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