Browsing by Author "Tetlow, R."

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    Design charts for carbon fibre composites
    (Cranfield Institute of Technology, 1958) Tetlow, R.
    This report contains charts of elastic properties and buckling coefficients of a simply supported compression panel, based on theory of multi layer plates of orthotorpic material, for a typical carbon fibre composite. In addition the optimum orientation of plies, of a three ply system, is considered for a corrugated compression panel together with the modifications necessary for other panel shapes. The computer programmes used are contained in the Appendix.
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    Design Project 1974/75 A 74 Aircraft Elevator Design.
    (Cranfield University, 1975-05) Mani Abraham, P.; Howe, D.; Tetlow, R.; Ward, R. E.
    Part 1 of this thesis contains the symmetric loading calculations and evolution of the design of elevator for the A 74 Reduced Take off and landing aircraft. Part 2 contains the analysis of final design of elevators. The aircraft is designed to the specifications of DES 7400 and satisfies the British Civil Airworthiness Requirement. A 74 project aircraft has longitudinal control from the tail plane and elevator combination. Tail plane is used for trimming and elevators for pitch controls. All control surfaces are hydraulic power operated. The tailplane uses an inverted supercritical section. The elevator is a four piece arrangement with duplicated hydraulic actuator system. It is of round nose type and the elevator hinge line is at 0.6 C. perpendicular to the aircraft centre line. As elevators are fully power operated mass balancing is not provided. Section 5 in part 1 gives the schemes considered in the design of elevator leading to the final choice of each major part. Section 6 gives the description of final design. Elevator is made of conventional built up construction using Aluminium alloy L 72 sheets and L 65 forgings. Part 2 gives the detailed stress analysis of the final design in accordance with normal aircraft design practise.
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    Failure of Laminated Fibre-reinforced Composite Structures Subject to Combined Loadings
    (Cranfield University, 1980) Nahas, Mahmoud Nadim; Tetlow, R.; Trotman, C. K.; Howe, D.
    A new modified maximum strain failure criterion is proposed to predict the failure of the laminae of laminated fibre-reinforced composite structures when the laminate is subjected to combined loadings. The new criterion takes into account the layer non-linear behaviour which is an important factor in the failure prediction operation. The analysis of laminated structures containing laminae with non-linear stress-strain response is also studied and a new method is proposed for this analysis. The modified failure criterion introduces two levels of failure. The lower level is associated with the “yield” of the lamina, or the beginning of the lamina degradation, above which the lamina will exhibit irreversible damage. The higher failure level however, is associated with the “ultimate” failure of the lamina, above which the lamina cannot sustain any load. Cont/d.