Standoff Airborne Dispenser Key To The Overall Design

This paper is some advanced research work on conceptual design of standoff airborne spreader according to tactical and technical requirements of a certain standoff airborne spreader. The completed work includes two aspects: one is the method study of aerodynamic estimation of aircraft with noncircular shape cross section body; the other is the design and development of computer-aided steady-state performance analysis system of turbine engines used in missiles. These two aspects are key technology need to be solved in the phase of overall project preliminary design of standoff airborne spreader.In chapter 2, a set of aerodynamic estimation methods of aircraft with noncircular shape cross section body are established based on the analysis of aerodynamic characteristic of aircraft with noncircular shape cross section body. The methods used the aerodynamic estimation method of aircraft with circular shape cross section body to calculate the aerodynamic characteristic of aircraft with noncircular shape cross section body by inducing noncircular shape cross sectionadjustment factors (including noncircular shape factor FSB , coefficient Kc of correction of the interference factor between wing and body Kc, and Newton adjustment factor Fm.). Then the mathematic expressions of calculating Fsa andKc are derived, and the computational model to calculate the apparent area ofarbitrary shape cross section is established by constructing a new basic solution: two-dimensional constant dipole distributing linear element. The examples in this chapter validate the correctness and accuracy of the methods.In chapter 3, the computational model to calculate the steady-state performance of turbine engines (including turbojet engine and turbofan engine) used in missiles is established firstly, and then the computer-aided steady-state performance analysis system of turbine engines used in missiles is designed and realized, and the functional design, program structure and operational procedure of the system are given. And finally the system is proved to be correct, convenient and practical by two examples given in this paper, and so it can be used for the steady-state performance calculation of turbine engine in the phase of overall project preliminary design.