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Help your clients embrace civic pride and support local communities with products that embody excellence and sustainability.
USA-made promotional products make a big impact. According to the most recent Ad Impressions Study from ASI Research, 54% of consumers feel more favorable about an advertiser that promotes their company on a domestically made item. Fortunately, the promo industry is chock-full of made-in-America options.
Custom-labeled bottled water is a great way to quench thirst while effectively advertising clients’ services. Choose from two sizes. Great for conferences, trade shows and events.
Your clients can join the movement toward a greener future with the 32 oz. Crafted with Tritan ReNew, this reusable, dishwasher-safe drinkware is constructed with 50% certified post-consumer recycled material and has a drink-through lid. Available in five colors.
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These Brite Spots jumbo fluorescent highlighters illuminate important notes and textbook passages in six eye-catching colors. Perfect for highlighting both thick and thin lines. Choose either a silkscreen or full-color decal imprint.
The Tamarac menu cover features a silky leather-like exterior, sturdy black interior and album-style corners to provide a professional showcase for entrée, drink and dessert menus. Removable and replaceable inserts make it simple to update menu items.
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Founders : Who We Are : Naperville Education Foundation
The Naperville Education Foundation was incorporated in Illinois and registered as a 501(c)3 on March 6, 1992, to provide resources for enhancement of and opportunities for learners and educators in the Naperville Community Unit School District 203. These individuals, companies, and organizations listed contributed $1,000.00 or more to the Naperville Education Foundation in its charter year.
25th Anniversary Celebration
Andee Boiler & Welding Company Inc.
Dr. and Mrs. Fari Barhammand
Gary & Gloria Baumgartner
Blossoms: Bob & Margaret Park
W. Brand and Dr. Mary Ann Bobosky
Cellular Communications Corporation
Ed Channell
Dr. James A. & Jean N. Clark
Dennis & Bonnie Coates
Tom & Cathy Colgan
Colonial Caterers: Al & Naomi Rubin
Mary Lou Cowlishaw
Dave & Kathy Cox
Downers Grove Dodge
Dennis & Maggie Ellithorpe
Harris & Ruth Fawell
Framin’ Place (now Colbert Custom Framing & Art Printing): Tom & Mary Colbert
Jon T. & Geri Fuglestad
Neil & Virginia Gerald
John T. Greene
Mary Pat Greene
John Greene Realtor
Harris Bank, Naperville
Rita & John Harvard
Horizon Chevrolet
Steven & Janet Feller Hyde
Illinois Pork Producers Association
John & Sonja James
James, Brooks, Adams, & Tarulis Attorneys at Law
Jardine Insurance Brokers
Tom & Peggy Jordan
Kenneth & Susan Koranda
Rod & Ginny Lacy
Dr. Leon Lederman
Joyce & Raymond Lenart
Leo & Carolyn LeSage
Linden Oaks Hospital
Eddie & Carolyn Mack
Marge & John Matsock
Ed & Julie McCutcheon
MidAmerican Federal Savings Bank
Minuteman Press of Naperville
Nick & Alice Modaff: Class of 1933
Harold & Margaret Moser
Naperville Excavating, Inc.
Naperville Noon Lions Club
Naperville Sunrise Rotary Club
Naperville Unit Education Association
Tom & Kathleen O’Donnell
In Memory of Jeff Preston NCHS 1983
Rick & Monica Price
Karen & Gary Privett & Family
Dr. Christine Rauscher
Read-Rite Corporation
Luzern & Joann Richter
Saturn of Naperville
James & Kathleen Schlesser
Don & Phyllis Schroeter
Paul Schroeter NCHS 1972
The Rotary Club of Naperville
ServiceMaster Company
Sound Incorporated
William & Peggy Steinke
Sun Publications
Carol J. Carius Vermaat
Van Den Bergh Foods Company
Dr. & Mrs. Donald E. Weber
Jim & Kathleen Williams
Dennis & Rosemary Macko Wisnosky
Gordon & Grace Woeltje
Janice & Dick Yetke
Norm & Liz Zienty
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Intercontinental ballistic missile LGM-30A/B Minuteman-1
First stage engine:
Developed by Thiokol (TU-122) and runs on a mixed propellant consisting of polybutadiene acrylic acid, ammonium perchlorate, aluminum powder and epoxy resin (see manufacturing technology).
The first stage engine has four deflecting nozzles. Nozzles 2 and 4 deflect up and down for pitch control, and nozzles 1 and 3 deflect to one side for yaw control and to the other side for roll control. The deflection angle of the nozzles is about 8°.
The nozzle has a truncated cone shape with an opening angle of 42°. The throat diameter of the nozzle is about 0.2 m, the outlet diameter is about 0.56 m. The nozzles are bolted to flanges mounted on short exhaust pipes protruding from the lower bottom of the housing. The nozzle consists of a steel base and a moving part connected by a sealing ring. The length of the moving part of the nozzle is about 0.63 m. The moving part of the nozzle is made of reinforced phenolic resin with an insulating plastic gasket. The critical section of the nozzle has a tungsten insert reinforced with six graphite rings, the cross section of which is 3 cm2 on the front of the insert and 6 cm2 on the back. The inner surface of the nozzle from the critical section to the point with an expansion coefficient of approximately four has a protective graphite coating.
The deflection of the nozzles is carried out according to the signals from the guidance system, which enter the control unit installed in the central part of the lower bottom. The control unit is X-shaped and consists of a self-acting silver-zinc battery, an auxiliary power supply, four hydraulic servo cylinders and associated electronic equipment. The control unit does not require external power. The servo cylinders and auxiliary power supply are mounted on a platform that has internal channels that are pipelines. There are no external pipelines in the system.
Auxiliary power supply consists of motor, hydraulic pump, stopcock, filters, thermal resistance, 164 oil reservoir, quick connect fittings for filling and draining fluid, and a remote pressure switch. The variable displacement hydraulic pump is connected directly to a 27V DC compound motor. The ratio of weight to power output of this unit is 1 kg/hp. Each of the four nozzle drive hydraulic cylinders is rigidly fixed to the platform. The piston rod of the cylinder through the floating grain is connected to the fork on the movable part of the nozzle. Each actuator is equipped with a solenoid valve driven by signals from the servo amplifier of the control unit.
The wiring from the guidance system to the control unit is located on the outside of the engine case and is covered with a fairing.
Second stage engine:
Designed by Aerojet-General. Given the relatively small dimensions of the second stage, the engine housing could be made of fiberglass. However, studies have shown the inexpediency of such a solution, since in the three-stage version of the rocket, the middle stage body perceives large bending loads and would be too heavy if made of fiberglass. Therefore, steel of the same grade as for the first stage was chosen as a structural material (see manufacturing technology).
The second stage engine has four deflecting nozzles that are attached to the exhaust pipes on the underbody. Each nozzle has a truncated cone shape and an expansion factor of 18. The critical section of the nozzle contains a tungsten insert held in a graphite gasket about 25 mm thick. Exhaust cone nozzles are made of reinforced plastic. The nozzles are deflected by the same hydraulic system as in the first stage. Each nozzle can deviate within 6°.
An igniter is inserted into the hole in the center of the upper bottom of the cone, which is a small solid propellant rocket engine, the fuel of which weighs about 900 g and is in fact the same composition as the main engine fuel. The igniter enters the fuel charge by about 0.5 m and has a safety device that is the same for the igniters of all three stages.
Third Stage Engine:
Developed by Hercules and runs on dual base fuel, the main components of which include ammonium perchlorate with aluminum powder and nitroglycerin-nitrocellulose, which also serves as a binder (see manufacturing technology).
Each nozzle (see diagram), as in the first two stages, consists of a fixed base and a swivel exhaust cone that can deviate by 4°. Nozzle throat diameter approx. 0.09 m, outlet diameter approx. 0.38 m, expansion factor 18.
Nozzle exhaust cone made by injection molding at high temperatures. On the inner wall of the nozzle is an insulating coating consisting of a layer of phenolic resin reinforced with quartz fiber and a layer of graphite fabric impregnated with resin. Graphite fabric has high thermal conductivity, while reinforced phenolic resin has low thermal conductivity. A tungsten insert on a graphite gasket is installed in the critical part of the nozzle.
The third stage engine igniter is inserted into the center hole of the bottom plate. It consists of a small charge of solid fuel, the combustion of which begins as a result of the ignition of powder pellets. The igniter is equipped with a safety device. The switch of the system for undermining the plugs to turn off the engine is located on the upper skirt of the hull. Outside the housing in the fairing is the electrical wiring from the guidance system to the nozzle control unit.
Connection of all stages of the rocket is carried out through adapters in the form of truncated cones. Fastening is done with bolts. All stages of the rocket are equipped with self-liquidators located under the electrical wiring fairings.
Control system:
Inertial guidance system developed by Nord American’s Autoneсtics division. The main elements of the guidance system are an inertial platform, a miniature calculator D.17 and standard electronic units made on transistors. All guidance system equipment is housed in a sealed container with a diameter of 1.14 m, filled with helium, which provides cooling for electronic devices. At the base of the container is a fan and a liquid fuel heat exchanger. Outside, the container is covered with fiberglass insulation and, before being installed on a rocket, is placed in an aluminum casing of a monocoque design with a special protective coating. According to reports, the guidance system unit weighs about 81.8 kg. The power supply of the guidance system equipment is provided by silver-zinc batteries.
The inertial platform of the guidance system is mounted on a gimbals and can freely rotate 90° relative to the pitch axis, ± 70° relative to the roll axis and ±20° relative to the yaw axis. The platform is stabilized by two two-axis free gyroscopes, the rotors of which are mounted on gas bearings. One gyroscope serves as a reference for the pitch and roll axes, and the other for the course axis (one of the axes of this gyroscope remains free). Two-axis gyroscopes with gas bearings were chosen because they provide good dynamic stability for a long time and are able to withstand high overloads. To detect the displacement of the gyroscope body relative to the rotor, capacitive-type sensors are used. When the rocket is stored in the mine, to correct the position of the pitch and roll gyroscope relative to the local vertical, the platform has a two-axis level sensor, and the constant alignment of the course gyroscope with respect to the reference azimuth is carried out using an optical collimator.
Three integrating accelerometers are installed on the inertial platform to measure accelerations along each of the three axes. Each accelerometer has a pendulum mass floating in the fluid to reduce friction. Acceleration along the sensitive axis of any accelerometer displaces its mass, resulting in a signal that is amplified and transmitted to a motor-driven brake cap, which creates eddy currents and torque to return the mass to its original position. To control the operation of the accelerometers, the platform has three two-axis level sensors, which are also used for periodic calibration of the accelerometers.
The calculator included in the guidance system, in addition to the main function of calculating the guidance equations, performs a number of additional functions related to the assembly of the rocket and its verification both during storage in the mine and in preparation for launch. When assembling a rocket, a calculator is used to test each stage, including testing nozzle control units, stage separation devices, and other elements.
After the rocket is installed in the launch silo, the computer performs continuous and periodic checks of all rocket systems during the entire storage period. Continuous testing provides quality control of all systems, while periodic testing provides more thorough monitoring, which determines the accuracy of each element and deviations in characteristics, and automatically makes the necessary corrections. The difference in the two types of verification mentioned above can be seen in the following example. With a constant check of the control system unit, a signal is sent to the amplifier of this unit to determine that the servo drives deflect the nozzles in the right direction, and during a periodic check, the response time of the drives to the signal is also determined.
When preparing a rocket for launch, the computer performs a pre-launch check and timing. After launching the rocket, the computer performs guidance calculations, determines the time of separation of the stages, issues a command to turn off the engine of the last stage, determines the moment of separation of the nose cone and cocking the warhead in such a way that it hits the intended target.
The computer solves the basic guidance and control equations taking into account the aerodynamic characteristics of the rocket and generates control signals based on the relative position of the rocket coming from gyroscopes and accelerometers. Thus, the calculator performs the functions of converting the signals of the guidance system into a form convenient for driving the controls.
The calculator is a general-purpose calculator with a 27-digit code, in which 24 characters are used for calculations. The computer’s memory block is a magnetic disk rotating at a speed of 6000 rpm. The capacity of this block on rockets of the first modification is 2985 words.
The computer accepts 43 types of data from various equipment and performs two main calculation cycles: one cycle provides the solution of the guidance equation (where the missile is at the moment in relation to where it should be to hit the target), and the other – the calculation of signals for the control system.
The calculator provides three pairs of digital output signals for inputting corrections to the gyroscopes and three output voltages in analog form for driving the pitch, yaw and roll control nozzles. In addition, for verification tests, the calculator sends a signal to drive a paper tape puncher or electric teleprinter, recording the test results. During experimental launches, the calculator is also used to signal the action of the telemetry system.
The calculator is designed in such a way that by changing the information entering the memory block, it can be completely reprogrammed. To enter data into the memory block of the calculator, a programmer located on the conveyor is used, which is brought to the launch shaft and sends to the memory block the data necessary to hit a specific target. All Minuteman missiles in the silos are pre-programmed to hit a pre-selected target.
Since the calculator performs a number of complex functions related to checking and calibrating the rocket, it is necessary to have some kind of instruments that check the operation of the calculator itself.