bluuebunny/crossref_metadata_2025 huggingface dataset:
Television Broadcasting by Synchronous Satellite
Authors: Colburn P. J. , Squires D. M. , O’Hagan M.
Published: June 2018

In 1962 and 1963, the two Telstar experimental satellites were launched demonstrating the feasibility of transmitting television pictures by satellite link. Since this time, the Early Bird satellite (launched in 1965) and, subsequently, the Intelsat II satellites have demonstrated that point-to-point relay of television using synchronous satellites is an economic and a practical proposition for operational use. Many satellite systems have also been considered for television distribution between continents or between countries in a continent, or even within a country. Such satellites are Intelsat III, Intelsat IV, CETS-ESRO satellites and the Franco-German Symphonie satellites. The use of satellites for television distribution in this way solves only one small part of the television distributors problems. The largest problem is that of ensuring a good ground coverage of the broadcasting signals so that the percentage of homes which can receive television without complex aerials or amplifying equipment approaches 100%.
Earth Resource Satellite Systems
Authors: Pardoe G. K. C.
Published: June 2018

The direct use of satellites is already beginning to have enormous influence on the development of civilisation in our world. An initial study of the benefits to be obtained for mankind by the use of satellites to survey the natural and man-made resources of the earth leads to the inescapable conclusion that this will undoubtedly be one of the major applications of satellite technology that will evolve in the next few years. It is only very few years ago that the real impact of this use of space became evident, but already in that period of time an extremely wide range of types of measurements and different use of such data has been examined and a considerable amount of experimental work been carried out both in earth terrestrial laboratory conditions and also using equipment orbiting in space. There is now a wealth of data on what is possible already and might be possible in this new field of endeavour. I shall attempt in this paper to summarise the main potentialities of different types of systems and try and relate some of the key elements of the satellites to the natural resources being observed.
Fatigue Crack Propagation in Clad RR58 Sheet to DTD 5070A: Analysis and Correlation of Test Results
Authors: Rooke D. P. , Gunn N. J. F. , Ballett J. T. , Bradshaw F. J.
Published: June 2018

In recent years there has been an increasing need for data on the rates of fatigue crack propagation in alloys of interest to the aircraft industry. In general alloys in which cracks grow slowly, under given stress conditions, have an obvious advantage over those in which cracks grow faster; there is more time to detect a crack before failure. It is possible that, in the future, quantitative crack propagation data may be used to give better estimates of the safe life of a structure. There is, however, a need to rationalise the presentation of such data and to study the effect of such parameters as specimen geometry and stress level. Some experiments to investigate the effect of varying some of these parameters in one clad aluminium alloy, DTD 5070A are described. It is a summary of work contained in two RAE Technical Reports.
All-Weather Operation for Helicopters: Flight Control Systems for Helicopters
Authors: Collomosse H.
Published: June 2018

The term “All-Weather Systems for Helicopters” is capable of many different interpretations dependent upon operational requirements. Certainly there are no hard and fast rules laid down defining the equipment required to enable a helicopter to operate under adverse weather conditions. The accuracy to which the aircraft has to be flown under instrument conditions and the ability of the pilot to complete a given mission safely without undue fatigue are the prime considerations which need to be considered in determining the facilities and degree of sophistication necessary for a flight control system.
Procedures for Project Management Based on Detailed Programming
Authors: Williamson A. G.
Published: June 2018

During his presentation Air Cdre. Tyndall told you that the foundations of the procedures recommended by the Downey Committee were laid down in the late 1950's and early 1960's. May I remind you of the Internal Directive of March 1960 he mentioned which stated that cost control must be accorded equal importance with technical control. All of us have been developing our techniques of programming and monitoring technical achievements over the years, but at the time the investigations of current practice were being made for the Downey Committee in 1964-65 it was found that in twelve projects investigated only one contractor had procedures for monitoring and controlling cost progress adequately integrated with those for monitoring and control of technical achievement.
Effects of an Initial Gap on the Turbulent Jet Flow over a Curved Wall
Authors: Paranjpe S. C. , Sridhar K.
Published: June 2018

The flow in a two-dimensional curved wall jet with different initial gaps between the nozzle exit and the leading edge of the wall was probed at various stations along the jet. The jet slot thickness, the jet exit velocity and the radius of the wall were kept constant. It was found that the region close to the leading edge of the wall behaved like a settling zone. In this zone the type of flow changed from a free jet to a curved wall jet. The length required for settling depended on gap size and was less than that of the plane wall jet. Gap effects on surface pressure distribution and angular position of separation were examined. The hysteresis phenomenon associated with gaps was investigated.
Project Management and Technical Progress of the ESRO II Satellite Project
Authors: Hume C. R.
Published: June 2018

The ESRO II Satellite is due to be the first satellite to be launched as part of the joint co-operative programme between NASA and the European Space Research Organisation and as such, represents the first endeavour by the latter organisation to bring together various experiments in a satellite. While it is true to say that other satellites have been produced in Europe, this is the first integrated payload involving experiments from different countries to be realised in Europe.

The paper describes briefly the satellite and details the scientific experiments. The remainder of the paper is concerned with the aspects of project management involving four different nations and the technical programme.
Some Effects of Thickness on the Longitudinal Characteristics of Sharp-Edged Delta Wings at Low Speeds
Authors: Squire L. C.
Published: June 2018

Recently there has been renewed interest in the concept of an all-wing aircraft as a means of producing cheap air transport over relatively short distances. It is natural that with the large amount of information on slender wings now available an all-wing aircraft based on a sharp-edged slender planform should be considered for this role. One of the difficulties immediately faced in developing this concept is that since the aircraft must carry a large number of passengers it is necessary that as much of the wing area as possible should be deep enough to provide for a large passenger cabin. Thus the wing will be very thick over a large part of its area. If this condition is not met, then the aircraft has too much wing area and hence too high a structure weight. Typically one may think of an aircraft with a delta wing of aspect ratio 2 and with a wing thickness of from 15% to 20% of the root chord over as much of the wing area as possible. At first sight thickness of this order eliminates the main advantage of slender wings since the effect of thickness is usually to reduce the strength of the leading-edge vortices and hence the non-linear lift. Thus the incidence for a given lift is increased above that for a thin wing. This in turn means that the lift-to-drag ratio may be smaller.
Equilibrium Thermodynamic Properties Behind Strong Shocks in Helium
Authors: Lalor M. , Daneshyar H.
Published: June 2018

Tables of equilibrium thermodynamic properties of the ionized gas formed behind strong shock waves in Helium are presented, in the Mach number range 10 to 30, for initial pressures of 0-1, 0-5, 1, 5, 10, 50, 100 torr. The effect of the inclusion of the full partition function series is demonstrated in the Mach number range 20 to 30.

A numerical solution has been developed such that the only experimental quantities required for its use are the shock Mach number and the pre-shock conditions.
Selected Aspects of the Aerodynamics of Rotorcraft
Authors: Clarke A. E. , Bramwell A. R. S.
Published: June 2018

Both the authors have been members of a small Helicopter Research Team at the Royal Aircraft Establishment, whose main activities in recent years have already been described in papers presented at the V/STOL Loading Action Symposia held at Buffalo and Southampton in 1963 and 1965 respectively. It is a matter of regret that the size of this team, and indeed of corresponding teams elsewhere in Britain, has been such that significant reports could not be made more frequently. However, progress in research has been rapid elsewhere, particularly in the USA, and there has been a noticeable trend recently for changes in helicopter design. Hence, the Rotorcraft Section Committee requested a general survey of current rotorcraft aerodynamics. This is the object of the present paper, in which the findings of many workers in Western countries have been included. Even so, there will be omissions because the authors will not comment on subjects with which they have had no first-hand experience: rotor blade flutter and divergence is a notable omission on which there have been advances recently by the Massachusetts Institute of Technology and Southampton University.
Progress of the Rigid Rotor Concept
Authors: Culver I. H.
Published: June 2018

All of us know the history of the helicopter, but certain facets of this history need to be repeated in the framework of the development of the rigid rotor helicopter. It was in 1919, I believe, that Juan de la Cierva, shocked from the death of his brother in a spin accident, reasoned that the best way to build an aeroplane was to build one that made use of the spin as a fundamental. He put a bearing between the spinning wings and the fuselage so that the wings could spin without spinning the fuselage. This was a great advance in the state of the art and created an aeroplane with some rather good low-speed characteristics.
The Second Century Papers: Looking Ahead in Aeronautics—2. The Future for Agricultural Aviation
Authors: Wheeler A. H.
Published: June 2018

Predicting the future for Agricultural Aviation is rendered even more uncertain than predictions for most forms of aviation because in this case the future depends on two entirely separate sets of unknowns. These are the normal unknowns affecting aeronautical development but, more important, there are the unknowns affecting the development of agricultural chemicals. Also, in predicting the future evolution of any activity one must normally look back over the rate and the trend of developments in the activity, so far as they are relevant, from the past and then project this rate and trend into the future, bending and extending the line of projection in accordance with known or foreseeable influences. Here again we get a third set of unknowns related to future farming techniques, although these unknowns are perhaps less significant because the main expansion in agricultural aviation will probably lie in the vast undeveloped regions of the world where the farming techniques will merely be brought up to present standards, or just introduced where there was literally no agriculture before.
Helicopter All-Weather Operation—Equipment for the Transport Role
Authors: Curties M. C.
Published: June 2018

The theme of this lecture on Helicopter All-Weather Operation is a discussion of the equipment requirements for the helicopter in the transport role.

I have to say at the outset and possibly somewhat provocatively, that I believe that there are no real problem areas left, as far as the equipment means are concerned, between us and the realisation of a good all-weather capability in a transport helicopter. By this I mean that virtually all the basic work has been done in the main fields of guidance and control. Much of the equipment is already produced or in an advanced stage of development and most of that outstanding has already been defined and the feasibility of meeting the requirements examined. Thus, I believe, all that is required is a determination to achieve all-weather operation and to set in hand the processes of procuring the equipment. This means that the requirement has to be firmly stated and the price paid to meet it. It is idle to think that an all-weather capability can be achieved without an adequate equipment standard. However, it is reasonable to expect that its achievement should cost no more in the transport helicopter than for an equivalent standard in the transport aeroplane.
A Simplified Approach to Free-Surface Wave Drag Theory
Authors: Payne Peter R.
Published: June 2018

The problem of a two-dimensional pressure field moving over a free surface is analysed by dynamic modelling techniques. Using a simple second order linear differential equation, it is possible to obtain all the classical theory rersults for a uniform field in deep water. Squire’s results for the non-uniform pressure field of a planing wedge are also duplicated. Further results, not hitherto obtained with classical theory, may explain some anomalies associated with the classical theory. The method has the advantage that results for a large number of “pressure field distributions” have already been tabulated by workers studying the response of simple lumped parameter mechanical dynamic systems.

A conclusion of some practical importance in applied hydrodynamics is that the wave drag of a pressure field varies with its distribution. The more non-uniform a pressure field the greater its wave drag. The theory also gives insight into the occurrence of “humps and hollows” in model resistance curves, and gives some insight as to why a minor change in form may cause a major change in wave resistance.
Sudden Area Enlargement Pressure Recovery with Inflow Distortion
Authors: Tyler R. A. , Williamson R. G.
Published: June 2018

Pressure recovery measurements in a straight pipe with crossflow-generated entry velocity distributions suggested substantial effects of inflow distortion on the pressure recovery downstream of a sudden enlargement in area. This note reports results of actual measurements in the same pipe equipped with entry sections of various reduced diameters providing sudden area enlargement ratios of 1.33, 1.71, 2.04, and 3.52. The results have practical bearing on the performance of settling pipes located at diffuser exits where, in general, velocity distributions are significantly non-uniform. In addition, the results provide information on the momentum content of the crossflow-generated velocity distribution.
Complete Polynomial Displacement Fields for Finite Element Method
Authors: Dunne P. C.
Published: June 2018

It is generally accepted that the displacement patterns chosen to represent the deformation of a finite element should be such that there is complete compatibility with adjacent elements. Although some writers have doubted the necessity for the complete satisfaction of compatibility away from the reference nodes, provided the displacement pattern is capable of assuming certain uniform strain states, the desirability of complete compatibility is not in question. The displacement fields suggested in this note satisfy complete compatibility.
The Future Role of Computers with Special Reference to Aerodynamic Design
Authors: Thwaites Bryan
Published: June 2018

The computer is seen as the greatest invention in history, in that it has a universality which transcends all other known inventions. It will ultimately be capable ot any process describable in terms ot an open or closed logical structure.

In a deterministic science such as aeronautics, it has clear capabilities in the solution of the equations governing fluid flow, structures, propulsion, navigation and so on. The speed and size of future computers, together with all sorts of new software techniques, will facilitate almost instantaneous solutions of any problems, within the next century.

There will be two major constraints on these developments which we can predict with confidence. The first is financial. The second is more subtle: there may develop sociological resistance to technological advances, especially to those wielding the power implicit in future generations of computers, and this carries important implications for scientists.
The Royal Air Force Museum
Authors: Tanner John
Published: June 2018

From April to September of this year there will be numerous celebrations in honour of the Royal Air Force's 50th Anniversary, and it is highly appropriate that during this period the full plans for the Royal Air Force Museum are to be made public. The Museum is to be a new national institution maintained by the Treasury but built out of the sum obtained from a public appeal which is now in full operation.

A question constantly asked of all connected with this project is “who first thought of the idea?” The present writer has been told by at least a dozen men, all of them honest of eye and sincere of voice, that they and they alone were the only true begetter of the scheme, and it is a fact that every Station Commander who caused one or two aircraft to be preserved past the day of their official demise can feel that he and his men played some part in the slow development that has culminated in the present large-scale project.
A Standard Choked Nozzle for Absolute Calibration of Air Flowmeters
Authors: Sparkes D. W.
Published: June 2018

A choked nozzle installation suitable tor the absolute calibration of air flowmeters over a limited flow range is described. An entry package is prescribed to ensure that near ideal flow conditions are presented to the nozzle. This package should remove swirl and flow distortions from most entry flows.

Provided that the instructions given in this note are followed meticulously then the quoted discharge coefficients for the nozzle may be guaranteed to better than ±0-25% at Reynolds numbers greater than 106. The overall accuracy of flow calibrations are then dependent only on the accuracy with which the mean gas thermodynamic properties and condition of state at the nozzle entry can be determined.
The LUMINA Element for the Matrix Displacement Method
Authors: Argyris J. H.
Published: June 2018

It was pointed out in ref. 1 that various interpolation techniques could be used to develop elements (for the matrix displacement method) of increasingly more complex characteristics both as far as geometry and specification of strain are concerned. A number of authors have examined this problem in detail and attention is drawn to the excellent work of Bogner, Fox and Schmit on plate elements, and to the elegant paper by Pestel. Over a number of years the ISD at the University of Stuttgart has investigated the application of interpolation functions and has developed within the ASKA language a number of corresponding elements.
Further Comments on Pontryagins Maximum Principle Applied to the Profile of a Beam
Authors: Dixon L. C. W.
Published: June 2018

Following the appearance of my note on this subject in the July 1967 JOURNAL, Professor Hemp kindly pointed out a mistake in one of the basic assumptions. This has led to a recalculation of the results, and the correct results are given below.

a width of beam

b lower bound on height of beam

d upper bound on height of beam

E Modulus of elasticity

h (x) height of beam at position x

H the Pontryagin Hamiltonian

i second moment of area=ah3/12

i length of beam

M (x) bending moment =

rl, r2non-dimensional length parameters

p density al lengthparam

t non-dimensional length parameter=x/l

u non-dimensional length parameter=h/l

x horizontal distance from base of beam

y (x) vertical displacement of the centre-line of beam

Y error function in hill climbing sequence

Vectors

f phase space velocity vector =dX/dt

P adjoint vector

X non-dimensional state vector
Experiences of City Heliport Operations
Authors: Meyersburg Robert B.
Published: June 2018

This paper describes seven city heliports in the US, considering first their physical features and associated operating factors and, second, the possible application of the operational experience gained with these heliports to future heliport design.

Three of the seven heliports are in New York City—the Pan American Building rooftop, Wall Street Pier near the confluence of the Hudson and East Rivers, and the World's Fair Heliport. One is in Chicago, at Midway Airport. The remaining three are in California; Los Angeles International Airport, Anaheim / Disneyland, and Oakland.

Taken collectively, the seven heliports are representative of city heliport operation in the US today. Taken individually, they represent considerable variation in the significant factors affecting their operation, such as noise, height above ground level, traffic control towers, interface with other modes of transportation, both air and surface, lighting, instrument operation, obstacle clearance, turbulence, and related factors.
The Future City Centre Heliport
Authors: Payne N. J.
Published: June 2018

A forecast of future development for a period of 10 years postulates a complete change in civil air transport. Future city centre heliport developments are considered from an airport operator's point of view.

Full consideration has been given to helicopter sites in London by the Morris Report of 1961 and a VTOL Working Party of the Aeronautical Research Committee is now considering a report on the siting of Terminals for an Intraurban VTOL transport system.

Generally, the main considerations of committees on heliports consider the problems under the headings: —

1. Characteristics of the aircraft.

2. Noise limitations.

3. Safety, including aerodynamic effect of neighbouring buildings.

4. Air traffic control and operating procedures.

5. Traffic growth considerations.

6. Design layout and location of terminals.

7. Access to the city centre must be good and possibly not more than 15 minutes journey time.
The Second Century Papers: Looking Ahead in Aeronautics—6
Authors: Molyneux W. G.
Published: June 2018

Developments in computer technology will result in a capacity for structural analysis and definition of structural geometry in intimate detail, and this capacity will be used to the full for design and fabrication in the relatively brittle materials of high specific strength and stiffness that will become commonplace. However, only evolutionary developments in basic structural form are anticipated for the future, with stressed-skin structure remaining dominant. The structure will be windowless.

Mass-produced personal aircraft will be required for leisure purposes, and glass is likely to be a favoured structural material for these.
The Activities of ELDO
Authors: Iserland K.
Published: June 2018

I think that by now ELDO is sufficiently well known that I can assume its purpose and aims need no long explanation. I would prefer to give first a summary of its present situation, its achievements and the experience which has been gained; and at the end I shall give an indication of ELDO studies aimed at future activities.
The Impact of Speed on Transport
Authors: Edwards George
Published: June 2018

I am especially honoured to be invited to deliver the inaugural address of the newest branch of the Royal Aeronautical Society here in Ireland, with your exceptional contribution and involvement in both the pioneering and progress of commercial air transport. It is also a great pleasure to have my old friend Captain Jack Kelly-Rogers, one of the world’s truly great aviators and most appropriately your first Chairman, officiating tonight. As President of the Weybridge Branch of the Society I also bring you their greetings and best wishes.
The Hermes 8 Element for the Matrix Displacement Method
Authors: Argyris J. H. , Fried I. , Scharpf D. W.
Published: June 2018

The description of the LUMINA element in T.N. 11 is followed by another three-dimensional interpolation element, called HERMES 8, available in the ASKA language and briefly mentioned in ref. 1. Just as the LUMINA set, the HERMES element represents a general hexahedronal element with curved faces and has proved a most useful component block for three-dimensional analysis of complex bodies. The cardinal idea underlying the HERMES development aims at combining the advantages of the Lagrangian and Hermitian interpolation techniques.
The TET 20 and TEA 8 Elements for the Matrix Displacement Method
Authors: Argyris J. H. , Fried I. , Scharpf D. W.
Published: June 2018

Following on from the LUMINA and HERMES elements discussed in TN’s 11 and 12, this note analyses two further three-dimensional elements outlined in ref. 1. These new elements possess the desirable features of completeness and consequent invariance of the polynomials for the displacement fields. It has been shown in ref. 2 and stated in ref. 1 that third order complete polynomials yielding a second order or parabolic strain distribution fit into a tetrahedron element with 20 nodal points and 60 degrees of freedom, denoted within ASKA as TET 20 (Fig. 1).
A General Note on the Selection of Redundancies in Structural Analysis
Authors: Robinson John
Published: June 2018

This paper lists all the known published work on the development of automatic selection of redundancy techniques over the past decade. The main interest is a selection technique based on an algebraic procedure. It is emphasised that such a technique is very flexible in its application and that the redundancy selection can be completely automatic, completely preselected but automatically imposed or a combination of the two. This enables previous experience to be applied. The criterion is given for optimum redundancy selection and items which influence this are discussed. It is pointed out that the basic and redundant load transformation matrices can be generated automatically for general configurations.
Structural Aspects of the Do 31 Jet-Lift VTOL Aircraft
Authors: Flemming M.
Published: June 2018

The special structural problems of VTOL aircraft are examined, taking the Do 31 as a basis and it is shown how these problems can be solved without significant weight penalties.

After a short description of the aircraft and the systems associated with aircraft testing, the structural design of the Do 31 is described.

The effect of special VTOL load cases on the individual aircraft components are illustrated and it is shown where these are critical. The methods used in the calculations are explained briefly and theoretical results are compared with tests.

Special emphasis is given to the lift pod structure and its structural analysis.

There are special problems with VTOL aircraft which must be considered during the structural design phase. The effects of temperature on the engine pods, wing and fuselage are shown and the solution of the associated design problems are indicated. The results obtained are compared with a number of Do 31 test results.

If conventional British or US fire requirements are applied to the design of lift pods, there is a possibility of some weight penalties. Fire problems and fire requirements for lift pods are discussed with reference to test results. Recommendations for minimising the danger of explosions and for the use of fire detecting devices are also made.

A great advantage of VTOL aircraft is their ability to use unprepared sites. Debris may be thrown up by the downward deflected jet exhausts and strike the aircraft. Calculations and test results show the effect of impact velocities, stone shape, etc. Structural optimisation for withstanding debris impact is considered.

Noise problems have to be investigated during the aircraft design phase because of the high engine thrust installed in a VTOL aircraft. Results of the Do 31 tor near field noise levels are given. Particular attention is given to the proportion of overall noise level which affects the airframe.
The Second Century Papers: Looking Ahead in Aeronautics—8
Authors: Thring M. W.
Published: June 2018

Power generation for civilian aircraft can only be considered in terms of what kind of flying people will want to do in the 2nd century because the weight and cost of the fuel which will be best are dependent on how much people can afford to pay, how large and how fast they want the planes to be and what the world's total aircraft fuel consumption will be in relation to the world's total supplies of various fuels.

The predictable primary power sources of the second century are the fossil chemical fuels, oil and natural gas, the nuclear fuels (fission and fusion) and solar energy.
Increased Piloting Tasks and Performance of X-15A-2 in Hypersonic Flight
Authors: J. “Pete” Knight WM.
Published: June 2018

In past years, flying a basic X-15 from launch through a dead stick landing on a precise speed and altitude profile was considered a demanding piloting task. The success of each mission was determined by the pilot's ability to perform under the physiological and psychological stresses of flight into a hostile flight environment of high Mach numbers, high accelerations, high altitude, and limiting temperatures. Today the aircraft has been extensively modified to qualify the X-15 as a test bed vehicle for a ramjet engine, which will be carried in place of the movable ventral, providing real time flight environment for testing and developing an operational prototype ramjet for use on future hypersonic cruise vehicles. The additional systems pictured in Fig. 1 (external tanks, ramjet, external window, and ablative coating), their associated emergency procedures and the degraded flying characteristics of the X-15A-2 have increased the pilot's workload significantly over the standard X-15 mission.
Per Ardua—Peradventure
Authors: Goddard Victor
Published: June 2018

Before I begin to generalise about the RAF, let me make a generalisation about mankind and us islanders. All men are escapists by nature. What distinguishes islanders from all other men is that they are the progeny of active escapism. In the legends of antiquity these “Islands of the West” in which we live were the “Isles of the Blest”. Remote continentals longed to escape hither. That is something we tend to forget—not without reason nowadays!—although the process still goes on, in darker colours now. Aviation has become the most general and the most active form of escapism. It is essentially transcendental !
The Numerical Evaluation of Curvilinear Integrals and Areas
Authors: Nonweiler T. R. F.
Published: June 2018

We envisage here that it is desired to evaluate (using a digital computer) the integral of a function f (x, y) with respect to x (say), along a curve γ in the xy-plane; the value of the function and of the co-ordinates of the curve being known only at discrete, and possibly irregularly spaced, points of γ. Such a problem frequently arises, especially where γ is a closed curve: as for instance in aerodynamics when it is desired to estimate the force components and pitching moment inferred from an experimentally determined set of pressures taken over an aerofoil; here the function values are related to the pressure measurements and γ is the aerofoil contour.
The Dynamics of Low-Thrust Spacecraft Manoeuvres
Authors: Burt E. G. C.
Published: June 2018

Orbital manoeuvres by means of impulsive thrusts, such as those available with chemical rockets, are well known, but a different treatment is needed for the small, continuous thrusts that are typical of electrical propulsion systems. It is shown that with the aid of these small forces it is possible to change independently all the orbital elements of a spacecraft, and thus to proceed slowly from a given orbit to any other. For each manoeuvre there exists an equivalent velocity which depends only on the initial and final orbital states, and which can be related directly to the spacecraft propulsion parameters.

For any form of propulsion where the propellent acquires some or all of its energy from a separate energy source, as in electrical propulsion, it is found that optimum time-varying relations exist between the flow of mass and of energy, which may also be expressed in terms of the exhaust velocity and the thrust. In particular, the optimum exhaust velocity is shown to be an increasing function of time, related to the way in which the energy is released.

The practical realisation of electrical propulsion depends on the development of efficient propulsion units and of lightweight power supplies; these and other spacecraft components are discussed, and a number of examples of orbital manoeuvres are given, including close-Earth, far-Earth and lunar orbits. The paper concludes with a discussion of these orbital transfers in relation to their possible uses, including communication satellites and a test of relativity theory
The Effects of Solid Viscosities to Dynamic Load Factors of the Ring and the Hollow Sphere Subjected to Impulsive Loads
Authors: Suzuki Shin-Ichi
Published: June 2018

Although it has been said that dynamic load factor is equal to 2, it became evident by the author's researches that this value is influenced by the dimensions of members and loading conditions and is very different from 2. However, the solid viscosities are neglected in all these researches. Previously, the author obtained the coefficients of viscosities from the experimental results of damped oscillation of a cantilever beam in a vacuum vessel and investigated the relationships between dynamic load factors and solid viscosities on the beam and the rod subjected to transverse or longitudinal impulsive loads. From these results, it was found that the effects of solid viscosities to dynamic load factors cannot be neglected.

To find out whether the same fact can be obtained for the higher dimensions or not, the ring and the hollow sphere subjected to uniformly distributed impulsive loads along the inner and outer edges are analysed. Since σθ, the direct stress to the circumferential direction, is the most important from the engineering point of view, the relationships between solid viscosities and dynamic load factors of σθ are investigated.
Blockage Corrections for Blunt-Based Bodies of Revolution
Authors: Mair W. A.
Published: June 2018

Calvert has considered alternative methods of estimating the blockage corrections for blunt-based bodies of revolution in closed wind tunnels at low Mach numbers. His models were all of maximum diameter 152 mm, with an ellipsoidal nose section 203 mm long followed by a cylindrical afterbody. The ratio of overall length L to maximum diameter d varied from about 1.5 to 5.5. For each model the base pressure was measured in wind tunnels of two different sizes, so that the blockage correction factor e for the smaller tunnel could be derived for each model from the experimental results. These experimental values of e were compared with alternative theoretical estimates, using the methods given by Evans, Maskell and Pank-hurst and Holder.
Roll Dynamics of a Spinning Axi-Symmetric Satellite in an Elliptic Orbit
Authors: Modi V. J. , Neilson J. E.
Published: June 2018

Attitude dynamics of a spinning, axi-symmetric, rigid body undergoing central force motion has received considerable attention in recent times. Thomson et al studied the problem where the satellite was restricted to follow a circular trajectory. This stipulation reduced the system to an autonomous form which was then treated by linearised or Liapounov type of analysis. For the satellite in an elliptic orbit, Kane and Barba presented numerical solution to the linearised equations of motion. Recently Wallace and Meirovitch investigated the same problem by performing asymptotic analysis on linear and low order non-linear systems.
Two Probes for the Measurement of the Complete Velocity Vector in Subsonic Flow
Authors: K. Dau  , McLeod M. , Surry D.
Published: June 2018

Two probes which have been developed at the University of Toronto's Institute for Aerospace Studies for the purpose of determining the complete velocity vector in subsonic flow are described. That is, both probes provide the magnitude of the velocity at a point plus the two angles which determine the vector's orientation. The first probe, which also measures static pressure, was developed by K. Dau to determine wake properties behind a blowing wing. It uses a multiple pressure-hole technique. The second probe was originated by K. Dau and D. Surry and experimentally developed by M. McLeod. It is basically a spinning hot-wire probe whose periodic waveform uniquely defines the complete velocity vector.
Commonwealth Caribbean Air
Transport
Authors: Went T. E.
Published: June 2018

I would like to express my thanks to the Council of the
Royal Aeronautical Society for inviting me to
deliver this lecture. I am very happy that this
honour has been extended to me: I am happy for
myself, and also for my country, Barbados, one of
the newest sovereign states, but one which has
evolved with the British Commonwealth. Our
relationship has existed since 1625 and apart from
what I believe to be the first case of UDI in the
British Colonial Empire in the Cromwell era, we have
been stalwart members of the club.

In November 1966 Barbados became a sovereign state, the
colonial days were over. From here on we have been a
full member of the British Commonwealth of
Nations.
IATA—Very Suspicious
Characters
Authors: Hildred William
Published: June 2018

Sir William Hildred drew upon his personal experiences
until 1966 as Director General of the International
Air Transport Association.

That body worked closely with the International Civil
Aviation Organisation (ICAO)—the author, instigator,
and watchdog of Annex 9 of the Chicago Convention
which dealt wholly with the subject of facilitation.
Neither body had legislative power. ICAO could only
make recommendations but these required the assent
and action of Sovereign Governments before they
became effective. The President of ICAO had said it
was the increase in passenger and cargo volume which
created the problem but Sir William ascribed a good
deal of it to the entrenched conservatism of
Governments and their operating agencies.
Immigration
Authors: Fitzgerald T.
Published: June 2018

Immigration control is an expression of national
interest. The objective is to ensure that, of all
those people who wish to come from abroad to work
and settle here, we should accept only those whom it
is in the national interest to accept. The process
of selection must be operated in a way which does
not delay or inconvenience the great generality of
travellers.

In more detail, the current objectives of the UK
immigration control are: —

(a)

to prevent the
entry of people who are personally unacceptable,
for example, because of criminal
record;

(b)

to
protect and supplement the resident labour
force;

(c)

to
prevent immigration of a type, and on a scale,
which might give rise to serious social
problems.
Major Allister Macintosh Miller:
1892—1951
Authors: Van der Spuy K. R.
Published: June 2018

I Feel highly honoured at having been asked to deliver
this inaugural lecture as a prelude to the bi-annual
series of Memorial Lectures on the development of
Civil Aviation in South Africa. This lecture will be
devoted to the man—Major Allister Macintosh
Miller.

Much has come about in the field of Civil Aviation
since the days I am going to speak about. Space and
time have been telescoped. Colossal strides have
been made. In this hall tonight I see a number of
persons who, like myself, are able to make the
comparison between the civil aircraft of vintage
1919 and the civil aircraft of today.
The Limitations of Wide Strut Analyses for
Determination of the Optimum Proportions of Panels
Having Unflanged Integral Stiffeners
Authors: Grayley M. E.
Published: June 2018

Determination of the cross-sectional dimensions of
panels of least weight typically follows the
procedure set out by D. J. Farrar in this JOURNAL 20
years ago. Farrar made the assumption that for
panels of least weight the flexural and local
instability stresses were coincident. Using this he
investigated the Z-section stringer-skin combination
and later, using the same method, E. J. Catchpole
studied the panel having unflanged integral
stiffeners. In both cases the panel is treated as a
wide strut, i.e. the flexural buckling load was
taken to be the Euler buckling load, no account
being taken of the effect of edge restraint.
Selection of Interplanetary
Trajectories
Authors: Musker A. J.
Published: June 2018

It is only in fairly recent years that the idea of
sending an object to another planet has become a
practical reality. This has led to the rapid
development of celestial mechanics, although the
subject is by no means new. The purpose of the paper
is to introduce the subject and to see how
well-established results and equations may be
utilised to find out about the motion of an object
on its way to another planet. Once the path is
determined, various deductions may be made about the
rocket vehicle which must place the object or
spacecraft along that path.

The concept at “launch window” will be introduced and a
method of determining it will be presented. Once it
is known, the number of available trajectories
(although theoretically infinite) are narrowed down
by selecting desired values of some parameters.
Turbulent Boundary Layers
Authors: Bradshaw P.
Published: June 2018

In this lecture I hope to bring together the two branches of turbulence studies, (1) the fundamental study of the physics and mathematics of turbulent flow and (2) the methods of calculating turbulent flow development which are used by aircraft designers and other fluid dynamicists. While it is entirely reasonable that aircraft designers should wish to predict the behaviour of turbulent boundary layers without going deeply into the physical processes which govern their development, it is by no means reasonable that those who develop calculation methods in the first place should ignore the physics of the flow, or represent it by simple-minded formulae chosen for mathematical convenience rather than physical plausibility. Turbulence is not a simple phenomenon! The more naive integral methods that were in vogue until a few years ago have been disposed of once and for all by Thompson. The only method that emerged from Thompson’s review with any credit was Head’s entrainment method, which was distinguished from most of the other integral methods by being based on a clear physical hypothesis about turbulent flow. Head himself regarded this hypothesis as a very crude attempt to represent the entrainment properties of the turbulence, and indeed it is easy to see that this sort of hypothesis must fail in some of the more difficult situations.
A Hydraulic Transmission System for Powered Wind-Tunnel Models
Authors: England K. J.
Published: June 2018

A hydraulic transmission system is evaluated as a drive for wind-tunnel model propellers and fans. The system compares favourably with existing electrical transmission systems and appears to have other applications in wind-tunnel work.
Managing Costs for Profit: Part I—Business Objectives and Strategic Planning
Authors: Norman P. A.
Published: June 2018

This paper presents basic disciplines for effective management of costs for profitable operation in technologically orientated industries. The techniques outlined for strategic planning, implementation of the ensuing plan and for operational planning and control are not new, but available and proven by wide application in the USA and to a lesser extent in the UK.

The adoption of these or similar disciplines in the UK aerospace industry in co-operation with the Government in defining industry objectives and strategic plans, could represent a big step towards promoting a healthy and expanding industry for the future.

Application of these techniques will present difficulties in the aerospace industry, but by their very nature should yield an immense return in this environment. There would appear to be no insuperable difficulties in achieving successful application by both Government and Industry.

Since the 1967 Management Studies Group Symposium showed a strong demand for information on these techniques, and because no single source document can be recommended, the preparation of this survey has been undertaken.
The Five Point Loading Shear Stiffness Test
Authors: Langley Marcus
Published: June 2018

Howard suggested that the shear stiffness of a beam in bending could be more expeditiously determined by using the five point loading system.

Grayley reviewed the accuracy and speed of various methods of finding the shear stiffness of sandwich beams and showed that five point loading compared favourably on all counts with three point loading, four point loading, and with block shear tests.

The RAeS Data Unit gave a description of an experimental method of determining the shear and flexural stiffnesses of a sandwich material, based on Howard's work.
Bullous Pemphigoid in an Infant: A Case Report
Authors: Thabouillot Oscar , Le Coz Julien , Roche Nicolas-Charles
Published: June 2018

A seven-month-old girl was referred to the emergency department (ED) after a general practitioner suspected Steven-Johnson syndrome. Actually, the diagnosis of bullous pemphigoid (BP) was made based on biopsies; BP is a rare, autoimmune skin disease involving the presence of blisters known as bullae. The child was efficiently treated with topical steroids. This case shows the importance of the ED physician’s prior knowledge of BP so that a differential diagnosis with other autoimmune diseases (dermatosis, pemphigus) can be made.

Thabouillot O, Le Coz J, Roche NC. Bullous pemphigoid in an infant: a case report.Prehosp Disaster Med.2018;33(4):448–450.
Uncertain Futures: Organisational Influences on the Transition from Work to Retirement
Authors: Phillipson Chris , Shepherd Sue , Robinson Mark , Vickerstaff Sarah
Published: June 2018

The promotion of extended working life has created a period of uncertainty between the ending of work and the beginning of retirement. This period of the life course is now ‘open-ended’ in respect of whether older workers decide to remain in employment or leave working. However, the choices available are framed within public policy and organisational contexts as well as personal circumstances. The study reviews the organisation of ‘work-ending’, the construction of age within organisations, and the influences on provision of support in late working life. The article concludes with a discussion on the range of pressures that might limit control over pathways through middle and late working careers.
Irish Female Members of the European Parliament: Critical Actors for Women's Interests?
Authors: Cullen Pauline
Published: June 2018

The European Parliament (EP) is credited as an important actor in improving the rights of women in Ireland. Lacking a power base in national political parties, Irish feminists and European Union (EU) officials, including members of the EP (MEPs), have worked to secure progress on gender equality. This research explores whether, in the contemporary context, Irish female MEPs remain critical actors for women's interests at the EU level. Findings show that although Irish female MEPs have a limited record of involvement with the EP's main site for gender equality, the Committee on Women's Rights and Gender Equality, they do act in a variety of ways on women's interests. These include mobilization on gendered occupational roles and traditionally gendered areas such as care work, child poverty, and issues constructed as affecting women outside the EU. Irish female MEPs also facilitate forms of supranational lobbying in their support of EU-level advocacy for domestic gendered civil society and campaign groups. However, ideology and party political discipline, the pull toward local and national interests, and an absence of strong feminist agency work to diminish opportunities for female MEPs to act as critical actors and deliver critical acts on women's interests.