Transcript Document

Rocket Based Deployable Data Network
University of New Hampshire Rocket Cats
Collin Huston, Brian Gray, Joe Paulo, Shane Hedlund,
Sheldon McKinley, Fred Meissner, Cameron Borgal
2012-2013 Preliminary Design Report
Submission Deadline: October 29, 2012
Overview
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Objective
Vehicle Design
Materials and Justification
Vehicle Safety
Major Components
Recovery Design
Payload Design
Objective
• The UNH Rocket Cats aim to create a Rocket
Based Deployable Data Network (RBDDN). The
objective is to design a low cost data network
that can be deployed rapidly over a large area
utilizing rockets.
Vehicle Design
Vehicle Dimensions
• 67.75” in length
• 4.014” Outer Diameter
• 10.014” Span Diameter
Materials & Justification
Component
Material
Justification
Nose Cone
 PNC-3.9 Plastic
Nose Cone
 16.75” length
 3” Collar
 Easily
manufactured
 Designed to
contain
electronics bay
Vehicle
 4” Blue Tube
 51” length
 Strength
 Impact
Resistance
 Cost
Bulkheads
 Fiberglass
 Rigidity
 Strength
Motor Mount
 Fiberglass
 Rigidity
 Strength
Fins
 Fiberglass
 Rigidity
 Strength
Stability Margin
• Static Stability Margin
– 1.528
• Center of Pressure
– 48.321” from the nose tip
• Center of Gravity
– 42.211” from the nose tip
Vehicle Safety
• Equipment Concerns:
– Black Powder
– Hazardous Materials
– Motor
• Precautions:
– Refer to Material Safety Data Sheet (MSDS) for
related material
– Mentor and safety officer on site for supervision
Motor Safety
• Pre-Launch
– Appropriate motor selection
– Full inspection of motor assembly and
compartment
– Safe distance before launch
• Post-Launch
– Allow motor to cool before handling
Motor Selection
• Cesaroni Technology Inc. K400-GR-13 Reloadable Motor
• Total Length: 15.9 in
• Diameter: 2.13 in
• Launch Mass: 54.7 oz
• Total Impulse: 1595 Ns
• Average Thrust: 399 N
• Maximum Thrust: 475 N
• Burn Time: 4 s
• Thrust to weight ratio: 5.9:1
• Exit Rail Velocity: 55.5 ft/s
Motor Justification
• The primary reasoning for this motor choice is
to reach the 1 mile apogee goal
• Sufficient thrust to achieve safe rail exit
velocity
• Iterative approach to select motor based on
OpenRocket simulations
• The size of the motor fits very well in our
vehicle design
Launch Vehicle Verification and Test
Plan Overview
• Verification of Vehicle Components
– Perform tensile testing on all the load bearing
portions of the recovery system
– Perform compression testing on the tubing and all
other necessary portions of the vehicle
• Conducting planned test launches
– To ensure payload electronics are working
– Parachutes deploy properly
– Sustains stable flight
Recovery Subsystem
3 Event Recovery System:
• Drogue parachute deployment
at apogee
• Payload deployment at Range
Safety Officer announcement
• Main parachute deployment
at 700ft
Vehicle Recovery System
• Fully redundant recovery circuit
• #4-40 nylon screws for shear pins
• Black powder charges for
separation
Component
Part Choice
Altimeter
ADEPT22
Drogue Parachute
Public Missile Works
PAR-30
Main Parachute
Sky Angle Classic 36
Electric Matches
RocketFlite MF-12
Payload Recovery System
• Ejection charge initiated by
signal from ground station
• Nose cone separates and lands
independently with PAR-24
parachute
• Utilize one way bulkhead to
ensure that vehicle recovery
system is not compromised
One Way Bulkhead
• Ejection charges will
remove bulkhead from
only one direction
• Shear pins to hold in
bulkhead
Payload Design
• Primary Payload
– Raspberry Pi
– Sensor Suite (coincides with SMD)
– GPS
– XBee Pro 900
• Secondary Payload
– Raspberry Pi
– GPS
– Xbee Pro 900
Payload Design
Payload Design
Payload Verification
• Power: Payloads will require power for a
minimum of 2.5 hours. Our goal will be to have
enough power for 5 hours. The amount of
required power will be calculated and tested
• Data Acquisition: Testing will be done by
collecting data from all sensors and analyzing the
results
• Network: Both payloads will be tested by being
able to successfully communicate with each other
Payload Verification
• Data storage: Payloads will be given data to store
over the network. Successful storage will be
tested
• Location tracking: Payloads will have a GPS
module. Correct location data will be tested
• Network Range: Payloads will be required to be
able to communicate and maintain a network at a
distance of 1 mile. Our goal of 2 miles will be
tested with a clear line of sight for 2 miles and
analyzing signal loss