Guidelines for Technical Communication
D/SE and D/CME
United States Military Academy
Soldier Problem
Soldiers operating in dense urban environments will not be able to
use conventional avenues of approach and means of
reconnaissance due to future enemy capabilities.
Design Challenge
Develop a discrete, safe, and rapidly deployable breaching and
sUAS employment system for DARPA. This system should enhance
SquadX's situational awareness in dense urban environments under
the constraints associated with future enemy sensing and
weaponry.
Theater Study
• Researched wall types in predicted urban environments of
present and future areas of conflict
• Found that the typical wall is precast, non-structural, concrete
panels with Gr. 60 steel rebar (4000-5000 psi)
Concrete Behavior
• American Society of Civil Engineers guidelines used to predict
required forces for generating concrete failure.
• Guided anchor configuration and depth
• Predicted configuration highly accurate with final setup
Quad pod and Net Design
• Analyzed through finite element analysis to ensure success.
• Designed using computer aided design software and then
fabricated in shops
Breach Boys
Team Members: Cadets Aaron Finch, Brandon Shively, Marco Amalfitano, John Kelly, Blake Sandlin, Frank Wu
Sponsors: DARPA, LTC Philip Root, Dr. Scott Fish
Faculty Advisors: LTC Brian Novoselich, CPT Claude Barron, COL Ricardo Morales
Soldier Problem and Design Challenge Solution Design
Testing Results
Design Process
Design Merits
Solution Concept
Concrete is drastically weaker in tension than any other type of
loading. By loading the concrete in shear and tension we can
compromise the wall. Temporary concrete anchors allow a hydraulic
ram to impart force and generate failure. A breach allows UAS
deployment to further squad awareness.
Breach Process
• Drill four strategically spaced holes
• Place temporary concrete anchors in
• Utilize hydraulic ram mounted on
quadpod to generate force until
concrete fails
• Use chisel bit to remove material
• Deploy drone through breach using
sUAS deployment/retrieval device
Components
Figure 4: An example test showing the initial hole spacing, the breach
progress after one iteration and the breach after two iterations
• Generated five successful breaches throughout testing
• Generated a maximum breach size of 7 by 5 inches
• Employed system, from entering area to deploying drone, within 18
minutes
• Total current weight is 87 pounds
• Emissions averaged 1.9 𝑥 10
−5
ppm (PM10) increase during breach
Innovation
Our design presents a novel form of mechanical breaching that
incorporates non-explosive and rapid breaching capabilities for future
“Squad-X.”
Feasibility
• Generates no hazard when operated in enclosed environments
• Generates less noise than current explosive or mechanical
breaching methods
• Breaches more rapidly than current mechanical breaching
methods
• System weight comparable to weight of current mechanical
breaching methods
Technical Strengths
This design has been grounded in ASCE concrete guidelines, finite
element analysis on both the quad-pod and employment-net systems,
mathematical modeling, and thorough testing.
Reduce time on target
• Utilize rotary hammer for removing slack in the system
• Determine most efficient anchor spacing and depth
• Possibly drill additional holes to decrease breach time
Develop multi-use capability
• Utilize anchors for urban rappelling
• Develop systems to breach other obstacles using force of the
hydraulic ram
• Integrate solution with other logistic systems, such as drone
resupply
LTC Philip Root, DARPA
Dr. Scott Fish, UT Austin
COL Christopher Kuhn, Ft Hood, TX
LTC Brian Novoselich
Figure 3: All components for the system. From left to right, rotary
hammer, hydraulic ram and pump, quadpod, temporary concrete
anchors and net design
Figure 2: breaching system
being employed
Acknowledgements
CPT Claude Barron
Mr. Roderick Wilson
Mr. Richard Ellingsen
Mr. William Blackmon
Figure 1: The Breach Boys, breaching kit and two test walls
Decrease System Weight
• Redesigned quadpod featuring lighter
material and a more efficient design
• More compact hydraulic ram
• Lighter Carrying system
Figure 5: Proposed future quadpod
design which will more than half the
current weight.
Future Improvements
(a) Team Breach Boys.
United States Military
Academy at West Point
Department of Civil and
Mechanical Engineering
Cadets David Bindon, Mattias Cooper, Benjamin Duhaime, and Robert Woodings
Advisors: Dr. David Helmer, CPT Briana Fisk, COL Michael Benson, COL Bret Van Poppel, Dr. Chris Elkins
Turbine Vane Cooling Analysis
Experimental Methods and Setup IR Results and Analysis
Magnetic Resonance Velocimetry (MRV)
Problem Statement
To design a rig (or rigs) to test and analyze velocity and heat transfer
characteristics of the Advanced Recirculation Total Impingement Cooling
(ARTIC) turbine vane insert for the Air Force Research Laboratories (AFRL) in
order to validate computational fluid dynamic (CFD) models.
Acknowledgements
Special thanks to Air Force Research Laboratory (AFRL), the Combat
Capabilities Development Command Armaments Center (CCDC AC),
Florida Turbine Technologies Engines Division (FTT), USMA Laboratory
Technicians, and the Richard M. Lucas Center for Imaging at Stanford
University for their funding, support, and assistance.
Steady-State Infrared Imaging (IR)
• Joule-heated, 0.
005” stainless steel
shim models turbine vane inner surface
• Imaged with FLIR A655SC IR camera
• Flow Rate: 408 L
/min (Re=10,000)
• Current and voltage measured
• 45% flow rate through tip bleed
Heat Transfer Rig and IR Camera
• Mapping 2D image to 3D
curve using fiducial marks
• Use characteristic heat
t
ransfer equations to analyze
performance: Nusselt
number and convection
coefficient
• Lowest rate of heat transfer
at jet interaction locations
Distribution A: Approved for public release; distribution is unlimited.
ARTIC Insert MRV Model IR Model
# Modules 23 5 5
Zone 1 (Z1):
X/D, Y/D, Z/D
4.6, 4.6, 3.0 4.6, 4.3, 3.0 4.6, 4.3, 3.0
Zone 2 (Z2):
X/D, Y/D, Z/D
3.9, 3.9, 3.0 4.0, 3.6, 3.0 4.0, 3.6, 3.0
Zone 3 (Z3):
X/D, Y/D, Z/D
9.1, 9.1, 3.0 9.1, 13.1, 3.0 9.1, 13.1, 3.0
# Holes (Z1, Z2, Z3) 30, 17, 9 21, 10, 7 21, 10, 7
Tip Bleed? No Yes Yes
Scale (Insert:Model) 1:1 1:6.67 1:4.67
Design Decisions
Summary of Model Design Decisions
Modeling and Manufacturing Processes
• Modeled stresses, deformation, and flow rate
to achieve desired Reynolds number
• SLA additive manufacturing at CCDC AC
• Material: A
ccura 60 SLA Resin
• Final machining performed at Stanford
MRV
• Modeled theoretical power to achieve
desired ∆T – or temperature difference
• SLA additive manufacturing at USMA
• Material: Form
labs SLA Resin
• USMA water jet cuts copper bus bars.
• Rig sealed with silicone sealant
• Stainless steel shim for HT test spray
pai
nted black to ensure near black
body emissivity
IR
MRV Rig and Supports
Conclusions
Proved in-house manufacturing capabilities
3D velocity field of intricate geometry
Characterized heat transfer performance
2D surface temperature profile
Inform turbomachinery component design
Synthesize MRV & IR data extensively
Investigate phenomenon of film cooling
Analyze high MRV case to validate CFD
Produced IR rig at USMA
MRV techniques employed
IR testing on inner vane surface
MRV & IR Combined
Future Work
From bottom, clockwise: Reservoir setup, MRV rig in
scanner, ARTIC insert produced from MRV data
High Case Low Case
Reynolds Number [ ] 20,000 10,000
Inlet Flow Rate
[L/min]
74.4 37.2
Tip Bleed Flow Rate
[L/min]
33.5 16.7
Resolution [mm] 0.8 0.8
Imaging Matrix Size 222x300x166 222x300x166
Encoded Velocity
[cm/s]
300 (X,Y);
380 (Z)
275 (X,Y,Z)
Total Scans [#] 12 12
Uncertainty ±5% ±5%
Flow and Testing Parameters Table
MRV Results and Analysis
• Robust, high-fidelity, 3D velocity data
• Minimal module-to-module variation
• Two flow cases contain significant differences
• Main feed cavity flow recirculates
• Further analysis can validate CFD
• Informs ARTIC design choices
Feed Cavity Profile,
Flow Moving Left to Right
Recirculation, Inlet Profile Jet-to-Jet Interaction in an Oblique Plane
Example Infrared Image, Zone 1
Temperature Plot [K], Zone 1
Nusselt Number Contour,
Zone 2
MRV Total Velocity,
Zone 2 Impingement Surface
MRV and IR data
show expected
similarity: increased
fluid velocity yields
increased heat
transfer rate!
Main Outlet
Fluid Reservoir 21ºC
Val ve
Cold Fluid
Reservoir
8ºC
Pump
Tip Bleed
Heat
Exchanger
MRV Experimental Setup Diagram
Inlet
Introduction and Motivation
2. Hence, the Advanced Recirculation
Total Impingement Cooling (ARTIC)
gas turbine vane insert to cool the vane.
3. A cooler turbine vane means higher
thermal efficiency, which increases
turbine lifespan, reduces emission
rates, lowers fuel consumption, and
saves money!
4. Fluid dynamics modeling of these
systems must be validated by physical
tests, like Magnetic Resonance
Velocimetry (MRV) or infrared (IR)
imaging.
1. Thermal
efficiency of
turbines
increases when
operating fluid is
at higher
temperatures. A
limiting factor:
vane melting
temperature.
Flow Path through
Forward Insert
Temperature vs. Efficiency for
Varying Gas Turbines
ǂ
ǂ Ibrahim, T. K., Basrawi, F., Rahman, M., 2016. “Optimum Performance Enhancing Strategies of the Gas Turbine Based on the Effective Temperatures”. In MATEC Web of Conferences 2016, p. 01002.
(b) Team Cool Vanes.
Figure 6: Example technical posters.
1.01a – 17 August 2020
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