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
GB16315/58A
Inventor
Gerhard Eggers
Erich Haberkorn
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SASfiledCriticalSociete Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB867018ApublicationCriticalpatent/GB867018A/en
B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
B—PERFORMING OPERATIONS; TRANSPORTING
B64—AIRCRAFT; AVIATION; COSMONAUTICS
B64C—AEROPLANES; HELICOPTERS
B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
Landscapes
Engineering & Computer Science
(AREA)
Aviation & Aerospace Engineering
(AREA)
Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets
(AREA)
Elimination Of Static Electricity
(AREA)
Abstract
867,018. Dropping from aircraft. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. May 21, 1958 [June 18, 1957], No. 16315/58. Class 9(2). [Also in Group XXXIII]. A missile 2 is launched by a carrier aircraft 1 from which it is subsequently released at an appropriate altitude. The aircraft 1 has an annular wing 3 the interior surface of which is provided with three equi-spaced slideways 12 which co-operate with tracks (not shown) formed on the outer ends of three pins 8 on the missile 2. Locking means for securing the aircraft and missile together before separation comprise spring loaded, pressure released locking pins (not shown). Instead of a missile the slideways 12 on aircraft 1 may be used for the attachment of articles to be dropped.
Qualification of a HFB-320 Hansa and a Piaggio P 149 D for inflight simulation for the approach of a combat aircraft with high wing loading(Inflight simulation with high wing loading fighter aircraft approach using HFB-320 and Piaggio aircraft)
Flight measurements of some of the flying qualities and stability derivatives of a supersonic fighter airplane(Flight test to determine flying qualities and dynamic stability derivatives of supersonic fighter aircraft)
The static and dynamic-rotary stability derivatives of a model of the x-15 research airplane at mach numbers from 1. 55 to 3. 50(Static and dynamic rotary stability derivatives for X-15 aircraft at supersonic speeds)
Use of a large jet transport as an inflight dynamic simulator(Modified jet transport used as inflight dynamic simulator for supersonic transport low speed approach and landing characteristics)
Flight mechanical simulation from the user's point of view(Flight simulation of short takeoff aircraft and Dornier-31 aircraft, and results using cockpit simulator with 6 degrees of freedom for DO-31)
Program plan to develop airworthiness standards for STOL aircraft(Program plan to develop criteria for airworthiness standards applied to short takeoff aircraft used as transport service)
Flight test of the'ARAVA' Israel STOL airplane(ARAVA STOL aircraft, describing payloads, configuration, design flight testing, stability and landing characteristics)
Measurement full-scale of propelling nozzle performance in an attitude test facility(Full scale thrust performance tests of prototype dual stream propelling nozzle)
Flyover noise during take-off and landing of the series 50 DC-8 with P and WA JT 3 D-1 turbofan engines(Noise intensity levels under flight path of DC-8-50 with JT 3 D-1 turbofan engine during takeoff and landing)