This article may rely excessively on sources too closely associated with the subject, potentially preventing the article from being verifiable and neutral. (November 2023) |
The Zoche aero-diesels are a trio of radical German prototype diesel radial aero-engines intended for light aircraft, designed by Michael and Georg Zoche in the 1990s.[1] Zoche aero-diesels are modular piston engines and are all direct-drive, air-cooled, radial two-stroke diesels with up to four cylinders per row. They all feature direct fuel-injection, two-stage charging (turbocharger and supercharger), and intercooling. In each plane (or row), all the pistons connect to a single throw on the crankshaft.
| Zoche ZO series | |
|---|---|
| |
| Type | "Cross-8" radial aero-engine |
| National origin | Germany |
| Manufacturer | Zoche |
The testing and gestation period of the Zoche engines has already lasted over 25 years; and whether or when production may eventually start is unknown. However, in 2019, Georg Zoche posted this message online: "Don't worry and remain patient; we are working on it".[2]
Design and development edit
The range comprises three radial engines, namely: a "cross-4"; a twin-row "cross-8"; and a V-twin.[3] As yet, there are no plans for a 3-cylinder version.
The AOPA website explains the "cross-4" ZO 01A as follows: "The radial design was chosen for its ability to be effectively air-cooled and 100% balanced at all rpm with a simple counterweight system. All four connecting rods are attached to a single crankshaft throw. This prevents any crankshaft twisting, which is hard to balance out in opposed-configuration engines. Zoche engines use a pneumatic starting system that does away with the need for a heavy-duty starter and battery system".[4] Propeller rotation is clockwise (viewed from the cockpit). Engine mountings are attached to the cylinder heads. Engines are to be certified to JAR-E and FAR 33, and a TBO of 2,000 hours is anticipated.
The founder of the project is Michael Zoche, who claims that the ZO engines will have the following advantages:
- they will be lightweight, compact (with low frontal area) and very smooth;
- low fuel consumption; high power-to-weight ratio;
- the lubrication system will allow aerobatics;
- diesel fuel injection, so no carburetor icing;
- direct-driven generator, so no drive belts;
- good reliability through a low part count and absence of poppet valves;
- pneumatic starting obviates both electric starter motor and heavy starter battery;
- complete absence of rubber hoses; cheaper parts through modularity;
- reduced fire risk compared to avgas;[5]
- good power output, even at altitudes up to 9,000 feet (3,000 m).[3]
- the engines will also have a "classic radial" appearance that is appropriate for some aircraft types.
A Zoche engine has run effectively in wind tunnel tests,[6] but Zoche seem barely any closer to production than they were a in 2010. Experimental engine manufacturers seem to experience difficulties in proceeding beyond the prototype stage. The cited engine weights include: starter-generator, hydraulic propeller-governor, turbocharger and supercharger, and oil- and fuel-filters.
Zoche engine variants edit
- ZO 01A
- Single-row cross-4, 2,660 cc (162 cu in), (max) 150 hp (112 kW) @ 2500 rpm, 84 kg (185 lb)), fuel consumption 21 litres/h @ 75% power.[3]
- ZO 02A
- Double-row cross-8, 5,330 cc (325 cu in), (max) 300 hp (224 kW) @ 2500 rpm, 123 kg (271 lb)), fuel consumption 42 litres/h @ 75% power.[3]
- ZO 03A
- V-twin, 1,330 cc (81 cu in), (max) 70 hp (52 kW) @ 2500 rpm, 55 kg (121 lb)), fuel consumption 10 litres/h @ 75% power.[3]
- ZO 04A
- A 2,000 hp (1,500 kW) compound diesel engine for use in the Sentinel 5000 airship on vectoring mounts.[7]
A consequence of the modular design, with all engines sharing parts (such as an intercooler), is that the larger engines have a much higher power to weight ratio than the smaller engines, as follows:
- The 8 cylinder ZO 01A claims 2.43 bhp per kilogram;
- The 4 cylinder ZO 02A claims 1.78 bhp per kilogram;
- The 2 cylinder ZO 03A claims 1.27 bhp per kilogram.
Lambert Mission edit
The Lambert Mission 212,[8] a kit-built 4-seat aircraft from Belgium, was initially designed around the Zoche ZO1A engine; but, with the non-appearance of the Zoche, Lambert were obliged to select other engines, the DeltaHawk® DH200A4 (or DH180A4), or the XP-360 engine.[8] In May 2010 the second M212 Mission (and first kit-built example) was successfully flown.
See also edit
Comparable engines
- Thielert Centurion
- Wilksch Airmotive — WAM 100 (100 hp), WAM 120 (120 hp) and WAM 160 (160 hp)
- Diesel Air — 100 hp (75 kW) twin-cylinder two-stroke opposed-piston engine
- Continental O-300
- Continental O-360
- ULPower UL260i
- MidWest AE series
Related lists
References edit
- ^ "Home". zoche.de.
- ^ "Zoche aero-diesel running on wind tunnel test bench" – via www.youtube.com.
- ^ a b c d e ZOCHE aero-diesel brochure
- ^ "Horsepower of a Different Color". Archived from the original on January 8, 2007. Retrieved July 31, 2012.
- ^ Brochure claim: "High inflight reliability – no carburetor-icing, no magneto or spark- plug problems, no vapor lock. Turbine inlet temperature is so low that it needs no monitoring. Even cylinder head temperatures are not critical.
- ^ "zoche aero-diesels testbench video". www.zoche.de.
- ^ Gunston, Bill (2006). World encyclopedia of aero engines : from the pioneers to the present day (5th ed.). Stroud: Sutton. p. 254. ISBN 9780750944793.
- ^ a b "Lambert Aircraft".
External links edit
- www.zoche.de — Zoche site
Patents:
- Application filed by Michael 8000 Muenchen De Zoche DE 4020826
- Diesel engine EP 0231223
- Turbocharged diesel engine US 4781028
- Radial internal combustion engine US 5197416
- Japan 63-500818