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In this paper we consider the design of a power system stabiliser using the least‐integral‐square‐error algorithm. Describing function technique is employed to take the nonlinearity of exciter saturation into account. Results, obtained from the digital simulation of a sample power system, show that the proposed power system stabiliser can greatly improve the dynamic stability of the power system.

Smiths Industries is to supply the head‐up display system for the Sea Harrier. The company will design, develop and make the electronic head‐up display and weapon aiming computer system for the latest version of the HS Harrier which will operate from Royal Navy ships.

THE increasing use of low‐wing monoplanes has emphasized the susceptibility of this type of aeroplane to detrimental wing‐fuselage interference. This interference was first indicated by the inferior aerodynamic characteristics of the low‐wing as compared with the high‐wing monoplane.

THIS study has been conducted by the engineering section of the Aeronautics Branch for the purpose of developing a method of load factor determination which will be as nearly theoretically correct as possible, yet capable of being applied without difficulty by the average aeroplane manufacturer. Another aim has been to avoid making too abrupt changes in the present system of load factors, so that a minimum of confusion and controversy would be caused by the adoption of the new method.

DEVELOPMENT of new manufacturing technologies, together with optimisation of advanced production methods already in use, is essential to secure the future of the aircraft industry. It is no longer sufficient, however, merely to master these technologies; it is important that they should be used to aid productivity. The Transport Aircraft Division (UT) of the MBB Group has a team of specialists working in Hamburg on the development of advanced production processes. One of the team's objectives is to achieve a high standard of productivity and flexibility while maintaining good, consistent quality.

The high cost of copper combined with a world shortage has emphasised the need for economy in its many applications. The manufacture of printed circuits by the etched foil technique produces a wastage of 60–80% of the copper cladding of the boards and although recovery of the copper can be effected, the process is costly and time consuming to an extent that makes it impracticable for the printed circuit manufacturer. With the increasing use of additive processes for printed circuit manufacture and the consequent saving in copper wastage, the use of electroless copper plating has assumed even greater significance than for its application to through hole plating and the advantages gained by freedom from the current density problems associated with electroplating need no stressing.

INTRODUCTION HIGH utilisation potential in short haul operation at low cost is a keypoint in the F.28 design concept. This requires excellent qualities regarding servicing and maintenance to complement the aircraft's performance and economy in flight.

AIRBUS Industrie will shortly deliver the first A310–300, a long range version of the A310. The new airliner will carry 218 passengers non‐stop over 8,500km. One of the technological features of this aircraft is the trim tank system which, by disposition of the fuel, permits optimum control of the centre of gravity in the longitudinal axis; the aircraft is trimmed by the process of pumping fuel into a trim tank. The trim tank system comprises an additional fuel tank in the horizontal stabiliser, pumps, valves, sensors, a digital computer and a fuel line between the horizontal stabiliser and the main tank in the wings.

MODERN HIGH PERFORMANCE AIRCRAFT with large envelopes, a variety of external stores and possibly, variable geometry as well, cannot exhibit sufficient inherent stability (static and dynamic) and conformity of handling qualities without the use of artificial stabilisers. This is especially true for vertical take off and landing aircraft which exhibit either neutral stability or instability during hovering and transition.