Introduction to the Hawker Siddeley Harrierdoi: 10.1108/eb034581pmid: N/A
THE design concept of the Harrier (H.S.A. Type Number P.1127) arose over a few months in the summer and autumn of 1957 in studies by the Project Office at Hawker Aircraft Ltd., Kingston‐upon‐Thames. These studies were aimed at evolving a lightweight V/S.T.O.L. (Vertical and Short Take Off and Landing) strike reconnaissance aircraft round the Bristol Aero Engines Ltd. BE.53 engine.
The Achievements and Future Potential of the Harrierdoi: 10.1108/eb034583pmid: N/A
TO an extent so far unequalled, the engineering of the Harrier has reconciled the aerodynamic, propulsive, structural and controllability conflicts which have for so long denied the practical provision of satisfactory zero speed and transonic speed capabilities in a single vehicle.
Aerodynamic Design—Stability and Controldoi: 10.1108/eb034584pmid: N/A
THE Harrier is not only an effective V/S.T.O.L. machine, it is also an efficient strike aircraft. This has only been achieved by the solution of a wider than usual range of aerodynamic problems. Solving these problems has not been made easy by the apparent incompatibility of some of the requirements at the two extremes of the speed range. The intake, for example, has had to be endowed with an extremely high static efficiency at high mass flows to provide the best possible V/S.T.O.L. performance. At the same time excessive spillage drag could not be tolerated in conventional flight. This particular aspect is covered in detail elsewhere in this issue. Similar problems have arisen in the field of stability and control and this subject will form the main part of this chapter. Mention will also be made of some other aerodynamic aspects of particular interest.
Aerodynamic Design ‐ Air Intakedoi: 10.1108/eb034585pmid: N/A
WITH a vertical take‐off aircraft like the Hawker Siddeley Harrier, the only ground attack/ reconnaissance jet V/S.T.O.L. weapons system in operational service today, the air intakes have a vital influence on design and performance. At lift‐off and landing they need to absorb an exceptionally large flow of air with minimum loss. This demands a relatively large intake, which in turn increases the difficulty of keeping down drag during high speed flight. These design problems had to be met whilst providing also the ability to accept violent manoeuvring throughout all phases of the operational envelope.
Aerodynamic Design — Wingdoi: 10.1108/eb034586pmid: N/A
IN order to appreciate the development of the wing, it is necessary to understand how the basic objectives of the aircraft affect the wing, and the platform of knowledge on which the design was founded.
Structural Design of the Harrierdoi: 10.1108/eb034587pmid: N/A
THERE is no doubt that the outstanding difference between the structural design philosophy of the Harrier, as compared with conventional aircraft designed for similar duties, lies in the greater importance of achieving a minimum aircraft weight. This to be achieved with no loss in the ruggedness so essential to ground attack aircraft, especially when designed for use from advanced bases on semi‐prepared and natural sites. The structure represents some 35 per cent of the aircraft basic weight, and strenuous efforts have been made to keep this, together with the 65 per cent representing systems and equipment, to a minimum. It is, of course, necessary to attack weight at all times and in every aspect of design down to the smallest detail, and this policy has been pursued rigorously throughout the Harrier design.