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Aviation History
1942
1942 - 1964.PDF
3tb FLIGHT SEPTEMBER iyra, 1042 WORLD PRESS SUMMARY RESUME OF TECHNICAL ARTICLES DEALING WITH AIRCRAFT * AND ASSOCIATED SUBJECTS i For the summaries awl translations from aircraft and technical journals of the world, we are indebted to the. : : Directorate of Scientific Research and Technical Development, Ministry of Aircraft Production, Japanese Types ATTENTION has repeatedly been drawn to the difficulties which present themselves to the European in the distinc tion of Japanese aircraft types. It is known that the Japanese- aircraft designations contain the two last figures of the con- si ruction year of the prototype in the Japanese reckoning of time (00 stands for the year 2600 of the Japanese or 1940 of the Christian era); later reports state that the figure represents the year in which the production model was taken into active service. Ahead of this figure, the Japanese designations con tain one or two letters which represent the aircraft class and were not so far used as a general rule or replaced by the letter 'T" (for Type). Fighters are designated by "S" (e.g., Kawasaki S-97), light bombers of the Army Air Force by "KB," medium bombers by "B" (e.g., Mitsubishi B-96 " Otori"), heavy bombers by "OW," torpedo bombers by "G," naval dive-bombers by "K" (for Kyukoki), recon naissance aircraft by "T," reconnaissance floatplanes by " KT," flying-boats by "H," transport aircraft by " Y," and trainers by " K " (for Kyorenki). Japanese Type Designations. "Inter Avia.") (Japan.) -** Radiolocation Methods for Finding Targets, Especially for the Determination of Aircraft Positions. T HESE methods operate on the back-radiation principle. A transmitter scans the explored space in two dimensions, while the back-radiation from a body in that space causes in a receiver an intensity variation of a cathode-ray beam which if deflected in synchronism with the transmits 1 — D.R.P., 702,686, published February 15, 19.41. A.E.G. Inventor, T, Elmquist. Methods for the Determination of the Distance of Reflecting Objects, According to the Back-radiation Principle. The wavelength of a radiated beam is varied between two fixed values in successive half periods of a modulation fre quency M. If the time interval between the transmission and reception of the reflected wave is a whole multiple of the modu lation frequency, the beat amplitude in the receiver will be a minimum. In order to obtain an exact result for the distance d. the minimum is determined for two adjacent values M, N' on the modulation frequency. If the time interval is o=i/(N — M') then the required dis tance d = UO/2 where U = the velocity of propagation ^ of the waves. —D.R.P., 703,111, published February 28th, 1941. Com- pagnie de Telegraphic sans Fil, Paris. Inventor, H. Gutton. Foreign Radiolocation Patents. ("Electronic Engineer ing.") (G.B.) Carburettor Air Scoops THE design of a carburettor airscoop involves: 1. Location of the intake opening to receive full air-speed ram and exert minimum drag (which involves knowledge and experiment as to the external air flow around the airplane; and 2. Conducting the intake air to enter the carburettor with uniform pressure across its stream with minimum turbulence, and minimum loss of impact pressure (which involves the study of internal air flow). In general, the two main objectives, maximum ram and mini mum disturbance of carbuiation, go hand in hand and have the same structural requirements An analysis is given of the principles of fuel-air metering, by measuring the air velocity differential through air orifices of fixed size, and transmitting this differential, corrected for vari- tions of air density, to secure corresponding fuel flow differen tial through selected fuel orifices. A description is then given of the departures from steady full-stream air flow encountered in flight service, and the manner in which these affect air-speed metering. Methods are given for detecting, measuring, and curing dis turbances from these sources. Recommendations also are given for improved warm and cold air control, for protection against ice formation in the intake system, by eliminating the variable ram differential between cold and warm air flow which exists with most current scoop designs. In conclusion, the need is emphasised for freer co-operation between aircraft, engine, and carburettor engineers; and for recognition in our procurement procedure of the need for pre- lininary check tests in actual flight, on prototype aircraft,-W* the design and characteristics of not only the scoop ai^T carburettor, but also all other engine accessories whose functioning may be affected by differences between flight and ground-test conditions Aircraft Carburetter Air Scoops and Their Effect on Fuelf Ait Metering in Flight. (F. C. Mock, S.A.E.J.) (U.S.A.). The Kensei Engine T HE engine had been damaged in a crash and only certain parts were available for inspection to the author, who carried out an examination on behalf of the Wright Aero nautical Corporation. The parts examined include: Crank case, crankshaft, piston and connecting rods, cylinder and valves, reduction gear, accessory drives and supercharger. Rear cover plate (including carburettor) and front cover plate (including propeller) are missing. The propeller was appar ently of the two-position type. The author concludes : (1) The Japanese designer combined in an ingenious manner proved features of a number of products of foreign manu facture, mainly American. The engine should be highly dependable, though not highly developed, and probably gave its rated output without requiring any subsequent modifications. (2) The manufacturing methods and equipment utilised pro duced parts of a quality comparable to the originals copied. (3) The materials utilised show that there were adequate supplies of Ni, Cd, Co, Cn, No and tungsten at the time of manufacture. It is interesting to note that this engine is not fitted with a vibration damper. The general data of the 14-cylinder radial engine are given below: Bore and stroke 5-5'n. x 5.92m. *"i Diameter 47in. Piston area 332 sq. in. Displacement i 1,970 cu. in. Compression ratio 6.6. Impeller diameter 9.62m Supercharger gear 8.48 x crankshaft. Performance estimate on 95-100 octane. Cruising 650 h p. at 2,000 r.p.m. Rated (8,000ft.) 850 h.p. at 2,250 r.p.m. Military rating (5,500ft.) and _- u _ , take-off I,05° h'P' at 2,5°° rP'm- Some Notes'cn Design Features of a Captured Mitsubishi Kensei Engine. (W. G. Owen. S.A.E.J.) (Japan.) Hydraulic Energy Diagrams SPACE time .recorders are essential for the calculation of energy diagrams of the hydraulic elements in landing-gear shock absorbers. Most of the instruments employed so far for this purpose depend on mechanical linkages and are thus sub ject to inertia errors. The author describes a photographic method for obtaining the necessary records. All that is needed is the attachment of flash-light bulbs to the parts requiring study and photographing the light track on a rotating drum covered with sensitised paper. The completed record takes less than 15 minutes to prepare. The Space Time Recorder (F. N. M. Brown, /. Aeron Sci, (U.S.A.)).
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