Engines – Power

Peak Me 109 v.1 / Bek Treppenbau Me 109

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The ME 109 UL began with Tassilo Bek´s visit in the middle of the 80’s to Oshkosh. Seeing small reproductions of Mustangs and other fighters, hardly back in Germany, he began to sketch his own airplane. After some planning and drafts he began with the work on the first ME 109. Basis was a covered timber frame, with retractable landing gear (operates via crank) in addition, and somewhat larger span of approx. 10.5 m with a length of approximately 7 m. The first prototype, registered D-MBAK, was powered by a Hirth 2704 producing only 40 hp (30 kW) and first flew in 1991. This first 109 flew well, was not particularly agile. This aircraft achieved 190 km/h (118 mph) on its low power output, but Bek started a second prototype based on lessons learned in 1992. Thus he began to build with friendly engineers and craftsmen the first form for a plastic 109.

PDQ Aircraft Products PDQ-2

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Back in the early 1970’s Wayne Ison designed the P.D.Q. The PDQ-2 is a sort of strap-on monoplane with shoulder-high wings, a tiny tricycle gear and a pylon-mounted JLO snowmobile engine that swings a two-bladed pusher prop. The pilot sits up front biting bugs at a Vmax of 80 mph. On a cold day vertical velocity is 400 fpm. The I-tail is hung at the end of a boom borrowed from the Bensen gyrocopter. The wings are made from Styrofoam bonded over plywood ribs at root and tip of each panel, with seven foam ribs in between. The foam is then covered with Dynel, bonded at the edges and heat¬shrunk, with resin squeegeed into the cloth and sanded light¬ly. Finally, the direct-driven prop develops 45 hp at 5500 rpm or 35 hp at 5000 rpm.

Engine: 1385cc VW, 40hp
Wingspan: 22 ft
Length: 14 ft 6 in
Max wt: 600lbs
Empty wt: 340 lb
Max speed: 80mph
Cruise: 70mph
Climb rate: 500 fpm

PC Flight PG

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The PG is a side by side two seater with a spaceframe fuselage. The wings are made of riveted sheet dural and can be folded for transport.

Engine: Rotax 912 UL, 80 hp
Wing span: 10 m
Wing area: 11.66 sq.m
MAUW: 450 kg
Empty weight: 280 kg
Fuel capacity: 100 lt
Max speed: 210 kph
Cruise speed: 195 kph
Minimum speed: 63 kph
Climb rate: 5.5 m/s
Certification: vVz
Seats: 2
Fuel consumption: 17 lt/hr
Price (1998): 85 000 DM

PC-Aero Elektra Two

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The Elektra Two aircraft are scaled versions of the Elektra One Solar. Two versions are:

Version 1: Elektra Two Standard, with two different wing span: 17 meters and 14 meters
Version 2: Elektra Two Record. Only one unit for a range over 2000 km was to be built.

The outer shape of the Elektra Two Standard is the same as the Elektra Two Record. Two versions will be provided: the long span version (17 meters) and the short span version (14 meters).

Elektra Two Standard (long & short version) are for cruise, flying clubs and training

Construction is carbon / glass and solar cells on the wing surface provide the energy to fly. The solar cells will be laminated in the wing skin structure.

Specifications

Elektra Two Standard
Max. engine power: 40 kW
Wing span: 14 m / 17 m
Wing surface: 15 sq.m / 19 sq.m
MTOW: 350 kg
Empty weight: 200 kg
Battery weight: up to 100 kg
Payload: 180 kg
Max. range:
14 m wing span: 500 km
17 m wing span: 700 km
Max. endurance:
14 m wing span: 5 hours
17 m wing span: 8 hours
Cruise:
14 m wing span: 140 km/h
17 m wing span: 120 km/h
Aspect ratio:
14 m wing span: 13
17 m wing span: 15
Best glide ratio:
14 m wing span: 28
17 m wing span: 34
Certification: LTF-UL germany

Elektra Two Record
Max. engine power: 16 kW
Wing span: 17 m
Wing surface: 19 sq.m
MTOW: 350 kg
Empty weight: 140 kg
Battery weight: 80 kg
Payload: 150 kg
Max. range: more than 2,000 km
Max. endurance: over 20 hours
Cruise: 80 km/h
Aspect ratio: 15
Best glide ratio: 34
Certification: LTF-UL Germany

PC-Aero Elecktra One / Elektra One Solar

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The Elektra 1, designed by Calin Gologan and built by a group of Romanians including Sorin Mares, received an award for innovation in aviation, the Lindbergh Electric Aircraft Prize.

The one-seater plane is made of light carbon composite materials, utilising an electric motor, the batterys are charged while hangered, through solar panels. Elektra One Solar has six square meter solar cells on its wings to provide over 1 kilowatt (kW) of power for flying. Since the aircraft requires at least 2.5kW power for horizontal flight, this is slightly less than half the energy required for the plane to fly. The Elektra One Solar is not completely powered by the solar panels on its wings. To enable full flight, the plane has a series of high energy density rechargeable Li-Ion batteries on board. These can be recharged using the solar panels when the plane is parked outside. If the plane is parked inside, a specially outfitted solar hangar can take over the recharging duties.

PC-Aero developed the Elektra One Solar with the support from Solar Hangar and Solar World. The business idea behind it is that the solar panel equipped hangars will provide energy for the plane while the excess energy would be fed back into the grid. This predecessor of the Elektra One Solar, the Elektra One, has a range of 500 kilometers and an endurance of 3 hours. Its wingspan is also smaller at just 8.6 meters compared to 11 meters in the Elektra One Solar.

The Elektra One is in the German Ultralight LTF-UL-class powered by a 13.5 kW brushless electric engine. Germany’s Geiger Engineering developed the electric drive unit which includes the HPD 13.5 (16 kW maximum power) electric motor, controller, battery management system and propeller.

As the Elektra One was designed for minimum energy requirements at 160 km/h, once airborne, it is remarkably frugal with its use of energy. It can remain airborne for three hours and its claimed range has now increased to 500 kilometers. PC-Aero claims that the system offers operational costs per hour of less than EUR 35 or EUR 0.2 per km, which is a lot less than a roadgoing car.

Though the driving force and design of the Elektra One emanated from PC-Aero’s founder Calin Gologan, the team included team leader Einar Enevoldson, a 30 year veteran NASA-test pilot, engineer and test pilot.

Elektra One first flew on 19 March 2011, piloted by Jon Karkow, from Augsburg Airport in Germany. Three flights were performed, showing a climb rate of 400 fpm. Karkow checked flight performance and characteristics and briefed the German test pilot Norbert Lorenzen for the next flight on March 21.

A new 30 minute flight was performed on 23 March 2011. Only about 3kW from the total on board of 6kW energy was used and this was before the new variable pitch propeller and retractable landing gear were installed.

Endurance is estimated to be up to three hours and a cruising speed of 160 kph. The single seat Elektra One weighs 200 kg complete with battery and cost US$145,000 in 2012.

One of the Elektra One’s greatest advantages is its very low level of noise. The propeller speed is optimized for low noise too (under 50 dB). Cruising at 160 km/h, the propeller is rotating at just 1400 RPM. At this speed, PC-Aero claims it makes one fifth of the noise of a classic light aircraft and half the noise of an ultralight. Operating costs are below 35 €/hour and 0,2 €/km (2012).

Gallery

Elektra One
Engine power: 16 kW
Wingspan: 8.6 m (28 ft 3 in)
Wing area: 6.4 sq.m (69 sq ft)
Aspect ratio: 11.65
Empty weight: 100 kg (220 lb)
Gross weight: 300 kg (661 lb)
Battery weight: 100 kg
Payload: 100 kg
Best glide ratio; 25
Range: 500 km (311 mi; 270 nmi)
Endurance: 3 hours
Crew: one

Elektra One Solar
Wingspan: 11 m
Range: 1000 km
Endurance: 8 hours
Crew: one

PBS TJ 100

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Development of the TJ 100 turbo-jet engine began in 2002, as a drive unit for MAE UAV and piloted flying vehicles.

The TJ 100 is single-shaft engine with single-stage radial compressor, annular combustion chamber, single-stage axial turbine, and stationary exhaust jet.

In the compressor intake there is a brushless starter generator, which enables the starting from the board network and power generating in course of the engine operation.

The intake air is compressed in the radial compressor wheel, proceeds through radial and axial diffuser into the combustion chamber, where it is mixed with fuel sprayed by several fuel nozzles. Combustion gases arising in fuel burning in the combustion chamber expand through the single-stage axial turbine and exhaust jet into the atmosphere.

The rotor of the engine is mounted on 2 ball bearings lubricated with pressure oil.

Several versions were produced, varying by length of output nozzle, mounting, and by power.

PBS produce TJ 100, TJ 100C, TJ100E, and TJ 100I of 100 daN (225 lbf) power. The TJ 100A and TJ 100S are produced with 110 daN (247 lbf) power.

Static Thrust: 100 daN / 225 lbf
Spf. Fuel Consumption: 1.2 kg/daN.hr / 1.2 lb/lbf.hr
Oil Consumption: 180 ml/hr / 0.16 qt/hr
Electric Power Output: 28 V/800W
Weight – Engine: 16 kg / 35 lb
Weight – Wth/Access: 19 kg / 41 lb
Outside Diameter: 272 mm / 10.7 in
Length: 485 mm / 19 in
Fuel Consumption: < 128 kg/hr / < 281 lbs/hr
Max Running Altitude: 8 000 m / 26 246 ft

PBS TJ-100 E3S
Max Thrust (max 5 min.): 258.53 lbf [1150 N]
Electric Power Output: 650 W
Specific Fuel Consumption (max thrust): < 1.1376 lb/lbf/hr
Fuel Consumption at Idle: 11 gal/hr
Outside Diameter: 10.7″
Engine Length: 24.6″
Engine Weight: 43 lbs
Max Operating Altitude: 32,808 ft. msl
Max Starting Altitude: 19,685 ft. msl
Flight Speed Range: 0 to 0.8 mach
Speed Range for Startup: 0 to 0.6 mach
Fuel Requirements: JET-A, JET-A1, JP4, JP8, TS-1, T2, RT
Lubrication: according to MIL-L-23699 (Mobil Jet Oil II, Aeroshell 560)
Price 2020: $65,000

PBS / První Brnenská Strojírna

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První Brnenská Strojírna Velká Bíteš, a.s./ PBS is a manufacturer of:
Small aircraft turbojet engines and auxiliary power units,
Environmental control systems for aircraft and helicopters,
Ground power units,
Precise castings for automotive, aerospace and glass industries and healthcare,
Complex and completely machined parts of electromotors, alternators, mammographs and wind power plants,
Decanting centrifuges for sewage plants, i.e. programs closely related to ecology and environmental protection.

Pazmany PL-9 Stork

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The Pazmany PL-9 Stork is an 3/4 replica of the Fieseler Storch. It authenticity is backed up by more than 9000 hours of aeronautical engineering design in order to obtain the same flying and handling characteristics of the original German Aircraft. The fuselage is welded chrome alloy steel tube, with aluminum sheet metal/fabric covered wing and empenage.

Designed to take off and land in extremely short distances, the Storch had a take off ground roll of 131 feet and a landing roll of 36 feet with 13 miles per hour head wind.

It has a well-proven aircraft configuration designed for a number of functions such as fish spotting, forest fire detection, farm work, missionary work, etc. The PL-9 Stork has a cruise speed of 104 mph with a standard Lyc. O-320/150 hp engine. Optional Subaru 2.2 lt engine.

Using the new Pazmany 3/4 scale plans, amateur builder Ruben Hardy embarked on his own construction of the PL-9. With great enthusiasm, financial commitment, and building ingenuity, bringing the first new Stork to life.
In March l999 at Oshkosh, Wisconsin his plane was displayed at the EAA convention to great public interest, in the presence of the design engineer Ladislao Pazmany.

PL-9
Engine LYC 0-320
Power Range 150-160 hp
Height 7 ft
Length 24.3 ft
Wing Span 36 ft
Wing Area 166 sq. ft
Empty Weight 1,132 lb
Gross Weight 1,739 lb
Fuel Capacity 30 USG
Top Speed 116 mph
Cruise 104 mph
Stall 33 mph
Range 332 mi
Rate of Climb 1400 fpm
Take-Off Distance 250 ft
Landing Distance 90 ft
Service Ceiling 15,000 ft
Number of Seats 2
Landing Gear Tailwheel
Information Package PDF 2009 $9
Information Package printed 2009 $12
Plans 2009 $550

Pazmany PL-4A

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When designer Ladislao Pazmany was encouraged to come up with an easy-to-build, simple, safe, inexpensive, metal plane that could carry a Volkswagen 1600-cc or Continental A-65 engine in the early l970’s, he came up with the PL-4A. The fuselage is made up from formed sheet metal channels and standard extruded aluminium angles for the longerons with sheet metal skins. The wing consists of a centre section and two outer panels which can be folded back along the fuselage. Each panel incorporates a metal spar, a Zed section rear spar, pressed metal ribs and metal skins. Pop rivets are used extensively. Plain ailerons, but no flaps or trim tabs are fitted to the wing. The empennage is of “T” tail configuration with an all moving tailplane at the top of the fin with a large anti-servo tab. The tailwheel undercarriage consists of spring steel main legs with 3.50 x 6” tyres and brakes and a steerable tailwheel. A 9.5 Imperial gallon moulded fibreglass fuel tank is fitted behind the firewall. Engines from 50 to 75 hp may be installed.

Pazmany PL-4A N44PL

The prototype was flown on July 9, 1972 and plans were made available. The plane is roadable (folding wings), and Pazmany did supply the fiberglass pieces, plexiglass windscreen and canopy, landing gear, welded engine mount, and control stick.

The PL-4A has been built by air cadets in Argentina and Canada.

Gallery

PL-4A
Engine Used: VW 1600 c.c.
Power Range: 50-90 hp
Top Speed: 120 mph
Cruise: 97 mph
Stall: 46 mph
Range: 280 mi
Rate of Climb: 650 fpm
Take-Off Distance: 560 ft
Landing Distance: 440 ft
Service ceiling: 13,000 ft
Fuel Capacity: 12 USgal
Empty Weight: 578 lb
Gross Weight: 850 lb
Height: 5.7 ft
Length: 16.5 ft
Wing Span: 26.7 ft
Wing Area: 89 sq. ft
Seats: 1
Landing Gear: Tailwheel
Information Package (PDF) 2009: $9
Information Package (printed) 2009: $12
Plans 2009: $375