Patent GB-1193007-A (GB)
Title: Helicoptor having Provision for In-Flight Refueling
IPC: B64D39/04
Filed: 1968-03-29
Abstract: 1,193,007. Aircraft refuelling. UNITED AIRCRAFT CORP. 29 March, 1968 [3 April, 1967], No. 15203/68. Headings B7G and B7W. [Also in Division G3] A helicopter fuel system comprises an inflight refuelling probe 30 and an actuating mechanism 136, and a main fuel tank 46 (may be also 68 and 180, all mounted in the fuselage) and an auxiliary fuel tank 70 (and also 72 both of which may be jettisonable) mounted outside the fuselage 12, the actuating mechanism being powered by compressed air from the compressor 120 (or 122) of a gas turbine engine 24a (or 24b) to move the probe between a retracted position and an extended position when the probe extends beyond the periphery 29 of the disc area of the helicopter lift rotor 28. In the embodiment shown in Fig. 2, fuel may alternatively be supplied on the ground either under pressure through inlet 32 or under gravity through inlet valves 112, 114 which also act as pressure relief valves. Fuel may be passed from either auxiliary tank 70, 72 to the other, or to main tanks 46, 68 by appropriate pilot control of valves 130, 137 (supplying compressed air) 135, 139 (which open to vents) 52, 80 (which also automatically shut off when the appropriate tank 46, 68 is full) 90 and 102. Fuel from tank 180 may flow under gravity via valves 184, 188 to tanks 46, 68. Fuel may be jettisoned from the main tanks 46, 68 through valves 172, 174 by a rapid fuel dumping pump 150, fuel may also be passed from tanks 70, 72 at the same time. Refuelling probe (Fig. 3).-This 30 comprises a fixed cylinder assembly 250 and a probepiston assembly 252 reciprocable therein, comprising a double walled shaft 256, 258 extending from a probe tip 264 to a piston 260 which engages the inner surface of an outer cylinder 251 of the cylinder assembly which also has an inner cylinder 253, the annular space 259 between the cylinders 251 and 253 being divided into two chambers 282, 284 by the piston which has two grooves 266, 268 each engaged by a locking device 272 or 270 in the fully extended or fully retracted position. The assemblies 250, 252 may be of aluminium having the surfaces 810, 812 and 814 hard anodized. The locking devices 272, 270 may each comprise a retractable pin 266, 268 controlled by electrical circuitry, Fig. 4 (not shown) which also controls a multiposition valve 134 supplying compressed air to chambers 282, 284 and lighting indicators telling the pilot when the probe is extended, and also when the probe is not in a locked position. Jettisoning auxiliary tanks, Fig. 8.-The auxiliary tanks 70, 72 (see above) may be attached by links 600 pivoted as at 602 to the helicopter which also has arms 620, 622, 624, 626 to steady the tanks. The tank may carry mechanisms 612, 614 each carrying a pair of pins 608, 610 engaging the link 600. The pins 608, 610 may be retracted by a pilot operated lanyard (682), Fig. 9 (not shown) to release the tanks. At the same time the lines 94, 100, 132, 143, Fig. 2, are disengaged from the tanks and closed by tank shut-off valves. The Specifications 1,193,006 and 1,193,008 have identical disclosures but the claims are directed to a fuel valve and a flight refuelling probe respectively.