omniomni/omni-engineering huggingface dataset:
Kingsford Smith PL.7. 

The Kingsford Smith PL.7 was an Australian agricultural aircraft designed by Luigi Pellarini and built in the 1950s by Kingsford Smith Aviation Service.

Design and development
The PL.7 was basically a welded steel tank for the pilot and chemical hopper, on the front was mounted a  Armstrong Siddeley Cheetah X radial engine. It was an unequal span biplane with a tail unit supported by twin booms from the upper wings and a fixed tricycle landing gear.

Specifications

References

Notes

Bibliography

1950s Australian agricultural aircraft
Biplanes
Single-engined tractor aircraft
Aircraft first flown in 1956
Sodium tungsten bronze. Sodium tungsten bronze is a form of insertion compound with the formula NaxWO3, where x is equal to or less than 1. So named because of its metallic lustre, its electrical properties range from semiconducting to metallic depending on the concentration of sodium ions present; it can also exhibit superconductivity.

History
Prepared in 1823 by the chemist Friedrich Wöhler, sodium tungsten bronze was the first alkali metal bronze to be discovered.
Tungsten bronzes owe some of their properties to the relative stability of the tungsten(V) cation that is formed. A similar family of molybdenum bronzes may have been discovered in 1885 by Alfred Stavenhagen and E. Engels, but they are formed in a very narrow range of temperatures and were not reported again until the 1960s.

Properties
Sodium tungsten bronze, like other tungsten bronzes, is resistant to chemical reaction under both acidic and basic conditions. Colour is dependent upon the proportion of sodium in the compound, ranging from golden at x ≈ 0.9, through red, orange and deep purple, to blue-black when x ≈ 0.3.

The electrical resistivity of the bronze depends on the proportion of sodium in the compound, with specific resistances of 1.66 mΩ being measured for some samples. It has been suggested that electrons, released when the sodium atoms are ionised, are conducted readily through the tungsten t2g and oxygen π orbitals. This can be observed in the XPS and UPS spectra: the peak representing the tungsten 5d band becomes more intense as x rises.

For values of x below 0.3, the bronze is semiconducting rather than metallic. When cooled sufficiently, sodium tungsten bronze becomes a superconductor, with the critical temperature (Tc) for Na0.23WO3 being approximately 2.2 kelvin. The first record of superconductivity in a tungsten bronze was in 1964, with a Tc of 0.57 K.

Structure

When x = 1, sodium tungsten bronze adopts a cubic phase: the perovskite crystal structure. In this form, the structure consists of corner-sharing WO6 octahedra with sodium ions in the interstitial gaps. For x values between 0.9 and 0.3, the structure remains similar but with an increasing deficiency of sodium ions and a smaller lattice parameter.

A number of other structure types can also be adopted, with varying electrical properties: cubic, tetragonal I and hexagonal phases are metallic, whereas orthorhombic and tetragonal II structures are semiconducting.

Synthesis
Wöhler's 1823 synthesis involved reducing sodium tungstate and tungsten trioxide with hydrogen gas at red heat. A more modern approach reduces a melt of the reactants with electricity rather than with hydrogen. Microwave synthesis is also possible, using tungsten powder as the reducing agent. Hydrothermal (both batch and flow) syntheses are also possible.

Related compounds
The sodium in this compound can be replaced by other alkali metals to form their tungsten bronzes, and by other metals such as tin and lead. Molybdenum bronzes also exist but are less stable than their tungsten counterparts.

References

Non-stoichiometric compounds
Sodium compounds
Tungsten compounds
Oxides
British Engineering Excellence Awards. The British Engineering Excellence Awards (BEEAs) were established in 2009 as a means to demonstrate the high calibre of engineering design and innovation within the UK. Small and large British companies are encouraged to submit their entries into the appropriate categories for consideration. Here they compete on a level playing field where the quality of engineering design is the primary factor.

Organised by Dartford based Eureka and New Electronics, the BEEAs have received support from individuals with a vested interest in the future of UK engineering, such as Richard Nobel (Director of The BLOODHOUND Project) and Kate Bellingham.

The most prestigious award offered by the BEEAs is the British Engineering Excellence Grand Prix, chosen by judges from winning entries in the programme. In 2009 the award was received by Flybrid Systems, and then in 2010 by Andrew Burrows of i20 Water.

The Judges’ Special Award, an award issued at the judges’ discretion to an entrant of any of the award categories, was received in 2009 by Lotus Engineering and then by Dexela in 2010.

Categories
The award categories for the BEEAs are as follows:

 Design Engineer of the Year
 Young Design Engineer of the Year
 Consultancy of the Year
 Small Company of the Year
 Start Up of the Year
 Green Product of the Year
 New Product of the Year (Electronic)
 New Product of the Year (Mechanical)
 Mechatronic Design of the Year
 British Engineering Excellence Grand Prix
 Judges’ Special Award

Venue
The venue for the British Engineering Excellence Awards has been the UnderGlobe in London’s Shakespeare’s Globe Theatre and, as of the 2015, The Hurlingham Club.

See also

 List of mechanical engineering awards

References

External links
 

British science and technology awards
Mechanical engineering awards
Recurring events established in 2009
2009 establishments in the United Kingdom
RagWing RW9 Motor Bipe. The RagWing RW9 Motor Bipe is a family of single seat, open-frame fuselage, open-cockpit, single engine ultralight aircraft designed by Roger Mann and sold as plans by RagWing Aircraft Designs for amateur construction.

Design and development
The RW9 was designed as an FAR 103 Ultralight Vehicles compliant biplane that would have an empty weight within that category's  empty weight limit. The RW9 achieves its light weight in part due to its completely open-frame tube fuselage.

The RW9's wings are constructed entirely from wood and covered with aircraft fabric. The fuselage is a fastened aluminum tube truss construction. The landing gear is of conventional configuration. The aircraft's installed power range is  and the standard engine is the  Kawasaki 440A installed in tractor configuration. The  2si 460 has also been used.

The RW9 is available only as plans and reported construction time is 150–175 hours.

The same basic airframe design was also used to produce the parasol wing RagWing RW16 Aerial.

Variants
RW9 Motor Bipe
Open-frame fuselage, open-cockpit ultralight biplane first flown in 1995 and powered by a  Kawasaki 440A or a  2si 460.
RW16 Aerial
Open-frame fuselage, open-cockpit ultralight parasol wing aircraft, powered by a  Kawasaki 340.

Specifications (RW9)

See also

References

External links
Official website - RW9
Official website - RW16

1990s United States ultralight aircraft
Motor Bipe
Biplanes
Single-engined tractor aircraft
Single-engined piston aircraft
Aircraft with fixed conventional landing gear
SNCAC NC.4-10. The SNCAC NC.4-10 was a twin-engine floatplane torpedo bomber built in France in the late 1930s. It was one of several prototypes competing for a Navy specification but no contracts were awarded after the military lost interest in the type.

Design and development
The Farman F.410 was designed in 1934, before the part-nationalisation of the French aircraft industry in 1936-7 brought Farman and Hanriot together as the Société Nationale de Constructions Aéronautiques du Centre (SNCAC). The design anticipated the government specification MT/CPT-9 for a "combat scout seaplane" for the Forces Aériennes de Mer, which was circulated amongst manufacturers in May 1935. Farman revised the F.410 to accommodate this specification and four other French manufacturers also built prototypes to it. There were further changes to MT/CPT-9 in March 1937. Post-nationalisation, the F.410 was renamed the SNCAC NC.4-10.

The twin engine NC.4-10 was an all-metal aircraft. It had low-set wings with a rectangular centre section, tapering outboard of the engines. The fuselage was flat sided and tapered aft to a high set tailplane. This carried inboard twin fins, tall and straight tapered, on top of it. The pilots' cabin was above the wing leading edge and the deep nose was largely glazed. There were three machine gun and one Hispano cannon positions. The two long floats were each mounted on a pair of near vertical faired struts, with further cross bracing.

Originally the F.410 was designed to be powered by two Hispano 12 Ybrs, a V-12 engine then in its early development phase. When the NC.4-10 first flew, piloted by Lucian Coupet on 10 July 1939, it was powered instead by a pair of 890 hp (635 kW) Gnome-Rhône 14Knrs/ors 14-cylinder radials, mounted on the upper wing surface. After a few flights, these proved to be poorly cooled and to be prone to crankshaft failure, so they were replaced with 1050 hp (780 kW) Gnome-Rhône 14 N1/N2 radials.

The NC.4-10 initially flew as a landplane, using a temporary fixed conventional undercarriage. It flew to Marignane on the Côte d'Azur on 22 August 1939, where it was fitted with floats, and made its first take-off on floats from the Étang de Berre on 12 September, flown by Louis Giraud.

Conversely, the Admiralty had changed its mind and chosen to abandon the floatplane in favour of landplanes, ordering the Lioré et Olivier LeO 45. The seaplanes of specification MT/CPT-9 ultimately remained in use for miscellaneous tasks, the NC.4-10 going to St Raphael for tests of speed, service ceiling and range. As World War II developed, the aircraft was moved to avoid the now-encroaching axis forces; on 18 May 1940, the NC.4-10 translated to Biscarrosse on the west coast of France, to escape imminent Italian attacks on the south coast. In mid-June, with German task forces closing in, the aircraft was flown to the Gulf of Bougie in North Africa. Its ultimate fate is not recorded.

Specifications

See also

References

Bibliography

Floatplanes
SNCAC NC.04-10
Farman aircraft|F.410
040
Low-wing aircraft
Aircraft first flown in 1939
Twin piston-engined tractor aircraft
JCB HMEE. The JCB HMEE (High Mobility Engineer Excavator) is a military engineering vehicle made by JCB.

Design
The HMEE is an armoured backhoe loader designed for high speeds in order to self-deploy with military convoys. Most backhoes are limited to much lower speeds. It is also capable of towing heavy loads and has good off-road mobility. It is based on technology from the JCB Fastrac tractors.

The HMEE is built at JCB's plant in Pooler, Georgia, integrating armour made by American Defense Systems (ASDI).

Specifications
Engine: Cummins QSB 6.7
Weight:  armoured,  unarmoured
Speed: Up to

Users
 Australian Army: 8 vehicles
 Belgian Army: ~4 vehicles
 British Army: 17 vehicles
 German Army: 7 vehicles
 Danish Army: 6 vehicles
 Irish Defence Forces : 1 vehicle
 Israel Defense Forces
 New Zealand Army: 6 vehicles
 Spanish Army: 4 vehicles
 Swedish Army: 22 vehicles
 US Army: 800 vehicles
 Armed Forces of Ukraine

References

External links

Military engineering vehicles
GTR-18 Smokey Sam. The GTR-18A, commonly known as the Smokey Sam, is a small unguided rocket developed by Naval Air Warfare Center Weapons Division (NAWCWD) in China Lake, California as a threat simulator for use during military exercises. Widely used in training, the Smokey Sam remains in operational service with the United States military.

Design and development
The GTR-18 was conceived in the late 1970s by Robert A. McLellan, a Weapons Range Scientist working with Exercise Red Flag at Nellis Air Force Base.  He first searched for a commercially available system that would perform as he envisioned.  It quickly became apparent that no commercial product would perform adequately, so the development of the GTR-18 was undertaken by the Naval Weapons Center (NWC) during the early 1980s, with the intent of developing Mr. McLellan's idea of a simple and inexpensive rocket for visually simulating the launch of surface-to-air missiles (SAMs) during training exercises.

The design of the GTR-18A rocket is very simplistic and intended for minimal cost with the fuselage and nose cone being constructed from phenolic paper while the fins are constructed out of styrofoam. The fuselage and fins are joined to the nose cone by the motor tube which contains  of X-60 solid fuel propellant. Because of its very light construction, the Smokey Sam will only cause minimal damage even if it accidentally strikes a low-flying aircraft.

Operational history

The complete launch system, known as the Smokey Sam Simulator, includes single-rail  LMU-23/E and four-rail LMU-24/E launching pads, an AN/VPQ-1 radar set, the PVU-3A/E Igniter and the GTR-18A rockets themselves, making up the SMU-124/E system as a whole.

When launched, the GTR-18's rocket motor produces a distinctive white plume, providing a realistic simulation of the launch of a surface-to-air missile. While the ordinary GTR-18A has a simple, model rocket type motor, an improved "Dual Thrust Smokey Sam" tested in the early 2000s featured a modified rocket motor, providing a 1.5 second boost period, followed by a lower-thrust sustainer burn with burnout occurring at 7.1 seconds after launch.

This motor was altered to use a two-part laminated grain propellant which utilized both the standard zinc based grain and a high thrust aluminium based grain as used by other US rockets. The new propellant allows the "Dual Thrust Smokey Sam" to have a boost and sustain signature to better imitate a surface-to-air missile and while thrust is initially low, the higher thrust for the majority of the motors burn time gives an improved trajectory.

The Smokey Sam remains in production and operational service, and is extensively used by the U.S. military.

Gallery

Notes

References

Bibliography

External links
  Webpage covering the GTR-18A

Military specifications 
  GTR-18A
  SMU-124/E

Surface-to-air missiles of the United States
Rocket weapons of the United States
Model rockets
Military equipment introduced in the 1980s
MQR-13 BMTS. The XMQR-13A Ballistic Missile Target System (BMTS) was an unguided target rocket developed by the United States Army during the 1960s, intended for use in the development of missile defense systems. Utilising off-the-shelf parts in four different configurations, the BMTS was utilised in a series of launches in the late 1960s supporting tests of several missile systems.

Design and development
Developed by the U.S. Army Missile Command (USAMICOM), the Ballistic Missile Target System, or BMTS, was intended as a ballistic target rocket, utilising as many parts from existing missiles as possible, to be used in the development and evaluation of defense systems against ballistic missile attack.

Given the designation XMQR-13A in 1967, the BMTS could be launched in four different configurations. Configuration 1 used the booster from a Nike Ajax surface-to-air missile, with either an Apache (Version 1), Cajun (version 2), or inert Cajun (version 3) upper stage. Configuration 2 omitted the upper stage. All four variations fitted a radar enhancer in the nose cone to assist in target acquisition by the targeting missile.

Operational history
The XMQR-13A was used in a series of test firings between 1966 and 1968, primarily from the White Sands Missile Range, and using a modified Terrier portable launcher. The test launches supported a variety of antimissile development programs, including that of the HAWK, and was intended for use in the development of SAM-D.

The Nike-Apache and Nike-Cajun rocket configurations were also use extensively as sounding rockets for experimental missions conducted by NASA.

See also
Nike-Apache
Nike-Cajun

References

Notes

Bibliography

Target missiles
Cold War rockets of the United States
Military equipment introduced in the 1960s
Pratt & Whitney R-2060 Yellow Jacket. The Pratt & Whitney R-2060 Yellow Jacket was a liquid-cooled aircraft engine project developed for the United States Army in the early 1930s. The engine had five banks of four in-line cylinders, and displaced 2,060 cubic inches. Designed to produce 1,000 hp, the engine produced 1,116 hp on its final run after 35 hours of testing. The engine was cancelled in favor of continuing development of Pratt & Whitney's air-cooled R-1830 Twin Wasp radial engine.

Specifications (R-2060)

See also

References
Notes

Bibliography

External links
 Photos of the XR-2060 at enginehistory.org

R-2060
1930s aircraft piston engines
Escalera de los Moros. The Escalera de los Moros (Moors ladder) is a medieval-Islamic public building works aimed at a Dam or wetland located on the promenade of the Oron river outside the village of Librilla, Murcia, Spain.

Description 
Served a lowering of water from a stream to Weir of the promenade with a phased revosadero explains the place name by which he is known. Made in ashlar masonry typical of Arabic is a curious construction of hydraulic works in made in the Islamic period. Given the difficult access its state of preservation is excellent and is quite unknown to the researchers, although of great importance for the study of Islamic irrigation in the area.

External links 
 https://web.archive.org/web/20110725194848/http://contraclave.org/historia/CONGRESO%20IDENTIDAD/comunicaciones/Fernando%20Barquero%20patrimonio.pdf

Buildings and structures in the Region of Murcia
RagWing RW11 Rag-A-Bond. The RagWing RW11 Rag-A-Bond is a two-seat, high wing, strut-braced, conventional landing gear, single engine homebuilt aircraft designed by Roger Mann and sold as plans by RagWing Aircraft Designs for amateur construction.

The RW11 is a replica of the Piper PA-15 Vagabond.

Design and development
The RW11 was designed for the US experimental homebuilt aircraft category or as a US FAR 103 Ultralight Vehicles two-seat ultralight trainer and first flown in 1996.

The airframe is constructed entirely from wood and covered with aircraft fabric. The landing gear is of conventional configuration with bungee suspension. The cabin is internally  wide and drooped STOL style wingtips are optional. The aircraft's installed power range is  and the standard engine is the  Rotax 503, although the  2si 690 and  Subaru EA-81 engines have also been used.

The RW11 is only offered as plans and the designer estimates it will take 500 hours to complete the aircraft.

Specifications (RW11)

References

External links

Homebuilt aircraft
High-wing aircraft
Aircraft first flown in 1996
Rag-A-Bond
Single-engined tractor aircraft
Single-engined piston aircraft
Aircraft with fixed conventional landing gear
New Avio C205. The New Avio C205 is an aerobatic ultralight aircraft, seating two in tandem and produced by New Avio, Gruppo NewCar of Italy.

Design and development
The C205 is a low wing, single engine aircraft with a retractable conventional undercarriage. It has a wooden structure with a mixture of wood and carbon composite skinning. The low, trapezoidal wings, built around two spars, are entirely wooden apart from Kevlar reinforced leading edges. They have Hoerner-type tips; the trailing edge carries ailerons and electrically driven flaps. The main undercarriage legs are attached to the main spar and have a track of .  The main gear is retracted hydroelectrically; the tailwheel is fixed.

The fuselage has a wooden structure, reinforced with steel plates and roll-bar, and tapers to the rear. The fin and rudder are straight edged, tapered and swept; the rudder and elevators are all horn balanced. A long, single piece canopy covers both seats, with a separate windscreen. Ahead, the engine is under a polycarbonate cowling: the standard power plant is a  Rotax 912 UL flat four, driving a variable-pitch propeller with a choice of two or three blades.

The C205 can be built from kits, with two levels of pre-completion.

Operational history

By mid-2010 there were at least four C205s on the European registers, all Italian.  Three of these have been used by the aeroclub at Trevi, where New Avio is based. They have been flown by the three-man Walter's Bad aerobatic team.

Variants
C205
Original model
C205 Evo
Flying by 2007

Specifications (Evo)

References

2000s Italian sport aircraft
Low-wing aircraft
Single-engined tractor aircraft
Power Tower (Linz). The Power Tower is the first high-rise office tower to attempt to meet the strict Passive House energy efficiency building standard.  It was built to house the corporate headquarters of the Austrian utility company Energie AG in Linz, Austria.

In accordance with the Passive House standard the building has no connection to the local district heating system, and requires no fossil fuel inputs to maintain a comfortable interior climate, resulting in much lower carbon dioxide emissions than comparable buildings.

History 
In 2004 Energie AG decided to replace its corporate headquarters, built in the 1930s, with a much more efficient building.  After an architectural competition the Zürich firm Weber/Hofer was chosen to lead the design effort.  In the spring of 2006 construction began on the 3,750 m^2 lot.  The site houses a parking garage, a two story building, and the 19-story office tower.  Construction was completed in the late summer of 2008, and the building now provides offices for 600 employees of 13 different companies.

Building Energy Systems 
The Power Tower minimizes its external energy consumption via several integrated systems.

Advanced Building Envelope 
The building envelope was specially engineered to allow maximum daylighting while minimizing solar gain, which would normally be excessive and require a great deal of active cooling, given that two thirds of the facade is composed of glazing.

Geothermal Heating and Cooling 
Beneath the building, 46 geothermal wells, each 150 m deep were drilled prior to construction.

References

External links 
 Energie AG Oberösterreich

Low-energy building
Sustainable buildings and structures
Sustainable architecture
Environmental design
Buildings and structures in Linz
Skyscraper office buildings in Austria
Office buildings completed in 2008
SNCASE SE-400. The SNCASE SE-400 was a prototype French twin-engined coastal patrol floatplane of the Second World War. A single example was flown, but development was abandoned in May 1940 owing to the German invasion of France.

Design and development

In 1937 the French Air Ministry issued specification A46 for a three-seat coastal reconnaissance seaplane to replace the obsolete CAMS 37 biplane flying boats of the French Navy. To meet this requirement, the Société Nationale des Constructions Aéronautiques du Sud-Est (SNCASE) designed a twin-engined monoplane floatplane, the SE-400, work beginning on construction of two prototypes in March 1938.

The SE.400 was of mixed construction, with a steel tube fuselage and wooden wings. It had a twin tail and was powered by two 655 hp (489 kW) Gnome-Rhône 14M radial engines. The aircraft's undercarriage consisted of two light alloy floats mounted beneath the engines.

Operational history
The first prototype, the SE.400-01 made its maiden flight from Marignane on 31 December 1939. Flight testing showed that the SE-400 suffered from stability problems, and the aircraft had a new, larger, tail assembly fitted and its nose lengthened. These modifications resolved the aircraft's handling problems, but by this time the competing Breguet Nautilus had been ordered into production.

The war situation and the continuing delays in the program resulted in the development of the SE-400 being abandoned on 24 May 1940, with the second prototype, a landplane powered by two  Lorraine 9N Algol engines, left incomplete. The first prototype was found by Italian troops at Vitrolles, but while the aircraft's engines and propellers were removed, the rest of the aircraft remained intact until 1945.

Operators

French Navy

Specifications

See also

Notes

References

External links
Aviafrance

1930s French military reconnaissance aircraft
SE-0400
Floatplanes
Low-wing aircraft
Aircraft first flown in 1939
Twin piston-engined tractor aircraft