SUPERSONIC NOZZLE FOR A TURBOJET ENGINE
Assignee
SOCIETE NATIONHLE D'ETUDE DF CONSTRUCTION DE MOTEURS D'AVIATION (S.N.E.C.M.A.
Filed
Jan 12, 1984
Granted
Nov 5, 1996
Location
SAVIGNY SUR ORG FR
Abstract
Disclosed is a variable supersonic nozzle for a turbojet engine having an improved control system for varying the convergent and divergent nozzle flaps. All of the flaps are supported on several beams about the circumference of a gas passage. A control linkage interconnects hydraulic control cylinders, which are also mounted on the beams, with the convergent and divergent flaps such that, as the piston rod of the hydraulic control system extends and retracts, the angles of the flaps are varied accordingly. Additionally, cold flaps may be attached to the beams and interconnected with the linkage system such that their positions may also be varied by the control cylinder.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Nov 21, 1985
Rescinded
Jun 28, 1995
Duration
9 years, 7 months
Inventor
- 1ANDRE A.M.L. CAMBOULIVES
Record Details
- Patent number
- US 5571262
- Application
- 00065737
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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