Study On Safety Assessment Of Aircraft Encountering Vortex Based On Surfing Aircraft Vortices For Energy

In Reduced Vertical Separation Minimum(RVSM)has been widely implemented,the A380 and B747 heavy machine running,Re-categorization(RECAT)steadily promoting sustained growth,traffic flow,the airspace is more and more nervous and air traffic controller workload increasing against the background of civil aviation,aircraft strayed into front wing tip vortex is always difficult to completely avoid accident.Therefore,how to make full use of the existing airspace while ensuring the safety of aircraft after encountering wingtip vortex has become a hot topic in the research of civil aviation system.This paper first introduces the current research status of Surfing Aircraft Vortices for Energy(SAVE)and the safety control of the rear aircraft after encountering the wingtip vortex at home and abroad,and then explains the definition of SAVE.According to the wake research program of the German Aerospace Center,the development of wingtip vortexes is classified and the characteristics of the range of wingtip vortexes suitable for SAVE are explained.The aerodynamics principle,key technology and technical roadmap of SAVE are analyzed,and the development and application prospect of SAVE in civil aviation are introducedThen,the relevant parameter model of the aircraft wing tip vortex and the induced parameter model of the leading aircraft wing tip vortex to the rear aircraft are established.On the basis of these models,the minimum acceptable speed combined with the aircraft’s maneuverability characteristic parameters and safety margin was proposed as the limit of the slope Angle in the process of scaling out after enrolling the wingtip vortices,that is,the maximum acceptable slope Angle that the aircraft itself can bear.Whether the actual rolling slope Angle after enrolling the wingtip vortices is less than or equal to the maximum acceptable slope Angle was used as an evaluation method to determine whether the rear aircraft is safe or not.The induced velocities of an aircraft encountering a wing tip vortex at different locations from the center of the wing tip vortex core are simulated,which indicated that the appropriate vertical and lateral positions should be selected during the SAVE process.Quality,speed and its damping moment coefficient to the aircraft and the safety coefficient and other factors on the maximum acceptable slope angles are simulated,the influence of the identified the medium and heavy machine to SAVE safe distance,and the use of the simulation shows that the pilot will use safety assessment method can adjust the wingtip vortex encounter success after the aircraft attitude,make it can be SAVE successfully.Finally,the induced velocities of the aircraft encountered with the wingtip vortex at different locations from the center of the wingtip vortex core are simulated by using the proposed safety assessment method.Finally,the fuel efficiency of formation flight is calculated and analyzed by using the safety assessment method and the SAVE principle,which proves the effectiveness and practicability of this method.