Reinforced electromechanical actuator housing

Abstract

An electromechanical actuator housing assembly comprising a reinforcement ring is disclosed herein. The design of the electromechanical actuator housing assembly may be directed to improving load measurement accuracy. The design of the electromechanical actuator housing assembly may be directed to reducing housing deflections. A method of manufacture of an EMA housing assembly is also disclosed herein. This method may include an electromechanical actuator housing assembly having a reinforcement ring.

1 . A method of manufacture of an EMA housing assembly, comprising:
 forging an aluminum housing of an electromechanical actuator having a reinforcement ring integrally coupled to the EMA housing, wherein the reinforcement ring comprises a housing geometry with material lying distal to a retaining surface of the EMA housing that decreases in axial distance as measured from a mounting flange while moving towards an axial centerline as measured from an exterior surface of the EMA housing.   
     
     
         2 . The method of  claim 1 , wherein the reinforcement ring is configured to reduce deflections of the EMA housing assembly. 
     
     
         3 . The method of  claim 1 , wherein the reinforcement ring is configured to reduce inaccurate measurements of a load cell coupled to the EMA housing assembly. 
     
     
         4 . The method of  claim 1 , wherein the reinforcement ring is configured to stiffen a braking system associated with the EMA housing assembly. 
     
     
         5 . The method of  claim 1 , wherein the EMA housing assembly comprises aperture surface that bounds a cavity configured to receive an ADU motor retention nut. 
     
     
         6 . A method of manufacture of an EMA housing assembly, comprising:
 forging a housing of an electromechanical actuator having a reinforcement ring integrally formed in the housing assembly with a retaining surface located axially between the reinforcement ring and a mounting flange of the housing assembly, wherein the retaining surface comprises a polygonal geometry, wherein the reinforcement ring is disposed distal to the mounting flange of the housing assembly, and wherein the reinforcement ring has a tapered geometry.   
     
     
         7 . The method of  claim 6 , wherein the reinforcement ring comprises a housing geometry that varies across two parallel planes perpendicular an axial centerline of the EMA housing. 
     
     
         8 . The method of  claim 6 , wherein a surface of the integral reinforcement ring comprises an exposed surface of the EMA housing assembly. 
     
     
         9 . The method of  claim 6 , wherein the maximum stress of the EMA housing assembly measured at 8500 lbs actuation load is less than or equal to 38.7 ksi. 
     
     
         10 . The method of  claim 6 , wherein the EMA housing assembly is installed on an aircraft. 
     
     
         11 . The method of  claim 6 , wherein the EMA housing assembly is forged of aluminum. 
     
     
         12 . The method of  claim 6 , wherein the EMA housing assembly is forged of steel. 
     
     
         13 . A method of manufacture of an EMA housing assembly, comprising:
 machining a housing of an electromechanical actuator having a reinforcement ring integrally formed in the housing assembly located above a retaining surface, wherein the top surface of the reinforcement ring comprises a housing geometry which slopes in a proximal direction moving towards the axial centerline of the EMA housing.   
     
     
         14 . The method of  claim 13 , wherein the reinforcement ring comprises a housing geometry that varies across two parallel planes perpendicular an axial centerline of the EMA housing. 
     
     
         15 . The method of  claim 13 , wherein a surface of the integral reinforcement ring comprises an exposed surface of the EMA housing assembly. 
     
     
         16 . The method of  claim 13 , wherein the maximum stress of the EMA housing assembly measured at 8500 lbs actuation load is less than or equal to 38.7 ksi. 
     
     
         17 . The method of  claim 13 , wherein the EMA housing assembly is installed on an aircraft. 
     
     
         18 . The method of  claim 13 , wherein the EMA housing assembly is machined of carbon composite.