omniomni/omni-engineering huggingface dataset:
Vidor Asso X Jewel. The Asso X Jewel is an all - wood, low wing, single engine, two tandem seats ultralight aircraft, designed by Italian designer Giuseppe Vidor.

This aircraft is one of his many wooden designs, marketed by Vidor's Asso Aerei company, like the Asso V Champion, Asso IV Whisky and Asso VI Junior. The aircraft kit/plans are specified for the Rotax 912, but it is also one of the very few aircraft reported to be using the Sauer S 2100 ULT engine.

Variants
Millennium Master
A composite airplane, evolved from the Asso X Jewel.

Pelegrin Tarragon
A composite airplane, evolved from the Millennium Master.

Blackshape Prime
A composite airplane, evolved from the Millennium Master.

Specifications

References

Asso X Jewel
2000s Italian sport aircraft
Low-wing aircraft
Single-engined tractor aircraft
Murugappa Polytechnic College. Murugappa Polytechnic College is a government-aided institution, the college is located in Avadi, Chennai, India. Diploma programmes Civil Engineering and Computer Engineering courses offered include Electrical &
Electronics Engineering, Mechanical Engineering etc.

Courses Offered
Diploma Programmes
 Civil Engineering
 Computer Engineering
 Electrical & Electronics Engineering
 Electronics & Communication Engineering
 Mechanical Engineering
 Mechanical Engineering (Tool & Die)
 Electronics (Robotics)

Infrastructure
 Hi-Tech Center
 Library
 Cricket Ground
 Volleyball Court
 Football Court
 Ball badminton Court
 Table tennis
 Carrom Board
 Chessboard
 Shuttle Badminton Court
 Tennikoit Court
 8 Station Multi Gym
 National Social Service
 National Cadet Corps

References

External links
 

Universities and colleges in Chennai
Universities and colleges established in 1957
1957 establishments in Madras State
Transcode (character encoding). Six-Bit Transcode, or Six-Bit Transmission Code, was, for a few years, one of the three character sets used by IBM for Binary Synchronous Communications. Transmission using 6-bit Transcode had higher throughput than transmission using 8-bit EBCDIC or ASCII, provided that the data to be transmitted used a limited set of 48 characters.

The IBM 2780 data transmission terminal was announced with Transcode support in 1967. Its successor, the IBM 3780 data communication terminal, announced in 1972, dropped Transcode support and added a "space compression" option.

Transcode is a six-bit character code. It relates to IBM's punched card code but, like EBCDIC, it is not BCD. Its 64 values consist of the 26 uppercase letters, 10 numbers, 11 symbols, space, and 16 control characters. Its 48 printable characters are ABCDEFGHIJKLMNOPQRSTUVWXYZ0123456789 .'-/@#$%&*⌑; it cannot represent ,:;!?"()[]<>+^=_\`{}|~. Characters are transmitted with odd parity. The 2780 cannot use the 16 control characters as data characters in Transcode mode.

Code table

Code table (from 2780 manual)

Devices using Transcode
 IBM 2701 Data Adapter Unit
 IBM 2703 Transmission Control
 IBM 2780 Data Transmission Terminal
 IBM System/370 model 135 Integrated Communications Adapter (ICA)

References

Character encoding
IBM computer hardware
Gold monoiodide. Gold monoiodide is the inorganic compound of gold and iodine with the formula AuI. It can be synthesized by dissolving gold powder in an aqueous solution of iodine and potassium iodide. With Lewis bases, AuI reacts to give numerous complexes.

Preparation
Gold monoiodide can be obtained by reacting a tetrachloridoauric acid solution with furthermore potassium iodide. It is also possible to produce it by reacting gold and iodine in a protective atmosphere at around 390 °C.

Properties
Gold monoiodide is a yellow, crystalline powder that gradually decomposes upon contact with water, humidity or light. It has a tetragonal crystal structure with the space group P42/ncm (space group no. 138), a = 4.359 Å, c = 13.711 Å.

References

Gold(I) compounds
Iodides
Metal halides
Gold–halogen compounds
1992 Nigerian Air Force C-130 crash. On 26 September 1992, a Nigerian Air Force Lockheed C-130H Hercules crashed three minutes after take-off from Lagos, Nigeria. All 159 people on board were killed, including 8 foreign nationals. The aircraft was taking off at high weight and three engines failed.

A total of 151 Nigerians, 5 Ghanaians, 1 Tanzanian, 1 Zimbabwean, and 1 Ugandan military officers were confirmed to have died. This is the deadliest crash of a C-130 Hercules.

References

Accidents and incidents involving the Lockheed C-130 Hercules
Accidents and incidents involving military aircraft
Aviation accidents and incidents in 1992
Aviation accidents and incidents in Nigeria
20th century in Lagos
September 1992 events in Africa
1992 disasters in Nigeria
Military history of Lagos
Cengiz Topel Naval Air Station. Cengiz Topel Naval Air Station (), a.k.a. Topel Airport or formerly Cengiz Topel Air Base,  is a Turkish Navy air station located east of İzmit in Kocaeli Province, Turkey. The airport is in joint use for military and civil. Restructured in 1976, it hosts the Turkish Naval Aviation Command with two flying units, the 301st Squadron of fixed-wing aircraft and the 351st Squadron of rotorcrafts.

The facility, formerly a base of the Turkish Air Force, is named after the Air Force fighter pilot Capt. Cengiz Topel, whose F-100 Super Sabre was shot down on August 8, 1964 during Turkey's military air bombardment in Cyprus. He ejected safely over land, but was promptly captured after landing and lynched by members of the Cyprus National Guard. He was the first Turkish pilot ever killed in action.

History 
Topel Airport was originally a Turkish Air Force facility. Following the re-establishment of the aviation branch of the Turkish Navy in 1968, the first naval helicopter pilots were trained by the Turkish Army Aviation Command's flight school  at the Güvercinlik Army Air Base in Etimesgut, Ankara Province. The unit, formed in 1972 at the same base, was transferred on 19 May 1973 from Ankara to Cengiz Topel Air Base due to its location close to Gölcük Naval Base in Kocaeli Province following a protocol signed with the Turkish Air Force two weeks before. That day, Turkish Navy's first rotorcraft unit was renamed 351st Naval Helicopter Squadron.

The 301st Naval Air Squadron, formed in 1971 at Etimesgut Air Base in Ankara Province as the fixed wing aviation unit of the Navy, was transferred on 4 August 1972 to Bandırma Air Base to join the 6th Air Force Wing. With its four maritime patrol aircraft and twelve anti-submarine warfare (ASW) aircraft of type S-2 Tracker, the unit was then relocated to Cengiz Topel Air Base on 14 July 1976.

The base, in joint use since 1973 by the air force and the navy, was transferred to the Turkish Navy Command on 14 July 1976 following the order of the Turkish General Staff. Finally, the Naval Air Station Command was established on 4 August 1976.

The base was assigned to NATO on 28 October 1981. In 1983, helipads in Istanbul and Çanakkale were put in service so that helicopters of the air station could use them also.

In 2011, the airport was opened to public air traffic. Anadolujet operated domestic flights.

Airlines and destinations

The following airlines operate regular scheduled and charter flights at Cengiz Topel Airport:

Traffic Statistics

Access
Cengiz Topel Naval Air Station is situated  east of Köseköy neighborhood in İzmit and  west of Lake Sapanca between the highway  and the motorway .

References 

 

Turkish Navy bases
Airports in Turkey
Heliports in Turkey
Economy of Kocaeli Province
Military in Kocaeli
Buildings and structures in Kocaeli Province
Transport in Kocaeli Province
Martlet (disambiguation). Martlet is an English heraldic charge depicting a stylized bird of the swallow family.

Martlet may also refer to:

Technology
 Martlet (CU Spaceflight), a project of CU Spaceflight to develop a small rocket which can be launched from a balloon
 Martlet 3, and other Martlet projectiles during the US/Canada High Altitude Research Project (Project HARP)
 Southern Martlet, single-seat biplane sports aircraft
 Grumman Martlet, the original name given to Royal Navy Grumman F4F-4 Wildcat carrier fighters
 Martlet (missile), a rocket powered missile

Other uses
 The Martlet, a student newspaper at the University of Victoria in Victoria, British Columbia, Canada
 McGill Martlets, the women's athletic teams that represent McGill University in Montreal, Quebec, Canada
 Martlet House, a building which was the Montreal headquarters of the Seagram Company
 Operation Martlet, a British diversionary operation in the Second World War in June 1944 in France
 Martlet, a major character in the video game Undertale Yellow
Philip Hubert Smith. Philip Hubert Smith (10 April 1906 – 1 November 1969) was a British automotive engineer, author and motoring journalist.

Born in Keighley, Bradford, Smith began his career began as an automotive engineer, his qualifications including being a chartered engineer and memberships of both the IMechE and the SAE. He was also the technical editor of Motor World. It is for his technical books that he is best remembered, particularly The High-Speed Two-Stroke Petrol Engine, The Scientific Design of Exhaust and Intake Systems and (edited by L. J. K. Setright) Valve Mechanisms for High-speed Engines.

In later years he lived at Ben Rhydding, in Yorkshire. He died in Wharfedale, Yorkshire in 1969.

Published books

References 

British automotive engineers
British motoring journalists
1906 births
1969 deaths
STAL Dovern. The STAL Dovern was a Swedish turbojet design of the early 1950s, named after a lake in Finspång municipality in Östergötland, Sweden.   Intended to power the Saab 35 Draken, this aircraft was powered by the Rolls-Royce Avon instead.  The Dovern did not enter production.

Design and development
The STAL company had been designing steam turbine engines and in the 1940s begun designing gas turbine engines. Their first running engine was the Skuten, ground tested in 1949 but not flown. The Dovern was the next design, featuring a nine-stage axial compressor and single-stage turbine. First run in 1951, the engine was flight tested during 1953 using an Avro Lancaster provided by Air Service Training.  The engine was installed underneath in a nacelle faired-in to the Lancaster's bomb bay. After several thousand hours of ground running and more than 300 hours of flight testing the engine was not selected, the Rolls-Royce Avon being preferred.

Applications
Avro Lancaster (test bed only)
Saab 35 Draken (intended application)

Variants
Dovern
Base variant.

Dovern IIA
Basic engine without de-icing

Dovern IIB
Compressor bleed air system added for ice protection.

Dovern IIC
Afterburning version producing  thrust.

Specifications (Dovern IIB)

See also

References

Notes

Bibliography

 Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. 
 

1950s turbojet engines
Robert O. Pickard Environmental Centre. The Robert O. Pickard Environmental Centre is a waste water treatment facility in  Ottawa, Ontario, Canada. It provides secondary treatment to about 720,000 people.  

It is located at 800 Green Creek Dr., Ottawa, Ontario, and discharges to the Ottawa River. It was built in 1963 as a primary treatment plant, it was then later uprated to secondary treatment between 1988 and 1993. At the time of the upgrade, the site was named after the then Commissioner of Works.

It is also one of Canada's largest wastewater treatment facilities.

References

External links
City Of Ottawa Page

Sewage treatment plants in Canada
Buildings and structures in Ottawa
Egvoyager Voyager 203. The Egvoyager Voyager 203 is an Italian ultralight aircraft, designed and produced by Egvoyager and introduced in May 2011. The aircraft is supplied as a kit for amateur construction or as a complete ready-to-fly aircraft.

Design and development
The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a cantilever low wing, a two-seats-in-side-by-side configuration enclosed cockpit under a bubble canopy with gull-winged doors, fixed, or optionally retractable, tricycle landing gear and a single engine in tractor configuration.

The aircraft is made from composites. Its  span wing employs flaps. The standard engine available is a  Rotax 912ULS four-stroke powerplant. The basic model is the Voyager Fly, with the Voyager Club and the Voyager Style being models with options included as standard equipment.

A light-sport aircraft category version is planned for the United States market.

Variants
Voyager 203 CF
Fixed landing gear model
Voyager 203 CR
Retractable landing gear model, at an additional cost of €7000.

Specifications (Voyager 203)

References

External links

2010s Italian ultralight aircraft
Homebuilt aircraft
Single-engined tractor aircraft
Alkyl polyglycoside. Alkyl polyglycosides (APGs) are a class of non-ionic surfactants widely used in a variety of cosmetic, household, and industrial applications. Biodegradable and plant-derived from sugars, these surfactants are usually derivatives of glucose and fatty alcohols.  The raw materials are typically starch and fat, and the final products are typically complex mixtures of compounds with different sugars comprising the hydrophilic end and alkyl groups of variable length comprising the hydrophobic end. When derived from glucose, they are known as alkyl polyglucosides.

APGs exhibit good wetting, foaming, and detergency properties, making them effective in cleaning and personal care products. They are also stable across a wide pH range and compatible with various other surfactants.

Uses
APGs are used to enhance the formation of foams in detergents. They are also used in the personal care industry because they are biodegradable and safe for sensitive skin.

Preparation
APGs are produced by combining a sugar such as glucose with a fatty alcohol in the presence of acid catalysts at elevated temperatures.

References

Glycosides
Non-ionic surfactants
Institute of Cryptography, Telecommunications and Computer Science. The Institute of Cryptography, Telecommunications and Computer Science () or IKSI (ИКСИ) is a research institute within the Academy of the Federal Security Service of Russia, which trains specialists in areas such as the transfer, protection and processing of information. The key specialist training areas are cryptography, applied mathematics, information technology and digital technology, electrical engineering, radio technology and communications.

Prior to the dissolution of the Soviet Union, the Institute was known as The Technical Faculty of the KGB Higher School.

History
The institute began its history in 1949 when a resolution by the Politburo created the Higher School of Cryptographers, and a closed department was created under the Mechanics-Mathematics Faculty of Moscow State University by a resolution of the Council of Ministers of the USSR. Later they united to become the technical faculty of the Dzerzhinsky Higher School of the KGB.

The institute comprises faculties of applied mathematics, specialised engineering and information security, departments of natural science, special skills, and English language. The institute also runs an evening physics and maths school, an ex-budgetary Scientific Research Laboratory while the Academy has provision for post-graduate military courses, MA and PhD dissertation boards.

Specialties
Department of Applied Mathematics
Cryptography
Applied Mathematics and Computer Science Automation of information and analytical processes
Faculty of Special Technology Information, security telecommunications systems and electronic systems
Faculty of Information Security

Notable alumni

Eugene Kaspersky – cybersecurity expert

See also
FBI Academy
National Intelligence University
Mercyhurst University Institute for Intelligence Studies

References

External links
Institute of Cryptography, Telecommunications and Computer Science  in the FSB Academy Official Website

Federal Security Service
Universities and colleges established in 1949
Intelligence analysis
Intelligence education
Universities and institutes established in the Soviet Union
1949 establishments in the Soviet Union
KGB
Communications in the Soviet Union
Telecommunication education
Henry Haberfield Thomas. Henry Haberfield Thomas (11 May 1886 – 17 October 1918) was an English aircraft designer and chief designer at S.E. Saunders Limited. Only one of his designs flew before he was killed by the 1918 flu pandemic.

Early life
Thomas was born in Bristol on 11 May 1886.

Aircraft designer
In 1909 he joined the British & Colonial Aeroplane Company moving in 1914 to Vickers in London. At the start of the first world war he moved to the Royal Aircraft Factory. In July 1916 he was appointed the chief designer at S.E. Saunders Limited on the Isle of Wight. Thomas first design to fly was the Saunders T.1 a two-seat biplane, it first flew in 1917 but only one was built. His next project was a large flying boat bomber named Great Britain designed to carry a 1,000 lbs of bombs to Berlin. The design was not built possibly due to Thomas contracting influenza from which he died on 17 October 1918.

Family life
Thomas married in May 1917 to Martha Jessie Paterson and they had a daughter in May 1918.

References

1886 births
1918 deaths
English aerospace engineers
Deaths from the Spanish flu pandemic
Graham-Perren Racer. The Graham-Perren Racer, or Graham-Perren Monoplane, was a racing aircraft built to compete in the 1934 National Air Races, including the Greve Trophy.

Design and development
The racer was a short-coupled, wire braced, mid-winged aircraft with fixed conventional landing gear and an open cockpit. The  Wright Gipsy engine protruded upward through the cowl leaving little forward visibility.

Specifications (Graham-Perren Racer)

See also

References

Racing aircraft
Mid-wing aircraft
Single-engined tractor aircraft
Ehroflug Coach II S. The Ehroflug Coach II S is a Swiss ultralight aircraft, designed by Egon Scheibe and produced by Ehroflug of Altnau. It was introduced in 1989. The aircraft is supplied as plans, as a kit for amateur construction or as a complete ready-to-fly-aircraft.

Design and development
The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a strut-braced parasol wing a two-seats-in-side-by-side configuration open cockpit, fixed conventional landing gear and a single engine in tractor configuration.

The aircraft fuselage is made from welded steel tubing, with the wing built from aluminium tubing with wooden ribs. The airframe is covered in doped aircraft fabric. Its  span wing has an area of  and is supported by cabane struts, V-struts and jury struts. The wings are quickly detachable for storage. Standard engines available are the  Sauer 2.1 four-stroke Volkswagen air-cooled engine and the  Rotax 582 two-stroke powerplant.

While still in production in 2015, the aircraft was only built on request.

Specifications (Coach II S)

References

External links

1980s Swiss ultralight aircraft
Homebuilt aircraft
Single-engined tractor aircraft
Parasol-wing aircraft
Ascent propulsion system. The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and  oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion instability problems.

Origins
The LMAE traces its origin to the earlier Bell Aerosystems engines (8096, 8247) used in the RM-81 Agena, the rocket upper stage and satellite support bus developed by Lockheed initially for the canceled WS-117L reconnaissance satellite program.
The Agena served as an upper stage for several defense, intelligence, and exploration programs:  SAMOS-E, SAMOS-F (ELINT Ferret)  and MIDAS (Missile Defense Alarm System) military early-warning satellites, Corona photo intelligence program, and the Ranger and Lunar Orbiter lunar probes.

The Lockheed Agena target vehicle using the Bell 8247 engine was qualified for 15 restarts for NASA's Project Gemini.

A total of 365 Agena rockets were launched by NASA and the U.S. Air Force between February 28, 1959, and the last Agena D launched on 12 February 1987, configured as the upper stage of a Titan 34B.

Development
During the spring of 1963, Grumman hired Bell to develop the lunar module ascent engine, on the assumption that Bell's experience in development of the Air Force Agena engine would be transferable to the lunar module requirements. Grumman placed heavy emphasis upon high reliability through simplicity of design, and the ascent engine emerged as the least complicated of the three main engines in the Apollo space vehicle, including the LM descent and CSM service propulsion system engines.

Embodying a pressure-fed fuel system using hypergolic (self-igniting) propellants, the ascent engine was fixed-thrust and nongimbaled, capable of lifting the ascent stage off the Moon or aborting a landing if necessary.

The engine developed about  of thrust, which produced a velocity of 3,200 meters per second from lunar launch, to LOR, and CM docking.

RS-18 Engine

Rocketdyne brought the lunar module ascent engine out of its 36-year retirement in 2008 for NASA's Exploration Systems Architecture Study (ESAS) engine testing, re-designated it as RS-18, and reconfigured the non-throttleable hypergolic engine to use LOX/methane.

References

External links 

Rocket engines using hypergolic propellant
Apollo program hardware
Spacecraft propulsion
Rocket engines using the pressure-fed cycle
RS-18. The RS-18 is a reconfigured version of the Rocketdyne Lunar Module Ascent Engine (LMAE), modified to burn liquid oxygen (LOX) and liquid methane (CH4) for NASA's Exploration Systems Architecture Study (ESAS) engine testing in 2008.

Development
The 2005 NASA Exploration Systems Architecture Study (ESAS), part of the 2004 Vision for Space Exploration, recommended that the crew exploration vehicle (CEV) lunar surface access module (LSAM) ascent stage propulsion and service module propulsion systems employ a pressure-fed LOX/liquid methane (CH4) engine.

"Green" propellants, such as LOX and liquid methane, offer savings in both performance and safety over equivalently sized hypergolic propulsion systems in spacecraft applications such as ascent engines or service module engines.

The mass savings over monomethyl hydrazine (MMH) and nitrogen tetroxide (N2O4) were around 1,000 - 2,000 lb (450 – 910 kg) for the LSAM ascent module, which was larger than the current design.

The thrust levels identified in ESAS were 5,000 - 10,000 lbf (22 - 44 kN) for the ascent engine.

To remove key technology risks in the decision for hypergolic or LOX/Methane, the Propulsion and Cryogenics Advanced Development (PCAD) project is being conducted within NASA, led by the Glenn Research Center, for 5,500 lbf (24,500 N) ascent engine technology.

Progress
The RS-18 rocket engine was tested using LOX and liquid methane under simulated altitude conditions at NASA Johnson Space Center White Sands Test Facility (WSTF). This project is part of NASA's Propulsion and Cryogenics Advanced Development (PCAD) project.

Altitude simulation was achieved using the WSTF Large Altitude Simulation System, which provided altitude conditions equivalent up to —122,000 ft (~ 37 km).
The RS-18 gas spark-torch igniters were designed and supplied by Pratt and Whitney Rocketdyne as part of the LOX/Methane RS-18 test program.
Pyrotechnic ignition was not attempted on the RS-18, but was subsequently successfully demonstrated as part of the 2009 Armadillo Aerospace IPP engine testing.

The RS-18 engine was not selected for the Constellation program, and that NASA program was eventually cancelled on February 1, 2010.

References

Rocket engines using methane propellant
Rocketdyne engines
Rocket engines using the pressure-fed cycle
Rocket engines of the United States