The Bell Aerosystems Lunar Landing Research Vehicle (LLRV, nicknamed the Flying Bedstead*) was a Project Apollo era program to build a simulator for the Moon landings. The LLRVs were used by the FRC, now known as the NASA Armstrong Flight Research Center, at Edwards Air Force Base, California, to study and analyze piloting techniques needed to fly and land the Apollo Lunar Module in the Moon's low gravity environment.

The research vehicles were vertical take-off vehicles that used a single jet engine mounted on a gimbal so that it always pointed vertically. It was adjusted to cancel 5/6 of the vehicle's weight, and the vehicle used hydrogen peroxide rockets which could fairly accurately simulate the behavior of a lunar lander.

Success of the two LLRVs led to the building of three Lunar Landing Training Vehicles (LLTVs), an improved version of the LLRV, for use by Apollo astronauts at the Manned Spacecraft Center in Houston, Texas, predecessor of NASA's Johnson Space Center. One LLRV and two LLTVs were destroyed in crashes, but the rocket ejection seat system safely recovered the pilot in all cases.

The final phase of every Apollo landing was manually piloted by the mission commander. Because of landing site selection problems, Neil Armstrong, Apollo 11 commander, said his mission would not have been successful without extensive training on the LLTVs. Selection for LLTV training was preceded by helicopter training. In a 2009 interview, astronaut Curt Michel stated, "For airborne craft, the helicopter was the closest in terms of characteristics to the lunar lander. So if you didn't get helicopter training, you knew you weren't going. That sort of gave it away." Even Tom Stafford and Gene Cernan did not get LLTV training for their Apollo 10 mission which was the first flight of the Lunar Module to the Moon, because NASA "didn't have plans to land on Apollo 10" so "there wasn't any point in ... training in the LLTV." Cernan only got this training after being assigned as backup commander for Apollo 14, and in 1972 was the last to fly the LLTV while training as commander for Apollo 17, the final landing mission.

Built of aluminum alloy trusses, the LLRVs were powered by a General Electric CF700-2V turbofan engine with a thrust of 4,200 lbf (19 kN), mounted vertically in a gimbal. The engine lifted the vehicle to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen peroxide lift rockets with thrust that could be varied from 100 to 500 lbf (440 to 2,200 N) handled the vehicle's rate of descent and horizontal movement. Sixteen smaller hydrogen peroxide thrusters, mounted in pairs, gave the pilot control in pitch, yaw and roll.

For more details on the history, and the LLTV, click here.

(* Note: Another experimental machine built in the UK was also called the Flying Bedstead. It was designed for research VTOL and was the forerunner to the P.1127 and Hawker Harrier aircraft.)

The McDonnell 119/220 is a business jet developed and unsuccessfully marketed by McDonnell Aircraft in the late 1950s and early 1960s. Its configuration is unique for this type of aircraft, with four podded engines underneath a low wing. It is the only airplane built by McDonnell Aircraft to be marketed to civil buyers prior to the company's merger with Douglas Aircraft to form McDonnell Douglas. The jet could be outfitted for 10 passengers in a luxury executive configuration and could carry as many as 29.

The Model 119 was designed in 1957 for the U.S. Air Force's UCX (Utility-Cargo Experimental) contract announced in August 1956, competing with the Lockheed JetStar. McDonnell entered the UCX competition with an eye on commercial sales; the company had never produced a civil aircraft. 

Designed for a 2,200 nmi (2,500 mi; 4,100 km) range at 550 kn (630 mph; 1,020 km/h) airspeed against a 70 kn (81 mph; 130 km/h) headwind, the 119 had a wing sweep of 35 degrees and a vertical stabilizer sweep of 45 degrees. Critical field length on takeoff was 3,930 ft (1,200 m) to 5,255 ft (1,602 m), while the advertised landing roll was 1,800 ft (550 m) to 2,050 ft (620 m). Roll control was provided by conventional ailerons, a combination of split flaps and Fowler flaps were used to enhance low-speed control, and the wings were equipped with spoilers that doubled as speed brakes. The cabin floor had tracks to allow interior fitments to be changed quickly to suit different missions; the aircraft could be used for medical evacuation, with room for 12 stretchers and two attendants, and McDonnell also promoted it as a trainer for bombardiers, flight navigators, radar operators, or electronic countermeasure technicians. Having invested over $10 million in company funds in the program, McDonnell initiated the formation of commercial sales and transport divisions to promote the 119, but company founder James Smith McDonnell was unwilling to commit to full-scale production until sizable orders were received.  

Completion of the prototype was delayed until 1959 due to the cancellation of the intended Fairchild J83 engine. Fitted with Westinghouse J34 turbojets for flight test purposes, the 119 was first flown on 11 February 1959, but the Air Force rejected it later that year in favor of the Lockheed JetStar (designated C-140), citing concerns about foreign object damage with the 119's low-mounted engines. Following this setback, McDonnell continued to market the type commercially, renaming it the 220 to commemorate McDonnell's second 20 years of business, and showing it in a 10-place luxury configuration and a more basic configuration with 29 passenger seats. McDonnell drew up plans to equip production models with more modern Pratt & Whitney JT12 or General Electric CF700 engines, and the 220 was awarded a Federal Aviation Administration (FAA) type certificate on 17 October 1960.

The company made a provisional deal with Pan American World Airways to lease 170 of the jets, but no other orders materialized, and McDonnell was ultimately unable to offer the aircraft to Pan Am at an attractive price; consequently, the airline rejected the aircraft in favor of the Dassault-Breguet Mystère 20, and no further production ensued. The McDonnell Corporation subsequently used the prototype as a VIP transport before selling it in March 1965 to the Flight Safety Foundation, which used it for crash survival tests and other research in Phoenix, Arizona. The jet was subsequently rumored to have been used for covert missions in Latin America before winding up derelict in Albuquerque.

As of 2019, the single prototype was still extant, registered as N4AZ and stored at El Paso International Airport.[7] FAA records show that in January of 2022, the aircraft was sold. Registration certificate issued 28 Jan 2022, expiring 31 Jan 2025.

The McDonnell XF-85 Goblin is an American prototype fighter aircraft conceived during World War II by McDonnell Aircraft. It was intended to deploy from the bomb bay of the giant Convair B-36 bomber as a parasite fighter. The XF-85's intended role was to defend bombers from hostile interceptor aircraft, a need demonstrated during World War II. McDonnell built two prototypes before the Air Force (USAAF) terminated the program.

The XF-85 was a response to a USAAF requirement for a fighter to be carried within the Northrop XB-35 and B-36, then under development. This was to address the limited range of existing interceptor aircraft compared to the greater range of new bomber designs. The XF-85 was a diminutive jet aircraft featuring a distinctive egg-shaped fuselage and a forked-tail stabilizer design. The prototypes were built and underwent testing and evaluation in 1948. Flight tests showed promise in the design, but the aircraft's performance was inferior to the jet fighters it would have faced in combat, and there were difficulties in docking. The XF-85 was swiftly canceled, and the prototypes were thereafter relegated to museum exhibits. The 1947 successor to the USAAF, the United States Air Force (USAF), continued to examine the concept of parasite aircraft under three related projects following the cancellation: MX-106 "Tip Tow", FICON, and "Tom-Tom."

During World War II, American bombers such as the Boeing B-17 Flying Fortress, Consolidated B-24 Liberator, and Boeing B-29 Superfortress were protected by long-range escort fighters such as the Republic P-47 Thunderbolt and North American P-51 Mustang. These fighters could not match the range of the Northrop B-35 or Convair B-36, the next generation of bombers developed by the United States Army Air Forces (USAAF). The development cost for longer-ranged fighters was high, while aerial refueling was still considered risky and technologically difficult. Pilot fatigue had also been a problem during long fighter escort missions in Europe and the Pacific, giving further impetus to innovative approaches.

The USAAF considered a number of different options including the use of remotely piloted vehicles before choosing parasite fighters as the most viable B-36 defense. The concept of a parasite fighter had its origins in 1918, when the Royal Air Force examined the viability of Sopwith Camel parasite fighters operating from their 23-class airships. In the 1930s, the U.S. Navy had a short-lived operational parasite fighter, the Curtiss F9C Sparrowhawk, aboard the airships Akron and Macon. Starting in 1931, aircraft designer Vladimir Vakhmistrov conducted experiments in the Soviet Union as part of the Zveno project during which up to five fighters of various types were carried by Polikarpov TB-2 and Tupolev TB-3 bombers. In August 1941, these combinations flew the only combat missions ever undertaken by parasite fighters – TB-3s carrying Polikarpov I-16SPB dive bombers attacked the Cernavodă bridge and Constantsa docks, in Romania. After that attack, the squadron, based in the Crimea, carried out a tactical attack on a bridge over the river Dnieper at Zaporozhye, which had been captured by advancing German troops.[5] Later in World War II, the Luftwaffe experimented with the Messerschmitt Me 328 as a parasite fighter, but problems with its pulsejet engines could not be overcome. Other late-war rocket-powered parasite fighter projects such as the Arado E.381 and Sombold So 344 were unrealized "paper projects".

During wind tunnel testing at Moffett Field, California, the first prototype XF-85 was accidentally dropped from a crane at a height of 40 ft (12 m), causing substantial damage to the forward fuselage, air intake, and lower fuselage. The second prototype had to be substituted for the remainder of the wind tunnel tests and the initial flight tests.

McDonnell test pilot Edwin Foresman Schoch was assigned to the project, riding in the XF-85 while it was stowed aboard the EB-29B, before attempting a "free" flight on 23 August 1948. After Schoch was released from the bomber at a height of 20,000 ft (6,000 m), he completed a 10-minute proving flight at speeds between 180 and 250 mph (290–400 km/h), testing controls and maneuverability. When he attempted a hook-up, it became obvious the Goblin was extremely sensitive to the bomber's turbulence, as well as being affected by the air cushion created by the two aircraft operating in close proximity. Constant but gentle adjustments of throttle and trim were necessary to overcome the cushioning effect. After three attempts to hook onto the trapeze, Schoch miscalculated his approach and struck the trapeze so violently that the canopy was smashed and ripped free and his helmet and mask were torn off. He saved the prototype by making a belly landing on the reinforced skid at the dry lake bed at Muroc. All flight testing was suspended for seven weeks while the XF-85 was repaired and modified. Schoch used the down period to undertake a series of problem-free dummy dockings with a Lockheed P-80 Shooting Star fighter.

For further information on this project, click here.

The Messerschmitt Me 321 Gigant was a large German cargo glider developed and used during World War II. Intended to support large scale invasions, the Me 321 saw very limited use due to the low availability of suitable tug aircraft, high vulnerability whilst in flight and the difficult ground handling, both at base and at destination landing sites. The Me 321 was developed, in stages, into the six-engined Messerschmitt Me 323 Gigant, which removed some of the problems with ground handling, but vulnerability to ground fire and aerial attack remained a constant problem during operations of all variants.

When the plans for Operation Sea Lion were shelved in December 1940, and planning began for the invasion of the USSR (Operation Barbarossa), it was decided that the most cost-effective solution to the need for transport aircraft was to use gliders. Accordingly, the Technical Bureau of the Luftwaffe issued a tender for rapid development of a Grossraumlastensegler ("large-capacity transport glider") to the aircraft manufacturers Junkers and Messerschmitt. The specification called for the glider to be capable of carrying either an 88 mm gun plus its tractor, or a medium tank. The codename Projekt Warschau ("Project Warsaw") was used, with Junkers being given the codename Warschau-Ost and Messerschmitt Warschau-Süd.

However, the Junkers design, the Ju 322 Mammut was unsuccessful due to the company opting to use all-wood construction. Messerschmitt's design for this transport glider consequently secured the contract for the company. Initially given the RLM designation: Me 263; this designation number was later reused (see: RLM) for the second generation rocket fighter developed in 1945: Messerschmitt Me 263. That number was 'freed-up' when the number for this aircraft was switched to: Me 321.

The Me 263 had a framework of steel tubing provided by the Mannesmann company, with wooden spars and a covering of doped fabric. This allowed for quick construction and easy repair when needed and also saved weight. The Me 263 was redesignated the Me 321 and was nicknamed Gigant ("Giant") due to its huge size.

Its nose stood over 6 m (20 ft) high, and was made up of two clamshell doors. The doors could only be opened from the inside, when ramps would be used to allow vehicles to drive in or out. Compared to the Ju 52, the Me 321 offered a load area six times larger, at around 100 m2 (1,100 sq ft), and could accommodate a gross cargo weighing up to 23 t (23 long tons). The cargo space had been designed to replicate the load space of a standard German railway flatcar, allowing any cargo that could travel by rail to fit into an Me 321. Alternatively, if used as a passenger transport, 120-130 fully equipped troops could be accommodated.

The Me 321 was fitted with a jettisonable undercarriage comprising two Bf 109 mainwheels at the front and two Junkers Ju 90 main wheels at the rear and was intended to land on four extendable skids.

The first flight of the prototype Me 321 V1 took place on 25 February 1941, towed into the air by a Ju 90. It was piloted by Messerschmitt test pilot Karl Baur, and carried 3 tonnes (3 tons) of ballast. Baur reported that the controls were heavy and responses sluggish. It was decided to enlarge the cockpit to accommodate a co-pilot and radio operator, and dual controls were fitted. Electric servo motors were also fitted to assist in moving the huge trailing edge flaps and further tests caused a braking parachute to also be added.

The test flights were plagued by takeoff difficulties, since the Junkers Ju 90 was not powerful enough, and as an interim measure three Bf 110 heavy fighters were used, in a so-called Troikaschlepp, with the trio of twin-engined fighters taking off together in a V formation. This was a highly dangerous manoeuvre and Ernst Udet asked Ernst Heinkel to come up with a better aerial towing method. Heinkel responded by creating the Heinkel He 111Z Zwilling ("Twins"), which combined two He 111 aircraft through the use of a new "center" wing section with a fifth engine added. Underwing-mount, liquid monopropellant Walter HWK 109-500 Starthilfe rocket-assisted takeoff booster units were also used to assist takeoff from rough fields.

Following the cancellation of the Stalingrad operation, the Me 321 gliders were mothballed, scrapped, or converted into the powered variant, the Me 323 with six 895 kW (1,200 hp) engines, the largest land-based cargo aircraft of World War II. A further proposed operation — in which the remaining Me 321s would have landed troops on Sicily — was also abandoned, due to a lack of suitable landing sites.

Ultimately, 200 Me 321s were produced.

Me 321 Gigant

Me 323 powered Gigant

The Myasishchev VM-T Atlant (Russian: Мясищев ВМ-Т «Атлант», with the "VM-T" ("BM-T") standing for Vladimir Myasishchev – Transport)  was modified to carry rocket boosters and the Soviet space shuttles of the Buran program. It is also known as the 3M-T.

The design was conceived in 1978 when Myasishchev was asked to solve the problem of transporting rockets and other large space vehicles to the Baikonur Cosmodrome. Engineers used an old 3M (a modified M-4 bomber) and replaced the empennage with dihedralled horizontal stabilizers with large, rectangular end-plate tailfins to accommodate payloads measuring as large as twice the diameter of the aircraft's fuselage. A large, aerodynamically optimized cargo container, placed on top of the aircraft, would contain the freight. In addition, a new control system was added to the plane to compensate for the added weight.

The Atlant first flew in 1981 and made its first flight with cargo in January 1982. Its main task was to ferry Energia rocket boosters from their development plant to the Baikonur Cosmodrome. On several occasions, the Soviet space shuttle Buran was piggybacked to the Cosmodrome as well.

Two Atlants were built. They were replaced in 1989 by Antonov's An-225 Mriya. One Atlant (RF-01502) is kept at the Zhukovsky International Airport in Russia owned by TsAGI and Gromov Flight Research Institute, the other one (RA-01402) at Dyagilevo (air base) in Ryazan.

Capacity:
0GT payload container 45,300 kg (99,869 lb) - (38.45 m (126 ft) long, 23.8 m (78 ft) diameter)
1GT payload container 31,500 kg (69,446 lb) - (44.46 m (146 ft) long, 7.78 m (26 ft) diameter)
2GT payload container 30,000 kg (66,139 lb) - (26.41 m (87 ft) long, 7.75 m (25 ft) diameter)
3GT payload container 15,000 kg (33,069 lb) - (16.67 m (55 ft) long, 7.75 m (25 ft) diameter)

The test program at the NASA Dryden Flight Research Center, Edwards California, which successfully demonstrated an aircraft wing that could be pivoted obliquely from zero to 60 degrees during flight.

The unique oblique wing was demonstrated on a small, subsonic jet-powered research aircraft called the AD-1 (Ames-Dryden-1). The aircraft was flown 79 times during the research program, which evaluated the basic pivot-wing concept and gathered information on handling qualities and aerodynamics at various speeds and degrees of pivot.

The AD-1 aircraft was delivered to Dryden in February 1979. The Ames Industrial Co., Bohemia, New York, constructed it, under a US$240,000 fixed-price contract. NASA specified the overall vehicle design using a geometric configuration studied by Boeing Commercial Airplanes, Seattle, Washington. The Rutan Aircraft Factory, Mojave, California, provided the detailed design and load analysis for the intentionally low-speed, low-cost aircraft (there, the aircraft was known internally as the Model 35). The low speed and cost, of course, limited the complexity of the vehicle and the scope of its technical objectives.

The AD-1 was powered by two small Microturbo TRS18-046 turbojet engines, each producing 220 pounds-force (0.98 kN) of static thrust at sea level. These were essentially the same engines used in the BD-5J. The aircraft was limited for reasons of safety to a speed of about 170 mph (270 km/h).

For more details of the project background, aircraft and flight research, click here.

The  NIAI-1 LK-1 was a blended wing four-seat cabin aircraft designed and built in the USSR from 1933. It wa also called the Fanera-2, which translates as  "Plywood no.2", making it hard to search the 'Net for this plane. The design is somewhat unique in that it incorporates a blended wing so that the wing blended into the fuselage, forming the cockpit and cabin. Construction was all of wood/plywood, with a conventional single spar wing with plywood covering. The aircraft had seating for three passengers. It is unclear if the passengers sat three abreast behind the pilot, like galahs on a powerline, or in the usual 2 x 2 arrangement. In any case the blending of the wing into the fuselage, and the nose-mounted engine gave the pilot an asymmetrical view through the leading edge glazing.

The engine was a 5-cylinder radial. The prototype was fitted with a Townsend Ring Cowling, similar in appearance to the USA's NACA cowling for radials. The Townsend Ring was the invention of Dr. Hubert Townsend of the British National Physical Laboratory in 1929. The patents were supported by Boulton & Paul Ltd in 1929. 

Flight trials at Leningrad and state acceptance tests at the NII GVF(Naoochno-Issledovatel'skiy Institoot Grazdahnskovo Vozdooshnovo Flota - "scientific test institute for civil air fleet"), in Moscow, were very successful and an order for twenty production aircraft with modified tails, spats removed, no Townend ring, and other modifications was placed, for use by Aeroflot inside the USSR and the Arctic. One example was fitted with floats, the NIAI-1P – (Poplavkoviy – with floats). is video is from a Russian film in which the plane made a cameo appearance.

vie between timestamps 29:03 and 30:4

The Nord 1500 Griffon was an experimental ramjet-powered interceptor aircraft designed and built by French state-owned aircraft manufacturer Nord Aviation. The Griffon was developed to become a Mach 2 follow on to the supersonic Nord Gerfaut research aircraft. Development of the aircraft began in earnest after the receipt of a letter of intent in 1953 for a pair of unarmed research aircraft. The design featured an innovative dual propulsion turbojet-ramjet configuration; the former being used to takeoff and attain sufficient speed to start the latter.

The first prototype, named Griffon I, made its maiden flight in 1955 and eventually reached a speed of Mach 1.3. Because it lacked the ramjet engine, it was mostly used for exploring the aircraft's aerodynamic properties and its systems. Its flight testing was terminated shortly after the ramjet-equipped Griffon II made its first flight two years later. This aircraft attained a maximum speed of Mach 2.19 and set a world record for a small closed course in 1959. It was last flown in 1961 and currently resides in the Musée de l'air et de l'espace outside Paris, France.

The Nord 1500 Griffon originated from a state-sponsored study into delta and swept wings. To provide data for these studies Arsenal de l'Aéronautique (SFECMAS's nationalised predecessor) built a wooden glider, the Arsenal 1301, that could be fitted with both delta and swept wings and with and without canards. Towed to the release point by SNCAC Martinet, Douglas DC-3 or SNCASE Languedoc transport aircraft, the glider provided valuable data for the design of the Gerfaut.

To utilise this data SFECMAS's chief designer, Jean Galtier, initiated the 1400, 1500 and 1910 interceptor projects with delta wings and different types of propulsion systems. The 1400 developed into the Nord Gerfaut series, the 1500 became the Griffon, while the 1910, ambitiously specified with two large ramjet engines, was never pursued. Galtier envisioned the Griffon as the Mach 2 successor to the supersonic Gerfaut. By this time Arsenal had been privatised as SFECMAS - Société Française d'Etude et de Construction de Matériel Aéronautiques Spéciaux. Powered by a large ramjet with turbojet sustainer, the Griffon was renamed from the SFECMAS 1500 Guépard (Cheetah) after SFECMAS was merged with SNCAN to form Nord Aviation.

For more details of the development and testing of this aircraft, click here.

Variants
SFECMAS 1500 Guépard
The original designation and name of the initial design studies carried out at SFECMAS.
Nord 1500-01 Griffon I
The first aircraft completed with only the SNECMA Atar 101F afterburning turbojet component of the planned turbo-ramjet powerplant.
Nord 1500-02 Griffon II
The second aircraft fitted with the definitive turbo-ramjet powerplant.

 It was operated by the United States Air Force and the National Aeronautics and Space Administration as part of the X-plane series of experimental aircraft. The X-15 set speed and altitude records in the 1960s, reaching the edge of outer space and returning with valuable data used in aircraft and spacecraft design. The X-15's highest speed, 4,520 miles per hour (7,274 km/h; 2,021 m/s), was achieved in October 1967, when William J. Knight flew at Mach 6.70 at an altitude of 102,100 feet (31,120 m), or 19.34 miles. This set the official world record for the highest speed ever recorded by a crewed, powered aircraft, which remains unbroken.

During the X-15 program,12 pilots flew a combined 199 flights. Of these, 8 pilots flew a combined 13 flights which met the Air Force spaceflight criterion by exceeding the altitude of 50 miles (80 km), thus qualifying these pilots as being astronauts. The Air Force pilots qualified for military astronaut wings immediately, while the civilian pilots were eventually awarded NASA astronaut wings in 2005, 35 years after the last X-15 flight.

The X-15 was based on a concept study from Walter Dornberger for the National Advisory Committee for Aeronautics (NACA) for a hypersonic research aircraft. The requests for proposal (RFPs) were published on 30 December 1954 for the airframe and on 4 February 1955 for the rocket engine. The X-15 was built by two manufacturers: North American Aviation was contracted for the airframe in November 1955, and Reaction Motors was contracted for building the engines in 1956.

Like many X-series aircraft, the X-15 was designed to be carried aloft and drop launched from under the wing of a B-52 mother ship. Air Force NB-52A, "The High and Mighty One" (serial 52-0003), and NB-52B, "The Challenger" (serial 52-0008, a.k.a. Balls 8) served as carrier planes for all X-15 flights. Release took place at an altitude of about 8.5 miles (13.7 km) and a speed of about 500 miles per hour (805 km/h). The X-15 fuselage was long and cylindrical, with rear fairings that flattened its appearance, and thick, dorsal and ventral wedge-fin stabilizers. Parts of the fuselage (the outer skin) were heat-resistant nickel alloy (Inconel-X 750). The retractable landing gear comprised a nose-wheel carriage and two rear skids. The skids did not extend beyond the ventral fin, which required the pilot to jettison the lower fin just before landing. The lower fin was recovered by parachute.

For more details on design, propulsion and operational history, click here.

The North American Aviation XB-70 Valkyrie was the prototype version of the planned B-70 nuclear-armed, deep-penetration supersonic strategic bomber for the United States Air Force Strategic Air Command. Designed in the late 1950s by North American Aviation (NAA), the six-engined Valkyrie was capable of cruising for thousands of miles at Mach 3+ while flying at 70,000 feet (21,000 m).

At these speeds, it was expected that the B-70 would be practically immune to interceptor aircraft, the only effective weapon against bomber aircraft at the time. The bomber would spend only a brief time over a particular radar station, flying out of its range before the controllers could position their fighters in a suitable location for an interception. High speed also made the aircraft difficult to see on radar displays and its high-altitude and high-speed capacity could not be matched by any contemporaneous Soviet interceptor or fighter aircraft.

The introduction of the first Soviet surface-to-air missiles in the late 1950s put the near-invulnerability of the B-70 in doubt. In response, the United States Air Force (USAF) began flying its missions at low level, where the missile radar's line of sight was limited by terrain. In this low-level penetration role, the B-70 offered little additional performance over the B-52 it was meant to replace, while being far more expensive with shorter range. Other alternate missions were proposed, but these were of limited scope. With the advent of intercontinental ballistic missiles (ICBMs) during the late 1950s, manned bombers were increasingly seen as obsolete.

The USAF eventually gave up fighting for its production and the B-70 program was canceled in 1961. Development was then turned over to a research program to study the effects of long-duration high-speed flight. As such, two prototype aircraft, designated XB-70A, were built; these aircraft were used for supersonic test-flights during 1964–69. In 1966, one prototype crashed after colliding with a smaller aircraft while flying in close formation; the remaining Valkyrie bomber is in the National Museum of the United States Air Force near Dayton, Ohio.

For details of development, design, operational history and variants, click here.

The Northrop/McDonnell Douglas YF-23 is an American single-seat, twin-engine stealth fighter aircraft technology demonstrator designed for the United States Air Force (USAF). The design was a finalist in the USAF's Advanced Tactical Fighter (ATF) competition, battling the Lockheed YF-22 for a production contract. Two YF-23 prototypes were built, nicknamed "Black Widow II" and "Gray Ghost".

In the 1980s, the USAF began looking for a replacement for its fighter aircraft, especially to counter the USSR's advanced Sukhoi Su-27 and Mikoyan MiG-29. Several companies submitted design proposals; the USAF selected proposals from Northrop and Lockheed. Northrop teamed with McDonnell Douglas to develop the YF-23, while Lockheed, Boeing and General Dynamics developed the YF-22.

The YF-23 was stealthier and faster, but less agile than its competitor. After a four-year development and evaluation process, the YF-22 was announced the winner in 1991 and entered production as the Lockheed Martin F-22 Raptor. The U.S. Navy considered using the production version of the ATF as the basis for a replacement to the F-14, but these plans were later canceled. The two YF-23 prototypes were museum exhibits as of 2010.

For details o the development, design and operational history of the YF-23, clcik here.

 The Oertz W 6 "Flugschoner" or "Flying Schooner" with tandem biplane wings and twin chain driven propellers powered by two Maybach engines in the hull. Information on this aircraft is difficult to come by. From a Russian website:

The pusher propellers powered by two Maybach 240 PS (Hp) engines. The pusher propellers were mounted on a separate construction just behind the front wing.

Although the machine was not very succesfull it was acquired by the German Marine under Number 281.
The other Oertz flying boats were very elegant conventional biplane machines, this was the one out of the box. Probably another designer who wanted to try something a little different.

At a later date mid-wing ailerons were fitted to the rear pair of wings to improve lateral control.

The PZL M-15 was a jet-powered biplane designed and manufactured by the Polish aircraft company WSK PZL-Mielec for agricultural aviation. In reference to both its strange looks and relatively loud jet engine, the aircraft was nicknamed Belphegor, after the noisy demon.

Development of the M-15 can be traced back to a Soviet requirement for a modern agricultural aircraft to succeed the Antonov An-2; it was at the insistence of Soviet officials that jet propulsion would power the type. WSK Mielec's design team recognised the value of the An-2's biplane configuration to the role and set about developing an initial experimental aircraft, the Lala-1, for Latające Laboratorium 1 ("Flying Laboratory 1") to explore the use of a jet engine with such a configuration. On 20 May 1973, the first M-15 prototype performed its maiden flight; even during the test flight phase, it was apparent that there were several drawbacks to the aircraft, including its poor handling, limited range, and high operating costs. While production commenced in 1976, these problems remained unresolved and meant that the M-15 was noticeably inferior in several respects to the An-2. During 1981, production was terminated in favour of procuring more An-2s; a total of 175 M-15s were built against the many thousands which had once been planned.

The PZL M-15 Belphegor was a metal twin-boom sesquiplane. It was intended to be routinely operated by a single pilot, but also had provisions for two additional crew to serve as technicians when deemed necessary. Portions of the lower wings and the chemicals tanks were composed of a laminate to avoid corrosion. The upper and lower wings were connected with two thick columns which housed the chemical tanks. It was outfitted with a fixed tricycle landing gear arrangement. The M-15 was a relatively heavy aircraft, and has been described as being the heaviest biplane to ever be produced.

For the crop-dusting mission, the M-15 could accommodate a payload of just under three tons of pesticides within two sizable pylons that separated its two wings; chemical dispersal was achieved via compressed air. This storage system was relatively unorthodox, the conventional An-2 simply stored these in a single tank housed within the fuselage in a space that could be reused for various other cargoes if not fitted. As such, the arrangement adopted upon the M-15 allowed for no such flexibility and severely limited alternative uses for the aircraft. To avoid the engine exhaust interfering with the dispersal system during release, the engine had to be positioned in a relatively elevated location on top of the fuselage; this was also beneficial to minimise the engine's ingestion of debris, which was a particular problem when operating from austere airstrips.

For more details on development, fligght testing and production, click here.

The design was intended to be a multi-engine aircraft that in the event of failure of a single engine would not become dangerously difficult to control due to asymmetric thrust. The result is an asymmetrical aircraft with a very distinct appearance.

The Boomerang was designed around the specifications of the Beechcraft Baron 58, one of the best known and most numerous twin-engine civilian aircraft. The use of the asymmetrical design allows the Boomerang to fly faster and farther than the Baron using smaller engines, and seating the same number of occupants. The Boomerang is powered by two engines, with the right engine producing 10 hp (8 kW) more power than the left one (the engines are in fact the same model, just rated differently). The wings are forward-swept.

In 1997, avionics entrepreneur Ray Morrow and his son, Neil Morrow, founded an air taxi company. They settled on a modified version of Rutan's Boomerang design, which they designated the MB-300. They determined that the best business approach would be to manufacture the aircraft and run the air taxi services themselves. So Ray Morrow founded Morrow Aircraft Corporation in order to design and manufacture the MB-300. In the meantime, they started the SkyTaxi company using Cessna 414s as interim aircraft. In 1999, Morrow Aircraft Corporation applied to the Federal Aviation Administration (FAA) of the United States for a type certificate for the MB-300. In 2000, the FAA published a notice seeking comments on Morrow Aircraft's proposal to use an electronic engine control system (FADEC) in place of the engine's mechanical system.

Only 1 unit was produced.

Rutan's Boomerang was restored to flying condition in 2011 and made an appearance at Oshkosh that year as part of the Tribute to Rutan.

The Spirit of St. Louis (formally the Ryan NYP, registration: N-X-211) is the custom-built, single-engine, single-seat, high-wing monoplane that was flown by Charles Lindbergh on May 20–21, 1927, on the first solo nonstop transatlantic flight from Long Island, New York, to Paris, France, for which Lindbergh won the $25,000 Orteig Prize.

Lindbergh took off in the Spirit from Roosevelt Airfield, Garden City, New York, and landed 33 hours, 30 minutes later at Aéroport Le Bourget in Paris, France, a distance of approximately 3,600 miles (5,800 km). One of the best-known aircraft in the world, the Spirit was built by Ryan Airlines in San Diego, California, owned and operated at the time by Benjamin Franklin Mahoney, who had purchased it from its founder, T. Claude Ryan, in 1926. The Spirit is on permanent display in the main entryway's Milestones of Flight gallery at the Smithsonian Institution's National Air and Space Museum in Washington, D.C.

Officially known as the "Ryan NYP" (for New York to Paris), the single-engine monoplane was designed by Donald A. Hall of Ryan Airlines and named the "Spirit of St. Louis" in honor of Lindbergh's supporters from the St. Louis Raquette Club in his then hometown of St. Louis, Missouri. To save design time, the NYP was loosely based on the company's 1926 Ryan M-2 mailplane, the main difference being the NYP's 4,000-mile (6,400 km) range. As a nonstandard design, the government assigned it the registration number N-X-211 (for "experimental"). Hall documented his design in "Engineering Data on the Spirit of St. Louis", which he prepared for the National Advisory Committee for Aeronautics (NACA) and is included as an appendix to Lindbergh's 1953 Pulitzer Prize winning book The Spirit of St. Louis.

B.F. "Frank" Mahoney and Claude Ryan had co-founded the company as an airline in 1925 and Ryan remained with the company after Mahoney bought out his interest in 1926, although there is some dispute as to how involved Ryan may have been in its management after selling his share. It is known, however, that Hawley Bowlus was the factory manager who oversaw construction of the Ryan NYP, and that Mahoney was the sole owner at the time of Donald A. Hall's hiring.

The Spirit was designed and built in San Diego to compete for the $25,000 Orteig Prize for the first nonstop flight between New York and Paris. Hall and Ryan Airlines staff worked closely with Lindbergh to design and build the Spirit in just 60 days. Although what was actually paid to Ryan Airlines for the project is not clear, Mahoney agreed to build the plane for $6,000 and said that there would be no profit; he offered an engine, instruments, etc. at cost. After first approaching several major aircraft manufacturers without success, in early February 1927 Lindbergh, who as a U.S. Air Mail pilot was familiar with the good record of the M-1 with Pacific Air Transport, wired, "Can you construct Whirlwind engine plane capable flying nonstop between New York and Paris ...?"

Mahoney was away from the factory, but Ryan answered, "Can build plane similar M-1 but larger wings... delivery about three months." Lindbergh wired back that due to competition, delivery in less than three months was essential. Many years later, John Vanderlinde, chief mechanic of Ryan Airlines, recalled, "But nothing fazed B.F. Mahoney, the young sportsman who had just bought Ryan." Mahoney telegraphed Lindbergh back the same day: "Can complete in two months."

Lindbergh was convinced: "I believe in Hall's ability; I like Mahoney's enthusiasm. I have confidence in the character of the workmen I've met."[citation needed] He then went to the airfield to familiarize himself with a Ryan aircraft, either an M-1 or an M-2, then telegraphed his St. Louis backers and recommended the deal, which was quickly approved.

Mahoney lived up to his commitment. Working exclusively on the aircraft and closely with Lindbergh, the staff completed the Spirit of St. Louis 60 days after Lindbergh arrived in San Diego. Powered by a Wright Whirlwind J-5C 223-hp radial engine, it had a 14 m (46-foot) wingspan, 3 m (10 ft) longer than the M-1, to accommodate the heavy load of 1,610 L (425 gal) of fuel. In his 1927 book We, Lindbergh acknowledged the builders' achievement with a photograph captioned "The Men Who Made the Plane", identifying: "B. Franklin Mahoney, president, Ryan Airlines", Bowlus, Hall and Edwards standing with the aviator in front of the completed aircraft.

Lindbergh believed that multiple engines resulted in a greater risk of failure while a single-engine design would give him greater range. To increase fuel efficiency, the Spirit of St. Louis was also one of the most advanced and aerodynamically streamlined designs of its era.

Lindbergh believed that a flight made in a single-seat monoplane designed around the dependable Wright J-5 Whirlwind radial engine provided the best chance of success. The Ryan NYP had a total fuel capacity of 450 U.S. gallons (1,700 L; 370 imp gal) or 2,710 pounds (1,230 kg) of gasoline, which was necessary in order to have the range to make the anticipated flight non-stop. The fuel was stored in five fuel tanks, a forward tank – 88 U.S. gal (330 L; 73 imp gal), the main – 209 U.S. gal (790 L; 174 imp gal), and three wing tanks – total of 153 U.S. gal (580 L; 127 imp gal).[5] Lindbergh modified the design of the plane's "trombone struts" attached to the landing gear to provide a wider wheelbase in order to accommodate the weight of the fuel.

At Lindbergh's request, the large main and forward fuel tanks were placed in the forward section of the fuselage, in front of the pilot, with the oil tank acting as a firewall. This arrangement improved the center of gravity and reduced the risk of the pilot being crushed to death between the main tank and the engine in the event of a crash. This design decision meant that there could be no front windshield, and that forward visibility would be limited to the side windows. This did not concern Lindbergh as he was accustomed to flying in the rear cockpit of mail planes with mail bags in the front. When he wanted to see forward, he would slightly yaw the aircraft and look out the side. To provide some forward vision as a precaution against hitting ship masts, trees, or structures while flying at low altitude, a Ryan employee who had served in the submarine service installed a periscope which Lindbergh helped design. It is unclear whether the periscope was used during the flight. The instrument panel housed fuel pressure, oil pressure and temperature gauges, a clock, altimeter, tachometer, airspeed indicator, bank and turn indicator, and a liquid magnetic compass. The main compass was mounted behind Lindbergh in the cockpit, and he read it using the mirror from a women's makeup case which was mounted to the ceiling using chewing gum. Lindbergh also installed a newly developed Earth Inductor Compass made by the Pioneer Instrument Company which allowed him to more accurately navigate while taking account of the magnetic declination of the earth. Lindbergh's ultimate arrival in Ireland deviated from his flight plan by just a few miles.

Lindbergh sat in a cramped cockpit which was 94 cm wide, 81 cm long and 130 cm high (36 in × 32 in × 51 in). The cockpit was so small, Lindbergh could not stretch his legs. The Spirit of St. Louis was powered by a 223 hp (166 kW), air-cooled, nine-cylinder Wright J-5C Whirlwind radial engine. The engine was rated for a maximum operating time of 9,000 hours (more than one year if operated continuously) and had a special mechanism that could keep it clean for the entire New York-to-Paris flight. It was also, for its day, very fuel-efficient, enabling longer flights carrying less fuel weight for given distances. Another key feature of the Whirlwind radial engine was that it was rated to self-lubricate the engine's valves for 40 hours continuously. Lubricating, or "greasing," the moving external engine parts was a necessity most aeronautical engines of the day required, to be done manually by the pilot or ground crew prior to every flight and would have been otherwise required somehow to be done during the long flight.

The engine was built at Wright Aeronautical in Paterson, New Jersey by a 24-year-old engine builder, Tom Rutledge, who was disappointed that he was assigned to the unknown aviator, Lindbergh. Four days after the flight, he received a letter of congratulations from the Wright management.

For more information, click here.

The Proteus is actually a multi-mission vehicle, able to carry various payloads on a ventral pylon. Scaled Composites Proteus has an extremely efficient design, and can orbit a point at over 19,800 m for more than 18 hours. It is currently owned by Northrop Grumman.

Proteus has an all-composite airframe with graphite-epoxy sandwich construction. Its wingspan of 77 feet 7 inches (23.65 m) is expandable to 92 feet (28 m) with removable wingtips installed. Proteus is an "optionally piloted" aircraft ordinarily flown by two pilots in a pressurized cabin. However, it also has the capability to perform its missions semi-autonomously or flown remotely from the ground. Under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project, NASA's Dryden Flight Research Center assisted Scaled Composites in developing a sophisticated station-keeping autopilot system and a satellite communications (SATCOM)-based uplink-downlink data system for Proteus' performance and payload data. The Proteus wing was adapted for use on the Model 318 White Knight carrier aircraft, which is the launch system for Rutan's Tier One spacecraft and the DARPA X-37.

Flight testing of the Proteus began with its first flight on July 26, 1998, at the Mojave Airport and continued through the end of 1999. In June, Proteus was deployed internationally for the first time, debuting at the Paris Air Show. It was flown non-stop from Bangor, Maine to Paris. During the week-long show, it flew each day, demonstrating its capabilities as a telecommunications platform.

The Proteus is the current holder of a number of FAI world records for altitude (class: C1-e: landplanes 3,000–6,000 kg, Group: 3, turbojet), set in cooperation with NASA Dryden.[1] The highest altitude achieved was 63,245 feet (19,277 m) in October 2000.

Proteus was included in the list of the "100 Best of 1998 Design", Time Magazine, December 21, 1998.

Number built: 1.

For details of its operational history, click here.

It was announced in December 2011 and rolled out in May 2017. The aircraft features a twin-fuselage design and the longest wingspan ever flown, at 385 feet (117 m), surpassing the Hughes H-4 Hercules flying boat of 321 feet (98 m). The Stratolaunch is intended to carry a 550,000-pound (250 t) payload and has a 1,300,000-pound (590 t) maximum takeoff weight. It should release its rocket at 35,000 ft (11,000 m).

The aircraft flew for the first and so far only time on April 13, 2019, and shortly thereafter, the company announced it would halt development of its air-launched family of launch vehicles following the death of Stratolaunch founder Paul Allen in October 2018. The company ceased operations the next month, and placed all company assets, including the aircraft, for sale for US$400 million by June 2019. Cerberus Capital Management acquired Stratolaunch Systems including the Stratolaunch aircraft in October 2019. Stratolaunch announced in December 2019 that it would now be focusing on offering high-speed flight test services.

Stratolaunch has a twin-fuselage configuration, each 238 ft (73 m) long and supported by 12 main landing gear wheels and two nose gear wheels, for a total of 28 wheels. The twin-fuselage configuration is similar to the Scaled Composites White Knight Two. Each fuselage has its own empennage.

For more details of the history, developent and design of the Stratolaunch, click here.

The Sikorsky S-72 was an experimental compound helicopter developed by helicopter manufacturer Sikorsky Aircraft.

RSRA

The Rotor Systems Research Aircraft (RSRA) was developed by Sikorsky for NASA and the Army. The RSRA was developed to allow the inflight measurement of helicopter rotor characteristics. The airframe was developed using an existing Sikorsky S-61 main rotor, an S-61 roller gearbox, and a highly modified Sikorsky S-67 airframe. The RSRA could be fitted with TF34 turbofans and wings to allow compound helicopter configurations to be experimentally investigated at speeds up to 300 knots (560 km/h). In addition, it could fly as a fixed-wing aircraft without a main rotor.

Unique among helicopters of its time, it was fitted with a crew emergency extraction system. This system, when activated, fired explosive bolts that severed the main rotor blades, escape panels were blown off the roof of the aircraft, then the crew was extracted using rockets.

The RSRA was a unique pure research aircraft developed to fill the void between design analysis, wind tunnel testing, and flight results of rotor aircraft. The joint NASA/Army project began in December 1970, first flight on October 12, 1976 with the first of two aircraft arriving from Sikorsky to NASA on February 11, 1979.

One notable test performed with the RSRA was the use of the main and tail rotor load measurement system to determine the vertical drag of the airframe.

In 1981, NASA and the US Army solicited proposals for fitting a four-bladed main rotor to the RSRA. Sikorsky proposed fitting a UH-60A main rotor to the RSRA in their proposal, while Hughes Helicopters proposed fitting a YAH-64A main rotor and Boeing Vertol proposed fitting a YUH-61A OR Model 347 (four-blade CH-47) main rotor. In the end, this program did not proceed.

The X-Wing

The X-Wing circulation control rotor concept was developed in the mid-1970s by the David W. Taylor Naval Ship Research and Development Center under DARPA funding. In October 1976, Lockheed Corporation won a DARPA contract to develop a large-scale rotor to test the concept.

Intended to take off vertically like a helicopter, the craft's rigid rotors could be stopped in mid-flight to act as X-shaped wings to provide additional lift during forward flight, as well as having more conventional wings. Instead of controlling lift by altering the angle of attack of its blades as more conventional helicopters do, the craft used compressed air fed from the engines and expelled from its blades to generate a virtual wing surface, similar to blown flaps on a conventional platform. Computerized valves made sure the compressed air came from the correct edge of the rotor, the correct edge changing as the rotor rotated.

In late 1983, Sikorsky received a contract to modify one S-72 RSRA into a demonstration testbed for the X-Wing rotor system. The modified airframe was rolled out in 1986 and while many of the aircraft's technical issues had been resolved, with plans for it to begin flight tests with the rotor/wing system, it never flew and budgetary requirements meant that the program was cancelled in 1988.

The X-Wing was conceived as a complement rather than replacement for helicopters and fixed-wing aircraft, intended to be used in roles such as air-to-air and air-to-ground operations, as well as airborne early warning, search and rescue and anti-submarine warfare, as these roles could take advantage of the aircraft's ability to hover and manoeuvre as low speeds while also cruising at high speeds.

The Starr Bumble Bee II was an experimental aircraft designed and built specifically to acquire the title of “The World’s Smallest Airplane”.

The “Bumble Bee II” was designed, and built by Robert H. Starr in Phoenix, Arizona  with the intent of breaking the record for world's smallest biplane. Robert Starr had been deeply involved with the development of aircraft holding previous “smallest airplane” titles, including his own "Bumble Bee I", which lost the record of world's smallest aircraft to the "Baby Bird" designed by Donald Stits. Starr set out to build the Bumble Bee II after he lost the title of world's smallest airplane to the "Baby Bird" designed by Donald Stits. The design of the Bumble Bee II is similar to Starr's original "Bumble Bee I" except the Bumble Bee II was smaller and lighter Both aircraft were biplanes. Both aircraft had negative staggered, cantilevered wings and conventional landing gears. The fuselage of the Bumble Bee II was constructed of welded steel tubing with sheet metal covering, while the wings were covered in aircraft plywood. The power plant was a Continental C85 4 – cylinder air-cooled horizontally opposed cylinder engine (Boxer Motor) that produced 85 hp. The upper wings had flaps and the lower wings had ailerons. All wing airframe structures were equipped with tip plates to enhance the lift coefficient. The airplane had a small cockpit with the rudder pedals located under the engine compartment toward the front of the cowling.

The Bumble Bee I was flown on April 2, 1988, at Marana Airport just outside of Tucson, Arizona to achieve the world record for the smallest piloted airplane. According to the Guinness Book of World Records, the Bumble Bee II crashed and was destroyed during a flight on the 5th of May, 1988. At 400 feet of altitude, the engine failed on a down-wind leg. The crash destroyed the Bumble Bee II and severely injured Robert Starr, who made a full recovery.

Starr named the aircraft after the bumble bee because bumble bees allegedly do not have enough wing area to fly according to standard aerodynamics, and engineers and pilots made a similar statement about Starr's Bumble Bee II.

The Stearman-Hammond Y-1 was a 1930s American utility monoplane built by the Stearman-Hammond Aircraft Corporation and evaluated by the United States Navy and the British Royal Air Force.

In the early 1930s Dean Hammond designed the Hammond Model Y, a low-wing monoplane twin-boom pusher monoplane. Hammond cooperated with the aircraft designer Lloyd Stearman to develop the type for production. They formed the Stearman-Hammond Aircraft Corporation in 1936 to build the aircraft as the Stearman-Hammond Y-1. The first aircraft was powered by a 125 hp (93 kW) Menasco C-4 piston engine driving a pusher propeller. The performance was not impressive so it was re-engined with a 150 hp (112 kW) Menasco C-4S and re-named the Y-1S. Although designed to be easy to fly the high price meant only 20 aircraft were produced. The aircraft had no rudder as such, the tailplane fins being adjustable but fixed in flight. Turning was by differential aileron and elevator alone.

In 1934 the Bureau of Air Commerce held a competition for a safe and practical $700 aircraft. In 1936 the winner of the competition was the Stearman-Hammond Y-1, incorporating many of the safety features of the Ercoupe W-1. Two other winners were the Waterman Aeroplane and a roadable autogyro from the Autogiro Company of America, the AC-35. Twenty-five examples were ordered by the bureau at a price of $3,190 each. The first delivery was considered unacceptable in finish, prompting the production of the re-engineered Y-S model.

Two Y-1S, serial numbers 0908 and 0909,were used for radio controlled development trials by the United States Navy as the JH-1. A successful unmanned radio-controlled flight was made with a JH-1 drone on 23 December 1937 at the Coast Guard Air Station, Cape May, N.J. Take-off and landing was controlled via a land based radio set; for flight maneuvers, control was shifted to an airborne TG-2. KLM purchased a Y-1 (PH-APY) for use in training their pilots in tricycle undercarriage. The Royal Air Force also evaluated a former KLM Y-1S in the 1940s.

Approximately 2o built.

Variants
Hammond Model Y
Prototype for the 1934 Bureau of Air Commerce safe airplane competition.
Stearman-Hammond Y-1
Prototype aircraft with a 125hp (93kW) Menasco C-4 engine.
Stearman-Hammond Y-1S  (Specifications below)
Production aircraft with a 150hp (112kW) Menasco C-4S engine.
JH-1
United States Navy designation for two Y-1S used for tests.

A distinguishing feature of the aircraft was its forward-swept wing that gave the aircraft excellent agility and maneuverability. While serial production of the type never materialized, the sole aircraft produced served as a technology demonstrator prototype for a number of advanced technologies later used in the 4.5 generation fighter Su-35 and current fifth-generation jet fighter Su-57. While only one was built, it is not entirely unique, as it bears a remarkable resemblanc to the Grumman X-29.

Originally known as the S-37, Sukhoi redesignated its advanced test aircraft as the Su-47 in 2002. Officially nicknamed Berkut (Russian: Беркут) (the Russian name for the golden eagle), the Su-47 was originally built as Russia's principal testbed for composite materials and sophisticated fly-by-wire control systems.

The Su-47 is of similar dimensions to previous large Sukhoi fighters, such as the Su-35. To reduce development costs, the Su-47 borrowed the forward fuselage, vertical tails, and landing gear of the Su-27 family. Nonetheless, the aircraft includes an internal weapons bay, and space set aside for an advanced radar.

Like its immediate predecessor, the Su-37, the Su-47 is of tandem-triple layout, with canards ahead of wings and tailplanes. The Su-47 has two tailbooms of unequal length outboard of the exhaust nozzles. The shorter boom, on the left-hand side, houses rear-facing radar, while the longer boom houses a brake parachute.

For more information on the Su-47, click here.

The Terrafugia Transition is a light sport, roadable airplane under development by Terrafugia since 2006. It has been grante a number of exemptions by the FAA to qualfy.

The Rotax 912ULS piston engine powered, carbon-fiber vehicle is planned to have a flight range of 425 nmi (489 mi; 787 km) using either automotive premium grade unleaded gasoline or 100LL avgas and a cruising flight speed of 93 kn (107 mph; 172 km/h). Equipment includes a Dynon Skyview glass panel avionics system, an airframe parachute, and an optional autopilot.

On the road, it can drive up to 70 miles per hour (110 km/h) with normal traffic. The Transition Production Prototype's folded dimensions of 6 ft 8 in (2.03 m) high, 7 ft 6 in (2.29 m) wide and 18 ft 9 in (5.72 m) long are designed to fit within a standard household garage. When operated as a car, the engine power take-off near the propeller engages a variable-diameter pulley CVT automatic transmission to send power to the trailing-suspension mounted rear wheels via half-shafts powering belt drives. In flight, the engine drives a pusher propeller. The Transition has folding wings and a twin tail.

The experimental Transition Proof of Concept's first flight in March 2009 was successful and took place at Plattsburgh International Airport in upstate New York using U.S. Federal Aviation Administration (FAA) tail number N302TF. First customer delivery, as of March 2009, was originally planned to take approximately 18 months and occur in 2011.

On July 1, 2010, it was announced that the Terrafugia Transition had been granted an exemption from the FAA concerning its Maximum Takeoff Weight (MTOW), allowing the Transition to be certified with a take-off weight up to 1,430 pounds (650 kg); the limit matches the MTOW for amphibious light-sport aircraft. The extra 110 pounds (50 kg) granted by the exemption provides more weight allowance for the mandatory road safety features such as airbags and bumpers.

The proposed design of the production version was made by Danish designer Jens Martin Skibsted and his partners at KiBiSi and made public at AirVenture Oshkosh on July 26, 2010. Aerodynamic changes revealed included a new, optimized airfoil, Hoerner wingtips, and removal of the canard after it was found to have an adverse aerodynamic interaction with the front wheel suspension struts; furthermore, the multipurpose passenger vehicle classification from the NHTSA removed the requirement for a full width bumper that had inspired the original canard design.

For more information on the design and development of the Transition, click here. See same link for road specificatoins and performance details.

The Tupolev ANT-20 Maxim Gorky (Russian: Туполев АНТ-20 "Максим Горький", sometimes romanized as Maksim Gorki) was a Soviet eight-engine aircraft, the largest in the world during the 1930s. Its wingspan was similar to that of a modern Boeing 747, and was not exceeded until the 64.6-metre (212 ft) wingspan Douglas XB-19 heavy bomber prototype first flew in 1941.

The ANT-20 was designed by Andrei Tupolev, using German engineer Hugo Junkers' original all-metal aircraft design techniques from 1918. It was constructed between 4 July 1933 and 3 April 1934, and was one of two aircraft of its kind built by the Soviets. The aircraft was named after Maxim Gorky and dedicated to the 40th anniversary of his literary and public activities. The ANT-20 was the largest known aircraft to have used the Junkers aviation firm's design philosophy of corrugated sheet metal for many of the airframe's key components, especially the corrugated sheet metal skinning of the airframe.

The Maxim Gorky was meant as the flagship of the Maxim Gorky propaganda squadron — Maxim Gorky Agiteskadril — which flew around the Soviet Union promoting the aims and achievements of Soviet Communism. For this purpose, it was equipped with a powerful radio set known as the "Voice from the sky" ("Голос с неба", Golos s neba), printing machinery, a library, radio broadcasting equipment, a photographic laboratory and a film projector with sound for showing films in flight. In a first in aviation the aircraft was equipped with a ladder which would fold on itself to become part of the floor.

The aircraft was the first to use both direct current and alternating current. The aircraft could be dismantled and transported by rail if needed. The aircraft set several carrying-capacity world records and is also the subject of a 1934 painting by Vasily Kuptsov, which is now in the collection of the Russian Museum at Saint Petersburg.

For details of the crash of the Maxim Gorky and the history of its replacement, click here.

The Vought V-173 "Flying Pancake" was an American experimental test aircraft built as part of the Vought XF5U program during World War II.

Both the V-173 and the XF5U featured an unorthodox "all-wing" design consisting of flat, somewhat disk-shaped bodies (hence the name) serving as the lifting surface. Two piston engines buried in the body drove propellers located on the leading edge at the wingtips.

In the 1930s, Charles H. Zimmerman was a noted aeronautical engineer who advocated the concept of "discoidal" aircraft, the so-called "Zimmer Skimmer" and worked on a variety of projects on his own and with the Vought company. After testing using scale models, including a remotely controlled, electrically powered large-scale model, designated the Vought V-162, the US Navy approached Zimmerman and offered to fund further development. Data and concept documentation was given to the Navy in 1939, with wind tunnel tests on full-scale models being completed in 1940-1941.

The original prototype, designated the V-173 (Flying Pancake), was built of wood and canvas and featured a conventional, fully symmetrical aerofoil section (NACA 0015). Designed as a "proof-of-concept" prototype, the initial configuration V-173 was built as a lightweight test model powered by two 80 hp (60 kW) Continental A-80 engines turning F4U Corsair propellers. These were replaced by a pair of specially modified 16 ft 6 in three-bladed units. A tall, fixed main undercarriage combined with a small tailwheel gave the aircraft a 22° "nose-high" angle.

The disc wing design featured a low aspect ratio that overcame the built-in disadvantages of induced drag created at the wingtips with the large propellers actively canceling the drag-causing tip vortices. The propellers were arranged to rotate in the opposite direction to the tip vortices, allowing the aircraft to fly with a much smaller wing area. The small wing provided high maneuverability with greater structural strength. The empennage consisted of two vertical fins with rudders, all-moving stabilizers with anti-servo tabs,[5] and two large elevator/trim surfaces on either side of centerline on the trailing edge of the wing planform.

Zimmerman chose to include the all-moving stabilizer design because he realized that the increased drag, prop wash, and large wing area would make the aircraft difficult to control at low speeds. Wind tunnel tests would prove that this was a success to an extent. The aircraft would prove to require a lot of force to control at low speeds during in-flight testing but the tail design would prove to make the aircraft controllable.

In January 1942, BuAer requested a proposal for two prototype aircraft of an experimental version of the V-173, known as the VS-135. The development version, the Vought XF5U-1, was a larger aircraft with all-metal construction, and was almost five times heavier. Although a prototype was constructed, it only performed brief hops on the runway, it never entered true controlled flight.

For details of the operateional history of the V-173, click here.