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Aviation History
1922
1922 - 0484.PDF
ICHT AUGUST 24, 1922 THE HANRIOT TWO-SEATER FIGHTER, TYPE H. 15 An Interesting French All-Metal Machine AT the last Paris Aero Show there was exhibited on the Hanriot stand a very business-like racing monoplane, with cantilever wings, remarkable for its aerodynamic cleanness of design no less than on account of its all-metal construction. Certain of its details were not, perhaps, all that they might have been, but, generally speaking, the machine, which had been designed for last year's Coupe Deutsch, was one of very considerable interest. The racer was not finished in time to take part in the race, and we have not up to the present heard of it being tested in flight. However that unusual wing bracing, while some of the wing details are shown in the sketches. The fuselage construction consists of tubular longerons with triangular bracing, also of tubular construction. The front portion of the fuselage is covered with aluminium, but fabric is used from the pilot's cockpit to the stern post. Wing Construction Apart from the fact that it is fitted with a supercharger, the Hanriot 15 is chiefly interesting on account of the all- metal wing design, the fuselage construction showing fewer The New Hanriot All-Metal Two-Seater Fighter. may be, the Hanriot Works are carrying on with all-metal construction, and one of the latest to issue from the works for flying tests is the type H.15, for the illustrations and characteristics of which we are indebted to Our excellent French contemporary L'Adronautique. Designed for the Section Technique, the Hanriot 15 is an all-metal two-seater fighter pf unorthodox design. The power plant is a 300 h.p. Hispano-Suiza, and a Rateau super charger is fitted, as* the machine is intended to operate at great altitudes. As to how far the estimated performance will be realised, no information is as yet available. In the meantime, it is of interest to note that the calculated points of interest. From the accompanying sketches, it wilt be seen that each wing has one main spar only, but that this single spar is reinforced against torsion by two tubular auxiliary spars. The latter do not appear to be intended to take any part of the bending stresses. The main spar is of Duralumin, apparently of box section, terminating at the tip in a wooden end piece so as to avoid shaping the Duralumin box. The wing section is. deep, so as to allow of a good spar depth, but apparently the wing does not taper either in chord or thickness. The auxiliary spars are in the form of Duralumin tubes, and bolted to them, and passing through the main spar, are the tubular compression struts of the internal drag THE HANRIOT TYPE H. 15 : Some constructional details. In the drawing on the left, 1 and 2 are the top longerons of the fuselage ; 3 and 4, centre-section struts ; 5 and 6, sloping struts to lower plane ; 7, horizontal strut in top of fuselage. In the right-hand sketch, 1 is the Duralumin box spar ; 2, wooden end piece of spar ; 3, front auxiliary spar ; 4, rear auxiliary spar ; 5, aileron spar ; 6, tubular leading edge ; 7, rib flange (tubular) ; 8,[rib trellis ; 9, gusset plate, securing ribs to spar ; 10, aileron rib ; 11, aileron crank ; 12, tubular wing tip. speed at the height at which the H.15 is intended to operate 23,000 ft.) is 143 m.p.h. The theoretical ceiling (on the assumption that the supercharger works perfectly) is 33,600 ft., and it is estimated that the climb to 23,000 ft. will be accomplished in 25 minutes. It will thus be seen that, assuming the estimated performance to be attained, the Hanriot 15 should be a very useful machine for military purposes. As regards general design and detail construction, the former is shown by the accompanying photograph to be a considerable departure from orthodox lines, with its very bracing. The ',ribs are built up of Duralumin tubing, this material being used both for flanges and triangulated webs, as shown in the sketch. The wing bracing is unusual in. that the single ' struts are arranged to act as lift and anti-lift members at the same time. From a short distance out on the lower plane a strut runs to the top longeron of the fuselage, while another- strut slopes outward and upward to the top plane. The outer end of the lower plane is supported by a sloping strut running to the top centre section, crossing the lift strut en route. To reduce the bending moment on the fairly long bay in 484 /f.
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