Passively actuated variable area nozzle for an aircraft propulsion system

Abstract

An aircraft system is provided that includes a propulsion system structure and a variable area nozzle. The propulsion system structure includes a duct, and is adapted to move between a first position and a second position. The variable area nozzle is fluidly coupled with the duct. The variable area nozzle is adapted to move between a first configuration and a second configuration. An exit area of the variable area nozzle has a first value when the variable area nozzle is in the first configuration. The exit area of the variable area nozzle has a second value when the variable area nozzle is in the second configuration. Movement of the variable area nozzle between the first configuration and the second configuration is mechanically linked with movement of the propulsion system structure between the first position and the second position.

What is claimed is: 
     
         1 . An aircraft system, comprising:
 a propulsion system structure comprising a duct, the propulsion system structure adapted to move between a first position and a second position; and   a variable area nozzle fluidly coupled with the duct, the variable area nozzle adapted to move between a first configuration and a second configuration, an exit area of the variable area nozzle having a first value when the variable area nozzle is in the first configuration, and the exit area of the variable area nozzle having a second value when the variable area nozzle is in the second configuration;   wherein movement of the variable area nozzle between the first configuration and the second configuration is mechanically linked with movement of the propulsion system structure between the first position and the second position.   
     
     
         2 . The aircraft system of  claim 1 , wherein the movement of the propulsion system structure between the first position and the second position drives the movement of the variable area nozzle between the first configuration and the second configuration. 
     
     
         3 . The aircraft system of  claim 1 , wherein movement of the variable area nozzle from the first configuration towards the second configuration begins when the propulsion system structure moves from the first position towards the second position. 
     
     
         4 . The aircraft system of  claim 1 , wherein movement of the variable area nozzle from the first configuration towards the second configuration begins when the propulsion system structure moves from an intermediate position towards the second position, and the intermediate position is between the first position and the second position. 
     
     
         5 . The aircraft system of  claim 1 , further comprising:
 a stationary structure; and   a linkage system coupled to the stationary structure, the propulsion system structure and the variable area nozzle;   the linkage system adapted to move the variable area nozzle between the first configuration and the second configuration as the propulsion system structure moves relative to the stationary structure between the first position and the second position.   
     
     
         6 . The aircraft system of  claim 5 , wherein
 the propulsion system structure is movably connected to the stationary structure; and   a flap of the variable area nozzle is movably connected to the propulsion system structure.   
     
     
         7 . The aircraft system of  claim 5 , wherein the linkage system comprises a bell crank. 
     
     
         8 . The aircraft system of  claim 5 , wherein the linkage system comprises a cam element. 
     
     
         9 . The aircraft system of  claim 5 , wherein the linkage system comprises a first pulley, a second pulley and a tension member engaged with and spanning between the first pulley and the second pulley. 
     
     
         10 . The aircraft system of  claim 5 , wherein the linkage system comprises a track and a slider mated with and slidable along the track. 
     
     
         11 . The aircraft system of  claim 5 , wherein the linkage system comprises one or more linkages. 
     
     
         12 . The aircraft system of  claim 1 , further comprising:
 a fixed structure;   the propulsion system structure pivotally coupled to the fixed structure such that the propulsion system structure pivots between the first position and the second position.   
     
     
         13 . The aircraft system of  claim 1 , wherein
 the variable area nozzle comprises a first flap and a second flap;   the first flap is pivotally coupled to the propulsion system structure at a first side of the propulsion system structure; and   the second flap is pivotally coupled to the propulsion system structure at a second side of the propulsion system structure that is opposite the first side of the propulsion system structure.   
     
     
         14 . The aircraft system of  claim 1 , further comprising:
 a propulsor of an aircraft propulsion system;   the propulsor housed within the propulsion system structure.   
     
     
         15 . The aircraft system of  claim 1 , wherein
 the duct comprises a first duct, and the propulsion system structure further comprises a second duct in parallel with the first duct; and   the variable area nozzle is further fluidly coupled with the second duct.   
     
     
         16 . The aircraft system of  claim 1 , wherein a centerline of the duct when the propulsion system structure is in the first position is angularly offset from the centerline of the duct when the propulsion system structure is in the second position. 
     
     
         17 . An aircraft system, comprising:
 a propulsion system structure comprising a duct, the propulsion system structure adapted to move between a first disposition and a second disposition that is angularly offset from the first disposition;   a variable area nozzle fluidly coupled with and downstream of the duct; and   a linkage system adapted such that movement of the propulsion system structure between the first disposition and the second disposition drives actuation of the variable area nozzle through the linkage system.   
     
     
         18 . The aircraft system of  claim 17 , wherein
 the actuation of the variable area nozzle comprises movement of the variable area nozzle between a first configuration and a second configuration;   an exit area of the variable area nozzle has a first value when the variable area nozzle is in the first configuration; and   the exit area of the variable area nozzle has a second value when the variable area nozzle is in the second configuration.   
     
     
         19 . An aircraft system, comprising:
 an aircraft effector adapted to move between a first position and a second position;   a variable area nozzle; and   a linkage system adapted such that movement of the aircraft effector between the first position and the second position mechanically drives actuation of the variable area nozzle through the linkage system.   
     
     
         20 . The aircraft system of  claim 19 , wherein
 the aircraft effector comprises a propulsion duct; and   the variable area nozzle is fluidly coupled with and downstream of the propulsion duct.