Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB3015067A
Inventor
James Quintard Calkin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hawker Siddeley Aviation Ltd
Original Assignee
Hawker Siddeley Aviation Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hawker Siddeley Aviation LtdfiledCriticalHawker Siddeley Aviation Ltd
Priority to GB3015067ApriorityCriticalpatent/GB1236372A/en
Publication of GB1236372ApublicationCriticalpatent/GB1236372A/en
H01Q1/00—Details of, or arrangements associated with, antennas
H01Q1/08—Means for collapsing antennas or parts thereof
H01Q1/085—Flexible aerials; Whip aerials with a resilient base
Landscapes
Laminated Bodies
(AREA)
Abstract
1,236,372. Aerials. HAWKER SIDDELEY AVIATION Ltd. 30 Sept., 1968 [29 June, 1967], No. 30150/67. Heading H4A. An aircraft aerial consists of a projecting raked back member having a streamlined crosssection. The member is flexible transversely but shows substantially no torsional deflection about its raked back longitudinal axis when the aircraft is in flight. As described, the aerial 14 tapers down from root to tip and comprises a thin stainless steel skin 17, a solid stainless steel spar 19, and a rearward honeycomb filling 18. Forward of the spar 19 is a space 20 which is available for mass balancing using, for example, tungsten powder set in a suitable resin. The longitudinal neutral axis of torsional flexure, the mass axis, and the axis of aerodynamic loading are arranged to coincide at 16. The member is in stable equilibrium in flight, aerodynamic forces operating to counter any lateral deflection.
GB3015067A1967-06-291967-06-29Improvements in or relating to radio aerials for aircraft
ExpiredGB1236372A
(en)
Wind-tunnel investigation at Mach numbers from 1. 60 to 2. 86 of the static aerodynamic characteristics of a supersonic transport configuration with variable-sweep wings employing a double inboard pivot(Aerodynamic characteristics of variable sweep supersonic aircraft with pivoted wind)
XB-70 aerodynamic, geometric, mass, and symmetric structural mode data(Analysis of mass, structural, and aerodynamic data for XB-7 aircraft at three flight conditions)
In-flight measurement of rotor blade airloads, bending moments, and motions, together with rotor shaft loads and fuselage vibration, on a tandem rotor helicopter. Volume 1- Instrumentation and in-flight recording system(Instrumentation and recording system for aerodynamic loads and load effects on rotor and fuselage of flying tandem helicopter)
Dynamic stability of a flexible structure under controlled flight conditions with allowance for local stationary aerodynamic forces(Dynamic stability of flexible aircraft fuselage in controlled supersonic flight at zero angle of attack, basing analysis on elastic oscillation equations)
Aerodynamic problems posed by the concept of a supersonic transport(Optimization of supersonic and subsonic cruise, slow speed flight and flying qualities of supersonic transports)
Pilot tracking performance during successive in-flight simulated instrument approaches(Pilot tracking performance during in-flight simulated instrument approaches with single engine general aviation aircraft)
The role of aerodynamics and dynamics in military and civilian applications of rotary wing aircraft(Aerodynamic characteristics of helicopters with emphasis on airloads, aeroelasticity, and mechanical instabilities)
Preliminary study of supersonic-transport configurations with low values of sonic boom(Low sonic boom overpressure profiles for supersonic transport aircraft configurations)
Free-flight Investigation of Jet Effect on the Low-lift Drag and Longitudinal Trim of a Supersonic Interceptor-type Airplane Configuration with an Overhanging Tail Boom at Mach Numbers from 1.09 to 1.34