Mitigating transonic shock wave with plasma heating elements

Abstract

Systems and methods for enhancing operations of an aircraft may include a plasma generator, a sensor, and a controller. The plasma generator may be positioned on an exterior of the aircraft such that it can provide localized heating thereon. The sensor may be configured to sense and transmit information regarding a transonic flight condition such as speed to the controller. The controller may be configured to activate the plasma generator in response to information from the sensor, so as to mitigate a transonic shock wave through localized heating.

1 . A system for enhancing operations of an aircraft, comprising:
 a plasma generator on an exterior of the aircraft;   a sensor configured to sense and transmit information regarding a transonic flight condition; and   a controller configured to activate the plasma generator in response to information transmitted from the sensor regarding the transonic flight condition, so as to mitigate a transonic shock wave.   
     
     
         2 . The system of  claim 1 , wherein the information regarding the transonic flight condition comprises information regarding at least one of speed, altitude, and temperature. 
     
     
         3 . The system of  claim 1 , comprising an additional sensor configured to sense and transmit information regarding a transonic flight condition. 
     
     
         4 . The system of  claim 1 , wherein the plasma generator comprises a set of electrodes. 
     
     
         5 . The system of  claim 1 , comprising:
 a power source configured to provide power to the plasma generator;   wherein the plasma generator is flush with an exterior surface of the aircraft; and   wherein the controller is configured to transmit a signal to the power source to provide power to the plasma generator, only after determining, based on information transmitted from the sensor, that activation of the plasma generator would mitigate a transonic shock wave.   
     
     
         6 . The system of  claim 1 , comprising:
 an additional plasma generator on an exterior of the aircraft;   wherein the controller is configured to activate the plasma generators independently of one another; and   wherein the controller is configured to activate the additional plasma generator only after determining, based on information transmitted from the sensor, that activation of the additional plasma generator would mitigate a transonic shock wave.   
     
     
         7 . The system of  claim 6 :
 further comprising additional plasma generators;   wherein the plasma generators are grouped in clusters; and   wherein the controller is configured to activate the plasma generators in a given cluster independently from the plasma generators in another cluster.   
     
     
         8 . The system of  claim 6 :
 wherein the controller is configured to determine, based on the information transmitted from the sensors, whether each plasma generator would be activated in an optimal configuration, and wherein the controller is configured to activate only those plasma generators that would be activated in the optimal configuration.   
     
     
         9 . The system of  claim 8 , wherein the optimal configuration comprises a transonic shock wave mitigating configuration. 
     
     
         10 . The system of  claim 8 , wherein the optimal configuration comprises a fuel efficiency optimizing configuration. 
     
     
         11 . The system of  claim 1 , wherein the plasma generator is positioned on a wing of the aircraft. 
     
     
         12 . A method for enhancing operations of an aircraft, comprising:
 providing a system comprising:   a plasma generator on an exterior of the aircraft;   a sensor configured to sense and transmit information regarding a transonic flight condition; and   a controller configured to activate the plasma generator in response to information transmitted from the sensor regarding the transonic flight condition;   sensing, with the sensor, the information regarding the transonic flight condition;   transmitting the information regarding the transonic flight condition from the sensor to the controller;   determining, with the controller and based on the information regarding the transonic flight condition, whether activation of the plasma generator will mitigate a transonic shock wave; and   upon determining that activation of the plasma generator will mitigate a transonic shock wave, activating the plasma generator, so as to mitigate a transonic shock wave.   
     
     
         13 . The method of  claim 12  wherein the system comprises a power source configured to provide power to the plasma generator, and wherein activating the plasma generator comprises transmitting a signal from the controller to the power source to provide power to the plasma generator, upon determining that activation of the plasma generator will mitigate a transonic shock wave. 
     
     
         14 . The method of  claim 12 , wherein the information regarding the transonic flight condition comprises information regarding one of speed, altitude, and temperature. 
     
     
         15 . The method of  claim 12  wherein the system comprises an additional sensor configured to sense and transmit information regarding the transonic flight condition, and wherein sensing, with the sensor, information regarding the transonic flight condition comprises sensing, with both sensors, information regarding the transonic flight condition. 
     
     
         16 . The method of  claim 12  wherein the system comprises an additional sensor configured to sense and transmit information regarding an additional transonic flight condition, and wherein sensing, with the sensor, information regarding the transonic flight condition comprises sensing, with separate sensors, information regarding separate transonic flight conditions. 
     
     
         17 . The method of  claim 12  wherein the system comprises an additional plasma generator on the exterior of the aircraft, and wherein the controller is further configured to activate the additional plasma generator in response to information transmitted from the sensor regarding the transonic flight condition. 
     
     
         18 . The method of  claim 12  further comprising:
 determining, with the controller and based on the information regarding the transonic flight condition, whether activation of the additional plasma generator will mitigate a transonic shock wave; and 
 upon determining that activation of the additional plasma generator will mitigate a transonic shock wave, activating the plasma generator, so as to mitigate a transonic shock wave. 
 
     
     
         19 . The method of  claim 12 :
 wherein the controller is configured to activate the plasma generators independently from one another;   wherein the system comprises a power source configured to provide power to each plasma generator; and   wherein activating each plasma generator comprises transmitting a signal from the controller to the power source to provide power to that plasma generator.   
     
     
         20 . The method of  claim 12 :
 wherein the controller is configured to determine, based on the information regarding the transonic flight condition, whether activation of each plasma generator will enhance operations in an optimal configuration.   
     
     
         21 . The method of  claim 20 :
 wherein the optimal configuration comprises a fuel efficiency optimizing configuration;   wherein information relating to the transonic flight condition comprises information relating to fuel efficiency;   
     
     
         22 . The method of  claim 20  further comprising:
 calculating, with the controller and using the information relating to fuel efficiency, a fuel efficiency optimizing configuration.