A general discussion is presented herein, to outline the starter functions which are necessary for a successful engine start. In addition, sample calculations are included to illustrate an accepted method of determining the engine starting time from known data. Further consideration is then given to the relationship between starter torque output and engine pad strength and a generalized formula is presented for calculating the theoretical transient torque peaks for a simplified starter-engine system. Sample calculations for actual tests are included, and the results of these calculations are compared with measured values.

AE-6 Starting Systems and Auxiliary Power Committee

The Pond Racer - An Exercise in the Control of Heat Transfer in a Tight Composite Compartment

93015403/01/1993

The POND RACER is an all-Composite, twin boom airplane Figure 1,(1), (2), (3), fitted with two, dual turbocharged automotive engines. The exhaust system, Figure 2, for this six cylinder power plant occupies the rear portion of a compact engine compartment. Initially, no provision was made for moving cooling air through this densely-packed engine compartment. Portions of the exhaust system passed within less than 2.5 cm (1 in.) of the composite cowl enclosing the engine compartment. The temperatures developed could result in failure of the computer,which controls the engine, other components, and the composite cowl in a matter of minutes. Currently-used insulation designs did not appear to provide enough capability to work for this application. A Thermal Protection System was developed, installed, and proven out during test flights. Analysis of the flight data, measured by thermocouples linked into the flight recorder, verified the adequacy of the Thermal Protection System. These

Trelease, Robert B.

Prediction of Engine Casing Temperature of Fighter Aircraft for Infrared Signature Studies

92096104/01/1992

Prediction of Engine Casing Temperature of Combat Aircraft for various operating conditions needs modeling of convective and radiative heat flow from the jet pipe to the casing. Radiation modeling which implies modeling of multiple reflections and scattering is done here by the radiance-irradiance approach. The engine layout is approximated by three co-axial cylinders and axially discretized. The shape factors (which account for the directional dependence of radiation heat flow) for various configurations needed in radiation modeling are analytically obtained by a sequence of shape factor algebra from standard configurations. The resulting non-linear algebraic equations of combined convection and radiation heat flow are solved by an iterative technique to give the engine casing temperatures which may be used for infrared signature studies.

Mahulikar, Shripad Prabhakar

Integrated Air Separation and Propulsion System for Aerospace Plane with Atmospheric Oxygen Collection

92097404/01/1992

Aerospace plane with atmospheric oxygen collection for oxidizer supplying on rocket part of trajectory is very attractive concept. The key unit of power plant of such plane is an air liquefaction and separation system. It is proposed to accomplish the oxygen extraction on the bank of vortex tubes of special kind. The compressor of low speed turbojet engine would served in oxygen collection phase of flight as pressure generator for air separation system. Poor air after oxygen extraction is supposed to use actively in one of power plant combustion chambers. The configuration of integrated air separation and propulsion system and results of estimation of system using on two stage aerospace plane are discussed.

Balepin, V.V., Tjurikov, E.V.

Propulsion Systems with Air Precooling for Aerospaceplane

91118204/01/1991

Using LH2 heat sink capacity for air precooling in turbojets allows to increase specific impulse and in many cases to reduce specific mass (mass-to-sea level thrust ratio). A number of precooled turbojet schemes are considered. Classification of turbojet according to the cooled air amount and depth of cooling is proposed. ATR with extended precooling (Tout=100K) is examined in more detail. For propulsion systems including different types of engines, running simultaneously the concept of LH2 heat sink capacity concentration for turbojet air precooling is proposed.

Rudakov, A.S., Balepin, V.V.

A Canadian Government Look at Airworthiness

880935

03/01/1988

The paper traces the development of the approach to airworthiness taken by Canadian government authorities from its origin through to current practices. It describes the Aerospace industry, the carriers and general aviation in statistical terms, indicates the impact of economic regulatory reform and suggests the way ahead for Canadian and other authorities lies in the attitude and methodologies practiced by the European authorities in their development of JARs. I SHOULD PERHAPS start this presentation with a short word about authorities. At the conclusion of a speech on safety regulation by Mr. Ronald Ashford of the UK Civil Aviation Authority, reported in Flight International of April 19, 1986, the following quotation from St. Paul to the Romans appeared: “You wish to have no fear of the authorities? Then continue to do right and you will have their approval, for they are God's agents working for your good”. Aprocryphal or not, this would appear to give some divine authority for our

Mew, John F., Torck, James A.