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Wings Over the Rockies Air and Space Museum
The Titan IV Stage I rocket delivers 547,600 or 550,900 lb nominal vacuum thrust, depending upon the nozzle configuration. It is essentially two identical engines attached to a single steel frame which mounts onto the launch vehicle. These separate engines operate simultaneously under a single control system. The Stage I rocket engine consists of the following components and subsystems: pump suction (inlet) lines, turbopump assemblies, pump discharge lines, thrust chamber valves, gas generator systems, thrust chambers, autogenous pressurization system, control and instrumentation harnesses, and the engine frame.
The suction lines duct the Aerozine-50 fuel and nitrogen tetroxide oxidizer from the propellant tank lines to the turbopump assemblies, each of which is driven by a turbine rated at over 5000 h.p. The fluid pressure is increased by over 1000 psi, forcing the propellant into the thrust chamber. Thrust chamber valves control the engine start and shutdown. Gas generators are operated by propellant from the combustion chamber inlet lines, downstream of the valves, to drive the turbo pumps to maintain propellant flow. Combustion in the thrust chambers produces gas at pressures over 800 psia and temperatures above 5000° F. This gas is expanded through a convergent-divergent DeLaval design nozzle and exhausted at supersonic velocity to produce thrust.
Thrust vector control (pitch, yaw and roll) is achieved during Stage I flight by pivoting the thrust chambers independently on gimbal bearing mounts. The gimbal action is provided by hydraulic actuators which operate in response to signals from the launch vehicle guidance system.
System reliability is augmented through functional simplicity of design. The engine is hydraulically balanced, requiring no active control of thrust and mixture ratio. It is pre-set to consume propellant at a fixed rate and mixture ratio. Balance orifices in the propellant discharge lines fine tune the engine mixture ratio, controlling propellant flow to the gas generators, resulting in a stabilized turbine speed. Titan storable propellants are hypergolic, meaning they ignite upon contact. Therefore, an ignition system is not required to initiate combustion in the thrust chambers or gas generators.
Dry weight of the LR87-11 engine is 4300 lb for a thrust weight ratio of 128 using the 16.7:1 nozzle extension.
These are my isometric drawings and diagrams. The diagrams comprises of a circulation, balance by configuration, and geometric derivative.
Payless Store Lights While Drving
FxCamera App - SymmetriCam
Multi-Reflection Configuration
Google G1 Mobile
Lab Purpose: Master frame-relay principal, frame-relay switch basic
configuration, frame-relay client basic configuration.
Lab Requirement: frame-relay encapsulationis IETF, LMI type is ANSI.
Make the whole frame-relay network full-mesh and could ping from
each other.
Frame-relay Clients are in 10.1.1.0/24 network.
Click the below links to view the complete lab configuration.
Another official USAF photo of our configuration team:
Medical Evacuation Evaluations, McChord Air Force Base, Wash., July 23, 2007. Air Mobility Command's Rodeo 2007 is a readiness competition of U.S. and international mobility air forces. It focuses on improving warfighting capabilities and support of the Global War on Terrorism. (U.S. Air Force photo by Tech. Sgt. Maria J. Bare) (Released)
CX9000E Superb
Standard Configuration:
Main unit
14" high resolution monitor
2.5/3.5/4.0/5.0MHz Convex probe
Options:
Thermal Paper Printer
Cine loop system
CX9000E Superb Dual-display
CX9000E Superb Multi-F
CX9000E Superb Dual-display Multi-F
Comparison between PowerMac G3 and G5
End of 2004 - Update configuration
PowerMac G3 -> PowerMac G5 + PowerBook G4
ZEN MAGNETS - Neodymium Magnetic Balls (@510) - 7 Sphere configuration
Video: www.youtube.com/watch?v=xzCCiWrjF_M
7 x (C60 spheres) with 6 x (5-ball ring x 3) spacers inbetween the spheres
This was inspired by Daniel Wyllie's 5 Spheres of Persistance
www.flickr.com/photos/dwyllie/3865419726
The C60 Sphere didn't quite have the pentagon ring alignment for that shape so I improvised a bit.
This is sitting on a mini lazy susan with the LED crystal light base underneath.
The settings on my Behringer MIC200 preamp: Neutral mode, gain right in the middle, output all the way up, +48V on, low-cut on, 20db pad off, phase reverse off.
A technician in the Vertical Assembly Building carefully inspects the payload section of a Progeny Mk6 Block I rocket, which has been modified to carry two mystery goo containment units where a second payload truss like what is below usually resides. All 4 of the rockets batteries are now stored down there and no room remains for any additional science instruments
Used configurations box and Jesse James buttons to create this for a store display for The Crop Shop in Rockland, MA.
Net-connection for the thin-client that's the base of the weather-station.
Got it working on a desktop, just took a screen-dump to see if I could get it working via commandline on the server.
Decided to change my Pearl Forum Drum Kit configuration once again. This time it has the awesome 2012 release Paiste PST8 cymbals (More cymbals to come- wait for photos in the new couple of weeks).
Specifications:
12x11 Tom
13x11 Tom
16x16 Floor Tom
14x5.5Snare Drum
22x18 Bass Drum
Cymbals (Current- More to come):
Paiste PST8 14in Medium Hats
Paiste PST5 8in Splash
Paiste PST8 16in Medium Crash
Paiste PST8 20in Medium Ride
Pearl 16in Brass Crash
Wuhan 16in China
Hardware:
Gibraltar SC-GCA Cymbal Grabber Arm x1
Gibraltar 6609 Heavy Boom/Straight Cymbal stands x2
Pearl Ax20 Adapter Clamps x2
Pearl TH88 Short Tom Holders x2
Pearl CH70 Mini Boom Cymbal arm
Pearl B790 Lightweight Cymbal Boom Cymbal stand x1
Pearl B790 Lightweight Cymbal Straight stand x1
Lab Purpose: Master basic extended ACL configuration
Lab Requirement: Deny icmp traffic from network 192.168.1.0, only
pc1 can access FTP server.
Click the below links to view the complete lab configuration.
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