NASA Technical Note
Author :
Publisher :
Page : 624 pages
File Size : 16,37 MB
Release : 1972
Category :
ISBN :
Servosystem Design of a High-response Slotted-plate Overboard Bypass Valve for a Supersonic Inlet
Author : George H. Neiner
Publisher :
Page : 28 pages
File Size : 36,51 MB
Release : 1970
Category : Jet engines
ISBN :
Book Description
The servosystem design of a high-response airflow bypass valving system for supersonic mixed-compression inlets or other industrial or aerospace pneumatic systems is described. The valve utilizes a multislotted plate to achieve flow area change with minimum stroke and mass of moving parts. The servosystem utilizes a hydraulic piston-in-cylinder actuator close-coupled to a two-stage electrohydraulic servovalve. Using electronic compensation the small-amplitude response of the system, modulating 14 percent of its full flow area, is flat within 0 to -3 dB to 110 Hz. (161 cm [to the second power] ). A mathematical model of the system is presented and analytical responses are compared with experimental data.
Scientific and Technical Aerospace Reports
Author :
Publisher :
Page : 364 pages
File Size : 25,60 MB
Release : 1994
Category : Aeronautics
ISBN :
Book Description
An Automatic Restart Control System for an Axisymmetric Mixed-compression Inlet
Author : Gary L. Cole
Publisher :
Page : 44 pages
File Size : 18,3 MB
Release : 1969
Category : Airplanes
ISBN :
Book Description
Terminal-shock and Restart Control of a Mach 2.5, Axisymmetric, Mixed Compression Inlet with 40 Percent Internal Contraction
Author : Robert J. Baumbick
Publisher :
Page : 24 pages
File Size : 14,6 MB
Release : 1974
Category : Aerodynamics, Supersonic
ISBN :
Book Description
Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was coupled to either a choked orifice plate or a long duct which had a variable-area choked exit plug. Closed-loop frequency responses of selected diffuser static pressures used in the terminal-shock control system are presented. Results are shown for Mach 2.5 conditions with the inlet coupled to either the choked orifice plate or the long duct. Inlet unstart-restart traces are also presented. High-response inlet bypass doors were used to generate an internal disturbance and also to achieve terminal-shock control.
NASA Conference Publication
Author :
Publisher :
Page : 610 pages
File Size : 23,17 MB
Release : 1978
Category : Aeronautics
ISBN :
Book Description
NASA Technical Memorandum
Author :
Publisher :
Page : 1184 pages
File Size : 17,63 MB
Release : 1974
Category : Aeronautics
ISBN :
Book Description
U.S. Government Research & Development Reports
Author :
Publisher :
Page : 224 pages
File Size : 25,19 MB
Release : 1970
Category : Science
ISBN :
Book Description
Monthly Catalog of United States Government Publications
Author :
Publisher :
Page : 1388 pages
File Size : 50,95 MB
Release :
Category : Government publications
ISBN :
Book Description
Monthly Catalog of United States Government Publications, Cumulative Index
Author : United States. Superintendent of Documents
Publisher :
Page : 1348 pages
File Size : 35,13 MB
Release : 1970
Category : United States
ISBN :
