Songbo Zeppelin

Shi Songbo from Ningling, central China, spent 300,000 Yuan (£30,000) on the Zeppelin, which successfully completed a two-hour test flight near his home in October 2015.

Although his family have been farmers for several generations, his brother attended the Aeronautical Engineering Institute in Xi’an, central China.

As a result of his studies, Shi’s brother always brought home aeronautical engineering magazines and reading material, which got Shi interested in the techniques involved in building an aircraft.

Eventually, Shi would go on to work for an aerial model company as a designer, which gave him greater understanding of the composition of a plane.

In June 2015, Shi was let go from his job, which prompted him to start building his ‘Songbo’ Zeppelin. Shi Songbo spent four months building a Zeppelin. The Zeppelin is about 33 feet tall and 75 feet long. The top portion is composed of a hydrogen-filled airbag while the bottom is made up of the seat and controls.

Shi spent around four months and 300,000 Yuan (£30,000) on the Zeppelin, with many of the components imported from Germany and the USA.

Shi Songbo conducted his first official flight on October 25 2015 in a field near his home under the direction of friend Shang Jianjun, who acted as a dispatcher.

Along with his co-pilot Li Kai, the inventor made several different maneuvers and successfully took off and landed eight times over the space of two hours split between the morning and afternoon. Speaking of his first aerial experience, Shi said: ‘There were lots of low-hanging electricity cables.” ‘Because I was worried about bumping into the cables, everything had to be under the direction of the dispatcher.’ He added, ‘My co-pilot was my eyes and ears. He helped to monitor my surroundings.’

It is able to travel just over 30 miles per hour at 1,640 feet above the ground while carrying two people.
The Zeppelin prototype will need additional testing but Shi hoped that it could be used to distribute pesticide, aerial surveying or tourism in the future.

Sonex Aircraft Xenos

The XENOS follows in the Monnett tradition of bringing the cost of motor gliding to a highly affordable level. Using the same cost-effective and easy-to-build construction techniques and materials of the Sonex and Waiex, the Xenos offers another Reality Check for the soaring world. The Xenos comes standard with utility wing tips that can be easily removed to fit inside a 40 foot hangar, and can be quickly interchanged with optional aerobatic wingtips. The Xenos can either be flown as a Sport Pilot/LSA, or it can be flown by pilots that hold a glider rating with a self-launch glider endorsement. The Xenos can be flown as a powered aircraft, a self-launched glider that soars with the engine off, or it can motor-soar over great distances with incredible fuel economy.

The Xenos can either be flown as a Sport Pilot/LSA, or it can be flown by pilots that hold a glider rating with a self-launch glider endorsement. The Xenos can be flown as a powered aircraft, a self-launched glider that soars with the engine off, or it can motor-soar over great distances for fuel economy.

The Xenos is only available in kit form. The Xenos complete kit includes many pre-fabricated precision parts. Landing gear can be nose or tail wheel. Dual stick controls are standard.

Engine: 80 hp 2180 AeroVee
Length: 19′ 9″
Wing Span (Utility): 45′ 8″
Wing Span (Aerobatic, solo): 39′ 4″
Wing Area (Utility): 158 sq ft
Wing Area (Aerobatic, solo): 144 sq ft
Tail Configuration: Y-tail
Tail Height: 59″
Tail Width–with tail tips: 102″
Main Gear Width: 71″ (with wheel pants)
Primary Structure: 6061 Aluminum
Cockpit Width: 40 in. More Info
Fuel Capacity: 16 US Gal
Stall Speed (clean): 44 mph [71 km/h]
Maneuvering Speed: 115 mph [185 km/h]
Never Exceed Speed (Vne): 150 mph [241 km/h]
Empty Weight: 750 lbs
Baggage (Max): 40 lbs
Range: 400 miles
Cruise Speed @ Sea Level: 100 mph
Cruise Speed @ 8000 ft (TAS): 120 mph
Power Loading: 15.938
T.O. Distance: 300 ft
Landing Distance: 300 ft
Cockpit width: 40 in
Utility
Gross Weight: 1275 lbs
Useful Load: 525 lbs
Rate of Climb: 800-1000 fpm
Load Factor: +4.4 / -2.2 G
L/D: 24:1
CG Limits: 25-36% Wing Chord
Aerobatic
Gross Weight: 1050 lbs
Rate of Climb: 1000-1250 fpm
Load Factor: +6.0 / -3.0 G
CG Limits: 27-32% Wing Chord

Engine: 120 hp Jabiru
Length: 19′ 9″
Wing Span (Utility): 45′ 8″
Wing Span (Aerobatic, solo): 39′ 4″
Wing Area (Utility): 158 sq ft
Wing Area (Aerobatic, solo): 144 sq ft
Tail Configuration: Y-tail
Tail Height: 59″
Tail Width–with tail tips: 102″
Main Gear Width: 71″ (with wheel pants)
Primary Structure: 6061 Aluminum
Cockpit Width: 40 in. More Info
Fuel Capacity: 16 US Gal
Stall Speed (clean): 44 mph [71 km/h]
Maneuvering Speed: 115 mph [185 km/h]
Never Exceed Speed (Vne): 150 mph [241 km/h]
Empty Weight: 760 lbs
Baggage (Max): 40 lbs
Range: 350 miles
Cruise Speed @ Sea Level: 120 mph
Cruise Speed @ 8000 ft (TAS): 140 mph
Power Loading: 10.625
T.O. Distance: 250 ft
Landing Distance: 300 ft
Cockpit width: 40 in
Utility
Gross Weight: 1275 lbs
Useful Load: 515 lbs
Rate of Climb: 1200-1400 fpm
Load Factor: +4.4 / -2.2 G
L/D: 24:1
CG Limits: 25-36% Wing Chord
Aerobatic
Gross Weight: 1050 lbs
Rate of Climb: 2000+ fpm
Load Factor: +6.0 / -3.0 G
CG Limits: 27-32% Wing Chord
VNE: 167 kt / 192 mph / 309 kmh

Sonex Aircraft Waiex

WAIEX (pronounced “Y-X”) is simply a Y-tail Sonex. Built purely for it’s good looks, the Waiex specifications and performance numbers are identical to those of the Sonex and, like the Sonex, is perfectly suited to the new US Sport Pilot/LSA regulations. The Waiex retains the same Sonex flight characteristics and high performance in all phases of flight, including aerobatics.

The Waiex is only available in kit form. The Waiex complete kit includes many pre-fabricated precision parts.

Engine: 80 hp 2180 AeroVee
Length: 18′ 1″
Wing Span: 22′
Wing Area: 98.0 sq. ft.
Tail Configuration: Y-tail
Tail Height (Std Gear): 51″
Tail Height (Tri-Gear): 69″
Tail Width – with tail tips: 88″
Main Gear Width: 71″ (with wheel pants)
Air Foil: 64-415
Primary Structure: 6061 aluminum
Cockpit Width: 40 in.
Fuel Capacity: 16 US Gal.
Stall Speed (full flaps): 40 mph [64 km/h]
Stall Speed (clean): 46 mph [74 km/h]
Max Flap Extended Speed (Vfe): 100 mph [161 km/h]
Maneuvering Speed: 125 mph [201 km/h]
Never Exceed Speed (Vne): 171 kt / 197 mph / 317 km/h
Empty Weight: 620 lbs.
Range: 550 miles
Cruise Speed @ Sea Level: 130 mph
Cruise Speed @ 8000 ft (TAS): 150 mph
Power Loading (GW/HP): 13.125
T.O. Distance: 400 ft
Landing Distance: 500 ft
Cockpit width: 40 in
Utility Category
Gross Weight: 1100 lbs
Baggage (Max): 40 lbs
Useful Load: 480 lbs
Rate of Climb: 800-1000 fpm
Load Factor: +4.4 / -2.2 G
L/D: 11:1
CG Limits: 20-32% Wing Chord
Aerobatic Category
Gross Weight: 950 lbs
Baggage (Max): 10 lbs
Rate of Climb: 1000-1250 fpm
Load Factor: +6.0 / -3 G
CG Limits: 23-29% Wing Chord

Engine: 80 hp Jabiru
Length: 18′ 1″
Wing Span: 22′
Wing Area: 98.0 sq. ft.
Tail Configuration: Y-tail
Tail Height (Std Gear): 51″
Tail Height (Tri-Gear): 69″
Tail Width – with tail tips: 88″
Main Gear Width: 71″ (with wheel pants)
Air Foil: 64-415
Primary Structure: 6061 aluminum
Cockpit Width: 40 in.
Fuel Capacity: 16 US Gal.
Stall Speed (full flaps): 40 mph [64 km/h]
Stall Speed (clean): 46 mph [74 km/h]
Max Flap Extended Speed (Vfe): 100 mph [161 km/h]
Maneuvering Speed: 125 mph [201 km/h]
Never Exceed Speed (Vne): 171 kt / 197 mph / 317 km/h
Empty Weight: 620 lbs.
Range: 550 miles
Cruise Speed @ Sea Level: 130 mph
Cruise Speed @ 8000 ft (TAS): 150 mph
Power Loading (GW/HP): 13.125
T.O. Distance: 400 ft
Landing Distance: 500 ft
Cockpit width: 40 in
Utility Category
Gross Weight: 1100 lbs
Baggage (Max): 40 lbs
Useful Load: 480 lbs
Rate of Climb: 800-1000 fpm
Load Factor: +4.4 / -2.2 G
L/D: 11:1
CG Limits: 20-32% Wing Chord
Aerobatic Category
Gross Weight: 950 lbs
Baggage (Max): 10 lbs
Rate of Climb: 1000-1250 fpm
Load Factor: +6.0 / -3 G
CG Limits: 23-29% Wing Chord

Engine: 120 hp Jabiru
Length: 18′ 1″
Wing Span: 22′
Wing Area: 98.0 sq. ft.
Tail Configuration: Y-tail
Tail Height (Std Gear): 51″
Tail Height (Tri-Gear): 69″
Tail Width – with tail tips: 88″
Main Gear Width: 71″ (with wheel pants)
Air Foil: 64-415
Primary Structure: 6061 aluminum
Cockpit Width: 40 in.
Fuel Capacity: 16 US Gal.
Stall Speed (full flaps): 40 mph [64 km/h]
Stall Speed (clean): 46 mph [74 km/h]
Max Flap Extended Speed (Vfe): 100 mph [161 km/h]
Maneuvering Speed: 125 mph [201 km/h]
Never Exceed Speed (Vne): 171 kt / 197 mph / 317 km/h
Empty Weight: 620 lbs.
Range: 400 miles
Cruise Speed @ Sea Level: 135 mph
Cruise Speed @ 8000 ft (TAS): 170 mph
Power Loading (GW/HP): 9.583
T.O. Distance: 250 ft
Landing Distance: 500 ft
Cockpit width: 40 in
Utility Category
Gross Weight: 1150 lbs
Baggage (Max): 40 lbs
Useful Load: 530 lbs
Rate of Climb: 1200-1400 fpm
Load Factor: +4.4 / -2.2 G
L/D: 11:1
CG Limits: 20-32% Wing Chord
Aerobatic Category
Gross Weight: 950 lbs
Baggage (Max): 10 lbs
Rate of Climb: 2000+ fpm
Load Factor: +6.0 / -3 G
CG Limits: 23-29% Wing Chord

Somerville 1912 Biplane

The 1912 Somerville Biplane was an exhibition and sightseeing ship for Earl S Daughery, who relocated to Long Beach CA and founded its municipal airport.

Somerville Biplane with Daugherty at the helm

Coal City’s Illinois Aero Construction Co (IAC) initials were on the plane and 51; most likely when it was used as a trainer at IAC’s flying school.

Somerville-Borel monoplane

Somerville-Borel

Built by the Illinois Aero Construction Company and designed as an automatically stable machine by William E. (Billy) Somerville.

The 1910 Somerville-Borel was mentioned in the 27 September 1913 Aero and Hydro as a 50hp Gnôme-powered monoplane being flown at Rensselaer IN. Advertised as “automatically stable,” it might have been a copy, rather than a rebuild as thought, of the Morane-Borel.

Engine: 50hp Gnôme
Wingspan: 45’0″
Seats: 1

Sommer 1910 biplane

Humber-Sommer biplane in India

The Sommer 1910 Biplane was designed by Roger Sommer. It was a pusher configuration biplane resembling the successful Farman III, and was built in large numbers for the time. One was owned by Charles Rolls.

In May 1909 Sommer bought a Farman III aircraft, and on 7 August 1909 he gained fame in this by breaking the endurance record held by Wilbur Wright, making a flight lasting 2 hr 27 min 15 sec. Later that year he made a successful appearance at the Doncaster flight meeting, winning the prize for the greatest distance flown during the meeting. Meanwhile, he had started building an aircraft of his own design at Mouzon in the Ardennes, where his family had a felt-making business.

The design of the Sommer biplane was derived from that of the Farman III, the aircraft being a pusher configuration equal-span biplane powered by a 50 hp (37 kW) Gnome Omega. Lateral control was effected by D-shaped ailerons on the upper wing. A single elevator was mounted in front of the wings: behind the wings wire-braced wooden booms carried a horizontal surface which was operated independently of the front elevator and was used to adjust the aircraft’s trim rather than for control purposes. Early examples has a single large rudder mounted below this: this was later changed to four smaller rudders, two above it and two below, and subsequently changed again to one above and one below. The twin skids of the undercarriage were extended forwards to form part of the supporting structure for the elevator, and a single pair of wheels were mounted on an axle between the skids. A two-seat “Military” version with an extended upper wing was produced later.

The prototype was first flown by Sommer on 4 January 1910 at Mouzon, when he managed three flights of over 4 km (2.5 mi) This first machine was sold to a M. Viateaux within two weeks, and by the end of February he had built a replacement and established a flying school at Mouzon. A large number of examples were built: by spring 1910 Sommer had sixty aircraft on order. Sommer had established flying school at Douzy using his machines.

One example was bought by Charles Rolls, and was exhibited on the Royal Aero Society stand at the 1910 Aero Show at Olympia

A small number of license-built copies of the Sommer biplane were built in England by Humber. These were of mixed steel and wood construction, and one was used to carry out the world’s first official mail-carrying flight, when 6,500 letters were flown by Henri Pequet from the United Provinces Exhibition at Allahabad to Naini. The letters bore an official frank “First Aerial Post, U.P. Exhibition, Allahabad, 1911”, the text surrounding a drawing of the aircraft.

The first aeroplane flight in China was most likely on February 21, 1911, with René Vallon and his Sommer biplane flying over Shanghai. Like other entrepreneurial aviators, he was hoping to sell the concept to onlookers.

René Vallon and his Sommer above Shanghai.

Powerplant: 1 × Gnome Omega 7, 37 kW (50 hp)
Wingspan: 10.36 m (34 ft 0 in)
Wing area: 36 m2 (390 sq ft)
Length: 12.5 m (41 ft 0 in)
Crew: 1
Capacity: 1

Sommer Type E Monoplane / Bathiat-Sanchez

This Roger Sommer monoplane, a fabric covered fuselage version, was designed by Ingénieur Tonnet and flown circa 1911/1912. Léon Bathiat flew many variants of this fast monoplane in several competitions during 1910 and 1911, and in 1912 all interests were purchased by Bathiat who sold these monoplanes under the name Bathiat-Sanchez. Very similar to the Bathiat-Sanchez Type E, shown at the Paris Aero Salon of 1913.

Soltau Sturmvogel / Schwingenflieger

The “Sturmvogel” was an ornithopter designed by Austro-Hungarian engineer Andreas Soltau. It was powered by a carbonic acid engine. It was a relatively large machine, with a span of 11 meters and a wing area of 30 square meters. It had an elevator at the rear, a birdlike construction, and the rudder in front.

The machine was not successful, as the flapping had a too low frequency to lift it off. Tests were made at Linz on 16 August 1909, which were highly published in the contemporary Austro-Hungarian press. After his adventure with the Sturmvogel, Soltau left aeronautics, but he can still be traced in patents dating from the 1920s, one of which features a hot-air engine.