Various types of missile and aerospace systems can successfully operate only with automatic control and stabilization systems (ACS). The characteristics of FV either rigid or as elasticbody in the air flow are critical for ACS correct operation while choosing its structure and parameter settings. Discrepancies and counting errors in this regard can affect flight missions and even cause accidents that frequently occurred at the early stages of aircraft development.
FV complete dynamic model includes rigid FV and elastic FV. Flight motion dynamics of elastic FV is described by the corresponding mathematical models — perturbation equations [1, 2]. Such models developed with certain assumptions and used at NPOM for computer statistical simulation of elastic FV motion in flow are also called elastic dynamic design(EDD) of winged FV.
EDD equations are generated based on specific design models — elastic & mass models  and models of aerodynamic influence on FV . Great efforts are taken at NPOM to define, confirm and amend FV mass, rigid, elastic, dynamic and aerodynamic characteristics by calculations and experiments at all design stages in order to avoid significant counting errors during FV designing.
Due to importance of tasks solved based on EDD, a great scope of calculations and trials are conducted in the process of design to confirm EDD and correct it if required. EDD equations and calculation models are added during sketch design. It is now possible to amend EDD calculation models according to design documentation at the stage of detailed design and to correct it according to stiffness and modal tests at the stage of stand testing. EDD calculation models can be used to analyze emergency situations at the stage of flight trials.
This paper presents the main details of winged FV EDD generation and amendment. All forces acting on elastic FV in flow are taken into account while generating EDD motion equation. These are the elastic and inertial forces acting both on FV as a system with the distributed parameters and its control systems; structural damping and friction in fin control circuit; aerodynamic forces acting on FV and its control systems as well as all types of the external factors acting on FV in flight. The typical form of EDD equations is also given.
Typical EDD equations are given. It is explained how to calculate parameters of FV as a rigid body motion tones, i. e. “zero” tones. Ratios bringing the initial equation system of elastic FV motion to its accepted form (main normal coordinates) are presented. Matrix structure of EDD equation system is presented. Coordinate transformation ratios of FV motion are presented as to coordinates determined by sensitive elements of ACS.
Methods to calculate and amend the parameters of elastic FV EDD in flow are given:
These methods to define and amend parameters of elastic FV in flow are required for statistical computer simulation of FV motion and to improve the reliability of flight missions in the end.