: Deliverables
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Risk Management Risk Management Plan developed mid-
semester one. After the 3rd year Quadrotor incident, all
university engine testing banned indefinitely.
After approval from ARCAA H&S staff, testing continued at Airport hanger.
Michael Hamilton- 06219314
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PLATFORM | PILOTMichael Kincel - 06219322
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Airframe Power System
Electronics Mounting System
Platform
Michael Kincel- 06219322
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HLO-1 Platform
SR-B-01
Manual RC
Control
Perform RC Test Flight
SR-D-01400
Gram Payload
Develop Suitable Airframe
SR-D-02Maintenan
ce Document
Platform
Michael Kincel- 06219322
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Airframe Power System
Electronics Mounting System
Platform
Michael Kincel- 06219322
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Airframe
MikroKopter MK40 Readily Available Lightweight Durabiltiy Fulfils Payload Requirements
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Power System
Electronics Mounting System
Platform
Airframe
Michael Kincel- 06219322
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Power System
Vin
5V
GND
LF50A
220uF
ESC 1
Vin
GND
5V
LF50A
Vin
5V
GND
LF50A
220uF
ESC 2
Vin
GND
5V
LF50A
Vin
5V
GND
LF50A
220uF
ESC 3
Vin
GND
5V
LF50A
Vin
5V
GND
LF50A
220uF
ESC 4
Vin
GND
5V
LF50A
12V
Vin
GND
Autopilot100uF
Michael Kincel- 06219322
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Electronics Mounting System
Platform
Airframe Power System
Michael Kincel- 06219322
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Electronics
UART1
USB
UART2
FlightComputerUART
PWM
Input Capture
ModeControl
Unit
UART
InertialMeasurement
Unit
USB
ADC0
UART4
UART3
ADC1
ArduinoNano
PWM
RCReceiver
Signal Input
4x ESCs
UART
MagneticCompass
UART
Camera
Analogue Output
UltrasonicAltimeter
Analogue Output
BatteryVoltage
Ground Station/Vicon
WiF
i
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Michael Kincel- 06219322
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Acceptance Testing
HLO-1 Platform
SR-B-01
Manual RC
Control
AT-01
SR-D-01400
Gram Payload
AT-11
SR-D-02Maintenan
ce Document
AT-12
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Lessons Learnt
Scope Use commercial hardware if navigation is
desired Hardware Development
Minimum of two people developing hardware
Devote more time to hardware development
Dedicated project
Michael Kincel- 06219322
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FLIGHT COMPUTER (FC)Liam O’Sullivan - 06308627
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Flight Computer27
HLO-4 Autonomous Hovering Flight
SR-D-05 and 06
Receive and process
sensor data (50 Hz)
IMUCompassUltrasonic
MCUBattery voltage
Liam O’Sullivan - 06308627
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FC Design (Hardware)
Implemented on the Gumstix Overo FireSpecification
Overo Fire
Processor ARM Cortex-A8 OMAP3530Clock speed
720 MHz
Memory 256MB RAM / 256MB FlashWeight 5.6gSize 17mm x 58mm x 4.2mm Wireless Connectivity
• Bluetooth• WiFi
Features • I2C• PWM (6)• A/D(6)• UART• USB host
Overo Fire
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FC Design (Software Architecture)
Use this text format...Flight Computer (Overo Fire)
Control Thread Retrieve state data Compute control law inputs Calculate engine output pulse
widths
Downlink Thread Handle UDP client connections Transmit sensor and state data Receive updated control parameters
State Estimation Thread Read raw sensor data Compute state estimation
through filters
Actuators MCU Transmit data to
ESCs
Arduino Thread Read raw sensor data from
Arduino
MCU Thread Send data to MCU Handle RC commands
Overo Sensor IMU
Arduino Sensors Ultrasonic Compass Battery voltage
FC Software Architecture Liam O’Sullivan - 06308627
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HLO-4 Autonomous Hovering Flight
SR-D-05 and 06
Receive and process
sensor data (50 Hz)
AT-15
Collected compass, IMU, ultrasonic data
Processed at 50Hz
AT-16
Collected battery
voltage, flight status
Processed at 50Hz
FC Acceptance Testing
Liam O’Sullivan - 06308627
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STATE ESTIMATION (SE)Liam O’Sullivan - 06308627
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State Estimation32
HLO-3 State Estimation
SR-B-05Altitude
estimate at 50Hz
ViconUltrasonic
sensor
SR-B-06X and Y
estimate at 50Hz
Vicon
SR-B-04Attitude
estimate at 50Hz
IMUCompassKalman Filtering
Liam O’Sullivan - 06308627
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SE Design
15 states to be measuredState Sensor State SensorRoll rate X rate gyro (IMU) Z acceleration Z accelerometer
(IMU)Pitch rate Y rate gyro (IMU) X velocity Vicon*Yaw rate Z rate gyro (IMU) Y velocity Vicon*Roll IMU* Z velocity Ultrasonic and
Vicon*Pitch IMU* X
displacement Vicon
Yaw IMU* and compass Y displacement
Vicon
X acceleration X accelerometer (IMU)
Z displacement
Ultrasonic and Vicon
Y acceleration Y accelerometer (IMU)
x
y
z
x
y
z
x
y
z
* indirect measurement
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SE Design (Position and Velocity)
Vicon motion capture system External motion capture system Measures object translation and
rotation with sub mm accuracy 200Hz update rate Ethernet connection (via GCS) Located at the ARCAA building
Vicon IR camera
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SE Design (Attitude)
Attitude estimated by 3 Kalman Filters (KF)
1 KF for each Euler angle IMU rate data (Time Update) IMU acc data (Measurement Update) Compass data (Ψ Measurement Update)
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SE Design (Attitude)
Example: Estimating φ via KF
Liam O’Sullivan - 06308627
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SE Testing Outcomes (Attitude)
IMU mounting error in both φ (-1.4°) and θ (-1.2°)
Liam O’Sullivan - 06308627
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SE Testing Outcomes (Attitude)
Accelerometer low pass filtering
Liam O’Sullivan - 06308627
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SE Acceptance Testing39
HLO-3 State Estimation
SR-B-05Altitude
estimate at 50Hz
AT-05
Estimated Z position with
Vicon50Hz update
SR-B-06X and Y
estimate at 50Hz
AT-06
Estimated X and Y position
with Vicon50Hz update
SR-B-04Attitude
estimate at 50Hz
AT-07
Estimated Euler angles
with IMU50Hz update
Liam O’Sullivan - 06308627
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Lessons Learnt
Flight computer Too much operating system overhead
State estimation Accelerometer data needs filtering Ψ requires KF bound checking Difficult to design visual control within a
year (without a platform)
Liam O’Sullivan - 06308627
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GROUND CONTROL STATIONFLIGHT CONTROLTim Molloy - 06332064
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Ground Control Station42
HLO-5 Ground Control Station
SR-B-02Flight Mode Switching
Flight Control Widget
SR-B-08 and 09
Receive and Transmit
Telemetry via WLAN
Communications and Vicon
Threads; Gains and Parameter
Widgets
SR-D-07 and 08
Log Telemetry and Uplink Commands
Received and Transmit
Consoles and Data Logger
SR-D-09Display of State
and Control Data
Data Plotters & Artificial Horizon
SR-D-10System Status
Display
System Status Widget
06332064 Tim Molloy
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GCS Design (Architecture)
06332064 Tim Molloy
Ground Control Station Software - Ubuntu
Telemetry Thread Connect to UDP Server Receive Telemetry Data Transmit uplink data
GCS Thread Run GCS GUI Change Flight Modes Change Control Settings Display received telemetry data Log Data
Data Logging
802.
11 N
e tw
o rk
Signals/Slots
Vicon Thread Receive Vicon Data Forward Vicon Data
Signals/Slots
Net
wor
k
Signals/Slots
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GCS Implementation (User Interface)
06332064 Tim Molloy
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HLO-5 Ground Control Station
SR-B-02Flight Mode Switching
AT-02
SR-B-09 and 08
Receive and Transmit
Telemetry via WLAN
AT-08 AT-09
SR-D-07 and 08
Log Telemetry and Uplink Commands
AT-17 and AT-18
SR-D-09Display of State and
Control Data
AT-19
SR-D-10System Status
Display
AT-20
GCS Acceptance Testing
06332064 Tim Molloy
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Flight Control46
HLO-4 Autonomous Hovering Flight
SR-B-10PID Control Methodolog
y
Control Architecture
SR-D-03Stability
Augmented Flight
Attitude Control
Static Angle Setpoints
Dynamic Angle
Setpoints
Dynamic Angular Rate
Setpoints
SR-B-0350Hz Control
Rate
Control and Mode Control
Unit Flight Computer
Update Rate
SR-D-04Autonomous
Station-keeping
Guidance
06332064 Tim Molloy
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06332064 Tim Molloy
Flight Control (System Architecture)
Attitude Control
Position Control
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Angle Based Attitude Control
96 97 98 99 100 101 102
-20
0
20
40
60Angle Control : IMG0059 Angle Controller Oscillations
Pitc
h A
ngle
[d
eg]
ref
96 97 98 99 100 101 102
-20
0
20
40
60
Time t [sec]
Rol
l Ang
le
[deg
]
ref
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Dynamic Rate Based Attitude Control
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Altitude Control
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Flight Control Acceptance Testing
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06332064 Tim Molloy
HLO-4 Autonomous Hovering Flight
SR-B-10PID Control Methodolog
y
AT-10
SR-D-03Stability
Augmented Flight
AT-13
SR-B-0350Hz Control
Rate
AT-03
SR-D-04Autonomous
Station-keeping
AT-14
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Lessons Learnt GCS
Emphasis on modular design, unit testing and documentation tools to maximise code reuse
Avoidance of “from scratch” development
Control Separation of State Estimation and Controller Testing Reliance on controller designs based on proven
implementations rather than simulations Limitations on use of testing apparatus to mitigate
risks Effects of PWM resolutions on control performance Avoidance of USART Update Limitations in Control
06332064 Tim Molloy
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HARDWARE MOUNTINGMichael Hamilton- 06219314
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Hardware Mounting System
The design will protect the electronic equipment from striking the ground or other parts of the airframe in the event of a crash.
The frame that supports the equipment will be made of a material that will snap under a large instant force, such as a crash, to prevent this shock damaging the main electronics board or airframe.
The mounting system will be easy and cheap to manufacture, and within a local area to reduce delivery time.
Allow easy access to electronics and line of sight to all LED’s.
Michael Hamilton- 06219314
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Michael Hamilton- 06219314
Initial DesignMichael Hamilton- 06219314
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Michael Hamilton- 06219314
Final DesignMichael Hamilton- 06219314
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PROJECT SUMMERYMichael Hamilton- 06219314
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Finial BudgetCompany Items Description Debit Credit Total
QUT BEE Unit Funds $0.00 $400.00 $400.00
Boeing Boeing Sponsership $0.00 $2000.00 $2400.00
HiSystems GmBH Quad Copter Airframe $759.86 $0.00 $1640.14
Surveyor Corporation Camera $248.75 $0.00 $1391.39
Gumstix inc Onboard Computer $395.92 $0.00 $995.47
HobbyRama V-Tail Mixer $82.00 $0.00 $913.47
Bunning’s Warehouse Glue $16.03 $0.00 $897.44
Eckersley Wiring Equipment $29.95 $0.00 $867.49
QUT Bookshop Writing Material $5.70 $0.00 $861.79
Jaycar Autralia Cable $10.67 $0.00 $851.12
RS Components Coolum Counter $37.07 $0.00 $814.05
Farnel Electrical Parts $138.33 $0.00 $675.72
H.E.Supplies Pty Ltd Metal Components $44.85 $0.00 $630.87
New Generation Hobbies
Motors $221.55 $0.00 $409.32
HobbyKing ESC $100.53 $0.00 $308.79
Total Remaining
$308.79
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Conformance MatrixNumber
Definition Status Reference Document
SR-B-01 The platform shall have the ability to be manually manoeuvred with a radio controller.
Complete
AHNS-2010-PL-TR-002
SR-B-02 The GCS shall enable autopilot flight mode switching between manual, stability augmented flight, and autonomous station keeping.
Complete
AHNS-2010-GC-TR-001
SR-B-03 The airborne system shall provide control updates at an average rate of 50Hz.
Complete
AHNS-2010-AP-TR-001
SR-B-04 The estimator shall provide Euler angle and rate estimation for the system an average rate of 50 Hz.
Complete
AHNS-2010-SE-TR-001
SR-B-05 The estimator shall provide altitude estimation for the system an average rate of 50 Hz.
Complete
AHNS-2010-SE-TR-001
SR-B-06 The estimator shall provide x and y estimation in an Earth fixed co-ordinate system an average rate of 50 Hz.
Complete
AHNS-2010-SE-TR-002
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Conformance MatrixNumber
Definition Status Reference Document
SR-B-07 The system shall use image processing to aid in state estimation of x and y in an Earth fixed co-ordinate system.
Not Complete
No Document
SR-B-08 The autopilot system gain and reference parameters shall be updatable in flight using an 802.11g WLAN uplink from the GCS.
Complete
AHNS-2010-GC-TR-001
SR-B-09 The airborne system shall transmit telemetry data including state data to the GCS using 802.11g WLAN.
Complete
AHNS-2010-AP-TR-002
SR-B-10 The autopilot control methodology shall be based on cascaded PID control loops.
Complete
AHNS-2010-AP-DD-001
SR-D-01 The platform shall be capable of maintaining controlled flight with a total payload of 400 grams.
Complete
AHNS-2010-PL-TR-002
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Conformance MatrixNumber
Definition Status Reference Document
SR-D-02 A maintenance document shall be used to log airframe flight time, battery cycles and aircraft repairs.
Complete
AHNS-2010-PL-TR-001
SR-D-03 The autopilot shall provide stability augmented flight.
Complete
AHNS-2010-SY-TR-001AHNS-2010-SY-TR-002
SR-D-04 The autopilot shall provide autonomous station keeping capability within a 1 meter cubed volume of a desired position.
Not Complete
AHNS-2010-SY-TR-003AHNS-2010-SY-TR-004
SR-D-05 The airborne system shall receive and process measurement data from the state estimation and localisation sensors; supporting IMU, Camera, and Ultrasonic sensor.
Complete
AHNS-2010-AP-TR-002
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Conformance MatrixNumber
Definition Status Reference Document
SR-D-06 The airborne system shall collect avionics system health monitoring information in the form of radio control link status, flight mode status and battery level.
Complete
AHNS-2010-AP-TR-002
SR-D-07 The airborne system shall collect avionics system health monitoring information in the form of radio control link status, flight mode status and battery level.
Complete
AHNS-2010-AP-TR-002
SR-D-08 The GCS shall log all telemetry and uplink data communications.
Complete
AHNS-2010-GC-TR-001
SR-D-09 The airborne system shall receive and process measurement data from the state estimation and localisation sensors; supporting IMU, Camera, and Ultrasonic sensor.
Complete
AHNS-2010-GC-TR-001
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Conformance MatrixNumber
Definition Status Reference Document
SR-D-10 The GCS shall provide display of avionics system health monitoring including telemetry, uplink, radio control link and battery level status read-outs.
Complete
AHNS-2010-GC-TR-001
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Conformance Diagram66
HLO 1
SR-B-01
SR-D-01
SR-D-02
HLO 2
SR-B-07
HLO 3
SR-B-04
SR-B-05
SR-B-6
HLO 4
SR-B-03
SR-B-10
SR-D-03
SR-D-04
HLO 5
SR-B-02
SR-B-08
SR-B-09
SR-D-05
SR-D-06
SR-D-07
SR-D-08
SR-D-09
SR-D-10
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Conformance Diagram67
HLO 1
SR-B-01
SR-D-01
SR-D-02
HLO 2
SR-B-07
HLO 3
SR-B-04
SR-B-05
SR-B-6
HLO 4
SR-B-03
SR-B-10
SR-D-03
SR-D-04
HLO 5
SR-B-02
SR-B-08
SR-B-09
SR-D-05
SR-D-06
SR-D-07
SR-D-08
SR-D-09
SR-D-10
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Conformance Diagram68
HLO 1
SR-B-01
SR-D-01
SR-D-02
HLO 2
SR-B-07
HLO 3
SR-B-04
SR-B-05
SR-B-6
HLO 4
SR-B-03
SR-B-10
SR-D-03
SR-D-04
HLO 5
SR-B-02
SR-B-08
SR-B-09
SR-D-05
SR-D-06
SR-D-07
SR-D-08
SR-D-09
SR-D-10
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Project Summary Designed and constructed a platform to
facilitate flight utilising on board hardware and sensors.
Implemented State Estimation and PID control to enable autonomous flight.
Coded functional ground control station with 2.4 GHz wireless communication to platform.
Tuned gains for stable platform attitude while in flight.
Enabled future development on project to achieve position hold.
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Lessons Learnt System requirements and preliminary designs defined early. Work breakdown structure organised into large overall tasks, as the
project aims, designs and methods will change during the semester. The testing phase of the project should commence at the beginning
of semester two, as the AHNS project requires a lot of time for calibrating the system for flight conditions.
Organise the project time schedule to incorporate other subject assignment due dates, as project productivity was found to drop significantly during this time.
The risk management plan must be completed and approved well before testing commences, and ensure that all possible testing locations has been authorised.
Due to batteries requiring four times longer recharging that the flight time they produce, ensure a large number are available for flight-testing.
Purchase additional electrical hardware components to mitigate schedule delay from broken parts after flight crashes.
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SYSTEM DEMONSTRATION
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QUESTIONS?
MICHAEL HAMILTON - 06219314 MICHAEL KINCEL - 06219322
TIM MOLLOY - 06332064 LIAM O’SULLIVAN - 06308627