Systems and methods for monitoring impact on electric aircraft

Abstract

A system for monitoring impact on an electric aircraft is presented. The system includes a sensor communicatively connected to a flight component, wherein the sensor is configured to detect a measured force datum and generate an impact datum as a function of the measured force datum. The system further includes a computing device configured to simulate a landing performance model output as a function of the impact datum, generate a landing performance datum as a function of a comparison between the landing performance model output, determine an alert datum as a function of the landing performance datum, and display the landing performance datum on a user device.

1 . A system for monitoring impact on an electric aircraft, the system comprising:
 at least a sensor communicatively connected to a flight component, the at least a sensor comprising at least a strain gauge, wherein the at least a sensor is configured to:
 detect a strain parameter of the flight component; 
 detect a measured force datum; and 
 generate an impact datum as a function of the measured force datum; and 
   a computing device, the computing device configured to:
 determine an impact threshold for the flight, wherein the impact threshold includes a tunable threshold parameter; 
 simulate a landing performance model output as a function of the impact datum and the impact threshold, wherein the landing performance model is generated as a function of an impact machine learning model, and wherein the impact machine learning model is trained by utilizing impact training set; 
 generate a landing performance datum as a function of the landing performance model output; 
 determine an alert datum as a function of the landing performance datum, the alert datum describing a magnitude of an instance of a potentially dangerous event; and 
 display the landing performance datum and a performance of the flight component as a function of the strain parameter on a user device. 
   
     
     
         2 . The system of  claim 1 , wherein the electric aircraft comprises an electric vertical take-off and landing aircraft. 
     
     
         3 . The system of  claim 1 , wherein the flight component comprises a landing gear. 
     
     
         4 . (canceled) 
     
     
         5 . The system of  claim 1 , wherein the computing device is further configured to:
 detect a hazardous instance as a function of the landing performance datum; and   alert a user, by the user device, of the hazardous instance.   
     
     
         6 . The system of  claim 5 , wherein the hazardous instance is determined as a function of the impact threshold. 
     
     
         7 . The system of  claim 5 , wherein the computing device is configured to initiate an emergency landing as a function of the alert. 
     
     
         8 . The system of  claim 1 , wherein the computing device is further configured to record the landing performance datum into the impact database. 
     
     
         9 . The system of  claim 1 , wherein the landing performance model output is simulated as a function of a flight simulator. 
     
     
         10 . The system of  claim 1 , wherein the computing device is further configured to transmit the landing performance datum to a remote device. 
     
     
         11 . A method for monitoring impact on an electric aircraft, the method comprising:
 detecting, by a sensor communicatively connected to a flight component, a measured force datum and a strain parameter of the flight component;   generating an impact datum as a function of the measured force datum;   determining, by the computing device, an impact threshold for the flight component, wherein the impact threshold includes a tunable threshold parameter;   simulating, by a computing device, a landing performance model output as a function of the impact datum and the impact threshold, wherein the landing performance model is generated as a function of an impact machine learning model, and wherein the impact machine learning model is trained by utilizing impact training set;   generating a landing performance datum as a function of a comparison between the landing performance model output of the electric aircraft and a plurality of landing performance model outputs from an impact database;   determining an alert datum as a function of the landing performance datum, the alert datum describing a magnitude of an instance of a potentially dangerous event; and   displaying the landing performance datum and a performance of the flight component as a function of the strain parameter on a user device.   
     
     
         12 . The method of  claim 11 , wherein the electric aircraft comprises an electric vertical take-off and landing aircraft. 
     
     
         13 . The method of  claim 11 , wherein the flight component comprises a landing gear. 
     
     
         14 . (canceled) 
     
     
         15 . The method of  claim 11 , wherein the method further comprises:
 detecting a hazardous instance as a function of the landing performance datum; and   alerting, by the user device, a user as a function of the hazardous instance.   
     
     
         16 . The method of  claim 15 , wherein method further comprises determining the hazardous instance as a function of the impact threshold. 
     
     
         17 . The method of  claim 15 , wherein the method further comprises initiating an emergency landing as a function of the alert in the even the electric aircraft is in the air. 
     
     
         18 . The method of  claim 11 , wherein the method further comprises recording the landing performance datum into the impact database. 
     
     
         19 . The method of  claim 11 , wherein the method further comprises simulating the landing performance model output as a function of a flight simulator. 
     
     
         20 . The method of  claim 11 , the method further comprises transmitting the landing performance datum to a remote device. 
     
     
         21 . The system of  claim 5 , wherein computing device is further configured to detect a hazardous instance as a function of the straining parameter. 
     
     
         22 . The method of  claim 15 , wherein method further comprises determining the hazardous instance as a function of the straining parameter.