Transcript Preliminary Design Review - University of North Dakota

PRELIMINARY DESIGN REVIEW
University of North Dakota
Frozen Fury Rockety Team
DIMENSIONS
Vehicle
 Length: 114 in. / 9.5 ft.
 Diameter: 6.0 in.
 Span: 12.0 in.
 Unloaded mass:
900.9002 oz.
Fin Dimensions
 Root: 20.0 in.
 Tip: 12.0 in.
 Sweep length: 0 in.
 Semi Span: 6.0 in.
VEHICLE MATERIALS & JUSTIFICATIONS

Airframe:
Carbon fiber
 Superior strength to weight ratio
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Fin
Birch plywood in carbon fiber
 Past experience with
 Combined materials provide a strong, rigid fin
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Bulk-Head / Centering-Ring
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Birch plywood
Locally available, cabinet quality grain with few
knots
STATIC STABILITY MARGIN
CP 77.6030 in
 CG 59.9158 in
 Safety Margin 2.96
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PLAN FOR VEHICLE SAFETY
VERIFICATION AND TESTING
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Flight Simulation in RockSim
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Verify that vehicle descends at safe velocity for recovery
Recovery Subsystem:
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Altimeters
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Vacuum testing - pressure changes trigger altimeter
activity
Black powder ejection charges
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Parachute Deployment
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Will ensure we have enough force to separate rocket safely through
various conditions
Especially for drogue parachute after payload integration
Testing of Batteries and Cameras
Payload Testing and Confirmation
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Camera, Wiring, Storage Device, & Camera Mounts
Stability after payload integration
BASELINE MOTOR SELECTION AND
JUSTIFICATION
Motor
 Aerotech L2200G.

This motor type is still under discussion due to the
payload component weights being unknown
Altitude: 5076.35 ft. ± 3.00%
 Diameter: 75 mm.
 Length: 665 mm.
 Burn: 2.40 sec.
 Thrust: 2104.9852 N.
 Impulse: 5051.9644 N*Sec.
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THRUST-TO-WEIGHT RATIO AND RAIL
EXIT VELOCITY
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Thrust-to-Weight Ratio:
Rail Exit Velocity:
LAUNCH VEHICLE VERIFICATION AND
TEST PLAN OVERVIEW
Sub-scale
 Construction: Now – Jan. 25
 Launch: Jan. 26 – 31
Full-scale
 Construction: Jan 26 – Feb. 15
 Test flight #1: Feb. 16 - 28
 Test flight #2: Mar. 12 – 29
 Final launch: May 17 – 18
RECOVERY SUBSYSTEM
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Our recovery system consist of
altimeters, ejection charges, and
parachutes.
The parachutes are attached to
nylon shock chord with D-rings.
Black powder charges will go off
based on the altimeter readings.
Drogue parachute:

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36 in.
Deploy 5 seconds after apogee
Descend at a velocity of 49.9 ft./sec.
Main parachute:
72 in.
 Deploy at 700 ft.
 Descent rate of 23.4 ft./sec.

BASELINE PAYLOAD DESIGN
Hazard Detection Payload (3.1)
 Payload Faring/Deployment System (3.2.2.1)
 Liquid Sloshing Analysis Payload (3.2.1.2)

HAZARD DETECTION PAYLOAD (3.1)
Purpose: to scan the ground during decent and
relay any landing hazards, in real time, to a
ground station.
 Consist of a camera and the necessary
electronics.
 Major challenges:

Creating a 2-way communications system for the
rocket.
 Limited video storage.
 Viewing video from cameras near real-time from a
ground station.

PAYLOAD FARING/DEPLOYMENT
SYSTEM (3.2.2.1)
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Purpose: to deploy the Hazard Detection Payload
Consist of an altered nose cone and mechanical separation system
Nose cone:
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Cut into two pieces that will be friction fitted together.
Each half will be attached to the body tube with hinges.
Mechanical cone separation system:
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Separates the nose cone halves when the drogue chute is deployed
Consist of a tether:
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one end attached to the drogue chute
the other to a screw that will have levers with a gear on one end.
Initially the levers will be orientated towards the base corners of the nose
cone.
After drogue is deployed, the tether will pull on the screw causing the
levers to expand and separate the two halves of the nose cone.
To prevent the halves from interfering with the camera, the hinges
attaching the nose cone halves will lock once the halves are out of
the cameras viewing area.
Major Challenges:


Drogue chute fails to exert enough force on the levers.
Failure of cones separation will cause hinges to not lock.
LIQUID SLOSHING ANALYSIS PAYLOAD
(3.2.1.2)
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Purpose: research liquid sloshing in microgravity to support liquid
propulsion system upgrades and development.
Experiment will be done through a partitioned tank.
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Liquid in one half cylinder is allowed to move freely
Liquid in the other half cylinder will be controlled by a low pressure
piston.
Four cameras used to collect data:
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Each tank will be filmed by two cameras.
Two cameras are positioned along the body tube 180° from each other.
Another two are positioned on the top of one tank, and the bottom of
the other
Top choice for camera: GoPro HD Hero 960 helmet camera
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The data from the cameras will be stored onboard.
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60 frames per sec, 848x480 resolution.
Analyzed post flight.
Major challenges:
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Developing the appropriate software to analyze the video taken by the
cameras
Ensuring the rocket remains balanced.
PAYLOAD VERIFICATION AND TEST PLAN
OVERVIEW

Hazard Detection Payload (3.1)
Require static ground tests to determine the abilities the
camera and software in identifying potential landing
hazards.
 Testing before and after payload integration to launch
vehicle.
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Payload Faring/Deployment System (3.2.2.1)
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The mechanical system will require static ground tests to
determine the force required to separate the nose cone.
Liquid Sloshing Analysis Payload (3.2.1.2)

Several dynamic ground tests to measure the liquid
sloshing patterns

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Allow us to determine liquid patterns in standard gravity.
Will use this data to compare with data collected in-flight.
ANY QUESTIONS?