Internet Cafe Software
GETKO is a software solutions for the operation of an Internet Cafe, Cyber Cafe, Gaming Center, Internet Center or PC rental system.instrumentationtools.com Designed primarily for billing Internet Cafe business and also can be used to control the PCs on your intranet. System functions and user interface has been designed to be easy to use with little or no experience in the computer industry. The software allows you to set up various marketing plans for each user to chose from. GETKO is Client / Server application which allows you to easily manage and monitor all client machines status remotely from the Server in on-line and in real time. We have been producing Internet Access Time Management solutions and Internet Cafe Software for over 10 years and have sold our products all over the world. Our team specialize in timer software and software based control systems for Windows 98/ME/2000 and XP.
We supply computer access solutions to hotels, cruise ships, hospitals, schools, libraries, colleges, learning centers, law chambers, youth centers, Cyber Cafes and many other diverse areas of industry. There are a number of Internet Cafe Software and public access timer solutions from a variety of companies in today's market. They vary by their functionality, their look and indeed their stability. Choose wisely and join our ever growing global customer base, choose NetTime Software! This is a centralized Server version of the GET KO ™. Each customer PC will be installed with NetTime Client. All of the NetTime Client PCs connect to NetTime Server from which you can centrally manage your NetTime Network. Please Register or Login to post new comment. 5 things to consider while going for android app development.
Electrical power is connected to the dc utility power outlet on panel A15, and audio is connected to the PS comm outlet on panel A15. During launch, the PS comm outlet is used for crew communications; therefore, the audio cable for the teleprinter must be connected on orbit, and the ATU at panel L9 must be reconfigured on orbit. TDRSS. The TAGS consists of a facsimile scanner on the ground that sends text and graphics through the Ku-band communications system to the text and graphics hard copier in the orbiter. The interim teleprinter operates via the S-band PM system when the TDRSS is not operational.
The CCTV system also provides the capability to document on-orbit activities and vehicle configurations for permanent record or for real-time transmission to the ground. The CCTV system can be controlled by both onboard and remote uplink commands. The CCTV system is a standard monochrome (black and white) system with an optional color capability by means of interchangeable camera lenses. Color scenes are not available on the onboard monitors because of hardware restrictions; however, color scenes are available on recorded and downlinked video. Video inputs to the CCTV system are available from cameras mounted at several locations in the payload bay and on the remote manipulator system arm, which is mission dependent. Cameras are also used in the middeck and the flight deck of the crew compartment.
The information obtained through the sensors of the OEX instruments must be recorded during the orbiter mission because there is no real-time or delayed downlink of OEX data. In addition, the analog data produced by certain instruments must be digitized for recording. The support system for OEX comprises three subsystems: the OEX recorder, the system control module and the pulse code modulation system. The SCM is the primary interface between the OEX recorder and the experiment instruments and between the recorder and the orbiter systems.corby.com It transmits operating commands to the experiments. After such commands are transmitted, it controls the operation of the recorder to correspond to the experiment operation.
The SCM is a microprocessor-based, solid-state control unit that provides a flexible means of commanding the OEX tape recorder and the OEX and modular auxiliary data system. The PCM system accepts both digital and analog data from the experiments. It digitizes the analog data and molds it and the digital data received directly from the experiments into a single digital data stream that is recorded on the OEX recorder. The PCM also receives time information from the orbiter timing buffer and injects it into the digital data stream to provide the required time correlation for the OEX data. The SCM selects any of 32 inputs and routes them to any of 28 recorder tracks or four-line driver outputs to the T-0 umbilical; executes real-time commands; controls experiments and data system components; and provides manual, semiautomatic and automatic control.
The recorder carries 9,400 feet of magnetic tape that permits up to two hours of recording time at a tape speed of 15 inches per second. After the return of the orbiter, the data tape is played back for recording on a ground system. The tape is not usually removed from the recorder. This information will increase understanding of leeside aeroheating phenomena and will be used to design a less conservative thermal protection system. SILTS provides the opportunity to obtain data under flight conditions for comparison with data obtained in ground-based facilities. Six primary components make up the SILTS experiment system: (1) an infrared camera, (2) infrared-transparent windows, (3) a temper ature-reference surface, (4) a data and control electronics module, (5) a pressurized nitrogen module and (6) window protection plugs.
These components are installed in a pod that is mounted atop the vertical stabilizer and capped at the leading edge by a hemispherical dome. Mach 3.5 and that the accuracy of the air data would not satisfy aerodynamic research requirements. These measurements, combined with acceleration measurements from the companion high-resolution accelerometer package experiment, will allow calculation of orbiter aerodynamic coefficients in the flow regime previously inaccessible to experimental and analytic techniques. SUMS complements SEADS by providing data at higher altitudes. The resultant flight data base will aid in future development of analysis techniques and laboratory facilities for predicting winged-entry-vehicle performance in hypersonic rarefied flow. Furthermore, SUMS will measure equilibrium gas composition at the inlet port, making the experiment a pathfinder for future mass spectrometer application in the study of aerothermodynamic properties of the transition flow field.
The SUMS experiment system consists of a sample orifice, an inlet system and a mass spectrometer. The sample orifice penetrates a thermal tile just aft of the fuselage stagnation point and just forward of the orbiter nose wheel well. The orifice is connected to the inlet system by a short tube through the forward nose wheel well bulkhead. The inlet system is connected through a longer tube to the mass spectrometer, which is mounted above the inlet system on the forward nose wheel well bulkhead. SUMS is designed for easy removal and reinstallation between flights to accommodate modification or repair. The mass spectrometer is a flight spare unit from the Viking project's upper atmosphere mass spectrometer system.
The unit has been modified to be compatible with the orbiter's mechanical, electrical and data systems. The mass spectrometer measures gases from hydrogen through carbon dioxide at a five-second rate. The inlet system contains two switchable flow restrictors that expand the measurement range of the mass spectrometer and position its measurement interval over the desired altitude range. Data from SUMS are output to the OEX data system for recording during flight operation. SUMS is controlled by stored commands that are transmitted to the orbiter during flight and by internal software logic. Application of power for vacuum maintenance or for normal operation is controlled by stored commands; while internal control of system operation, such as opening and closing valves, is performed by preprogrammed logic. SUMS will be powered on shortly before deorbit burn initiation and will sample the inlet gases down to an altitude of 40 nautical miles.
At an altitude of about 59 nautical miles, the range valve will close to switch between the two flow restrictors. At 59 nautical miles, the inlet valve and protection valve will close; but the mass spectrometer will continue to operate until landing, observing the pump-down and background signals after entry. Operation of SUMS on repeated shuttle flights will not only build a substantial body of aerothermodynamic data for future winged-entry-vehicle design applications, but also add to the knowledge of mass spectrometer applications in aerothermodynamic research. As a further benefit, data will be obtained on atmospheric properties in the altitude range where experimental data are, to date, extremely sparse.
In addition, the baseline data are operational measurements that are not subject to the desired changes for conducting experiments. The ACIP is a group of sensors that will be placed on the orbiter to obtain experiment measurements unavailable through the baseline system. The aerodynamic acceleration data from the HiRAP experiment, output on existing ACIP channels, have been used to calculate rarefied aerodynamic performance parameters and/or atmospheric properties pertaining to several flights, beginning with the STS-6 mission. These flight data support advances in predicting the aerodynamic behavior of winged entry vehicles in the high-speed, low-density flight regime, including free molecular flow and the transition into the hypersonic continuum. Aerodynamic performance under these conditions cannot be simulated in ground facilities; consequently, current predictions rely solely on computational techniques and extrapolations of tunnel data.
For improvement or advances, these techniques depend on actual flight data to serve as benchmarks, particularly in the transition regime between free molecular flow and continuum flow. Advancements in rarefied aerodynamics of winged entry vehicles may also prove useful in the design of future advanced orbital transfer vehicles. Such OTVs may use aerodynamic braking and maneuvering to dissipate excess orbital energy into the upper atmosphere upon return to lower orbits for rendezvous with an orbiter from the space station. A key aerodynamic parameter in the OTV design is the lift-to-drag ratio, which is measured directly in the HiRAP experiment. Furthermore, an OTV may require a flight-proven, sensitive onboard accelerometer system to overcome uncertainties in the upper atmosphere.
The experience gained from the planned multiple HiRAP flights may provide valuable test data for the development of future navigation systems. In addition, the experiment provides data on key atmospheric properties (e.g., density) in a region of flight that is not readily accessible to orbital vehicles or regular meteorological soundings. It supplements existing orbiter operational instrumentation by conditioning, digitizing and storing data from selected sensors and experiments. The MADS collects detailed data during ascent, orbit and entry to define vehicle response to flight environments. It permits correlation of data from one flight to another and enables comparison of flight data from one orbiter to another orbiter.
All MADS equipment installed in the orbiter is structurally mounted and environmentally compatible with the orbiter and mission requirements. Because of its location, the MADS does not intrude into the payload envelope. Equipment consists of a pulse code modulation multiplexer, a frequency division multiplexer, a power distribution assembly and appropriate signal conditioners mounted on shelf 8 beneath the payload bay liner of the midfuselage. In OV-102 (Columbia), MADS inputs its information to the system control module and records it on the OEX recorder located below the crew compartment middeck floor. In OV-103 (Discovery) and OV-104 (Atlantis), a MADS control module and recorder are mounted below the crew compartment middeck floor.
MADS records approximately 246 measurements from the orbiter airframe, skin and orbital maneuvering system/reaction control system left-hand pod. The MADS interfaces with the orbiter through the orbiter's electrical distribution system and operational instrumentation inputs for status monitoring. Coaxial cables and wire harnesses from the sensors are routed through the orbiter payload bay harness bundles to the signal conditioners, PCM multiplexer and FDM, attached to the midfuselage shelf. After the signal conditioners and the multiplexers have processed the data, four outputs of the FDM and one output of the PCM multiplexer are routed forward to the SCM in OV-102 for recording on the OEX recorders.
In OV-103 and OV-104, the four outputs of the FDM and one output of the PCM multiplexer are routed forward to the MCM for recording on five tracks of the MADS recorder. In addition, the MADS recorder is used during ascent to record additional space shuttle data consisting of solid rocket booster wide band and external tank signals. The MADS is not considered mandatory for launch, and its loss during flight does not cause a mission abort. It measures and records data for predetermined events established by test and mission requirements. For a typical mission, approximately five hours before launch, the MADS is powered on from the preset switch configuration to supply a prelaunch manual calibration.
After calibration, all switches are returned to the preset configuration, leaving the MADS in the standby position and only the MCM receiving power. This mode continues until nine minutes before launch, at which time the MADS attains the full-system mode through uplink commands and all its components are powered on. In this mode, the MADS recorder is operating at a continuous tape speed of 15 inches per second, recording aerodynamic coefficient identification package, flight acceleration safety cutoff, ET, SRB, wide-band and PCM data. The MADS PCM bit rate is 64 kbps.youtube.com The wide-band-only mode is used during the prelaunch automatic and manual calibrations.
