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Technical Paper
Anil D. Shah, Michael W. Patnoe, Ervin L. Berg
The design and certification icing envelopes for ice protection systems do not consider potentially severe icing conditions associated with supercooled large droplets (SLD). Criteria for the SLD icing conditions have not been established. Since aircraft operate in freezing rain and freezing drizzle during the winter months, it is important that we recognize the supercooled large droplet (SLD)1 environment and analyze its impact on aircraft operation and performance. Currently no database exists on freezing rain and freezing drizzle to describe the operating environment in which the aircraft may be exposed. There is a present need to have a better understanding of freezing rain and freezing drizzle conditions. Drop-size distributions (DSD) in icing clouds are analyzed. These data were obtained during the Canadian Freezing Drizzle Experiments (CFDE) I and III over the St. John’s Newfoundland regions and the Great Lakes, respectively.
Technical Paper
R. S. Barker, T. R. Alalusi, R. H. Horstman
This paper updates the analytical rationale and the computed results from those presented in the initial paper delivered on this subject (see the first reference listed below). The operational scheme is the same in this paper as in the earlier paper. The ACS Ventilation and Relief Valve (VRV) in the depressurizing Lab Module is wide open due to the need to suppress a large fire in the Lab or to remove the contaminated Lab atmosphere. All crew-men have evacuated the Lab Module and all previously open hatches in the Lab Module have been closed.
Technical Paper
George R. Keller
In order to prove the design validity of SST flight control and hydraulics systems prior to flight, the systems will be assembled and operated in testing fixtures under simulated operating loads and expected flight environments. Clearance for first flight will depend upon successful demonstration in the testing complex. The program is named CODE (from controls DEvelopment), and for the prototype airplane it is divided into two stages. Initially, component problems will be studied in a Preliminary CODE fixture using a triple-channel conceptual servo actuator under mechanical and electrical command. This Preliminary CODE will allow for variation in load inertia, simulated aerodynamic load, and in the compliance used to represent the flexible airframe. Flutter loads will be generated by an external force servomechanism. Data from the Preliminary CODE program will guide design of flight hardware for the prototype airplane.
Technical Paper
Robert W. Abshire
Requirements which establish the Boeing SST hydraulic system configuration are described. Development of materials and components, thermal and reliability study results, and weight reduction techniques are discussed. Careful consideration must be given to hydraulic system design for an SST to assure economical performance, extended life, and reliability in a severe environment, and to control weight of a large and high powered system.
Viewing 1 to 4 of 4