Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

Abstract

This paper presents an aerodynamic study for a target unmanned air vehicle with controlled canard, at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The results of semi-empirical method (DATCOM), computational fluid dynamics (CFD) were compared with wind tunnel tests to evaluate perdition accuracy. Here DATCOM shows big discrepancy in pitching-moment coefficient; the CFD estimation of static aerodynamic force and moment agree well with wind tunnel data. An analysis was focused on the longitudinal data for complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a thick canard (NACA0012) and the final improved configuration with a thin canard (NACA0007) were reviewed. It is proved that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated.

A CFD Study of the Aerodynamic Characteristics of Twardowsky and FOK Rockets

“…the most important aspect of aerodynamic analysis is the determination of aerodynamic coefficients of forces and moments that allow an object's behaviour to be investigated using appropriate mathematical models. Determination of coefficients is usually performed using either wind tunnel measurements [1][2][3][4][5][6][7][8][9], semiempirical methods (such as those found in DAtCoM) [1,7,10,11,12] or CFD (Computational Fluid Dynamics) simulations ; results from the aforementioned methods are often compared for validation.…”

“…CFD has been used to approach many problems related to the aerodynamics of rockets. research topics have included estimating aerodynamic loads related to performance [1,4,5,7,10,12,[15][16][17][18][19][20][21], longitudinal stability [1,5,10,12,13,15,17,19,27] and roll control [3,6,11,14,15], but also more general themes like aeroelasticity [5,18,20] and the influence of various design elements, including nose cone geometries [16], grid fins [2], curved fins [7], spinning tail configurations [3,14] and canards [1,3,5,10,11,13,15,18,21]. some studies have explored the appropriateness of various CFD methods with regard to rocket aerodynamics [4,8,20,…”

Investigations of Lift and Drag Performances on Neo-Ptero Micro UAV Models

“…A micro unmanned aerial vehicle (micro-UAV) is a small unmanned aircraft capable of being fully autonomous or controlled on the ground by an operator [1]. The wings of a micro-UAV are classified into two types, namely fixed-wing and rotary-wing [2]. Given its wider coverage area and payload compatibility, a fixed-wing micro-UAV is more common than the rotary-wing type [1].…”

“…Ltd., as shown in Figure 1 [3]. This developed Neo-Ptero micro-UAV, known as Mark 1 Neo-Ptero, has adopted a symmetrical NACA0012 airfoil type for the tailless wing configuration [2]. The tailless micro-UAV prototype has been conceived and developed based on the CNC foam cutter machine.…”

Aerodynamic performance improvement of a canard control missile

“…As changing the aspect ratio from 2 to 10 (at a constant taper ratio and sweep angle) shifts the center of pressure location forward by over 1.5, body diameters in the inline configuration but decreases lift-to-drag ratio and range by 25 per cent approximately. Xie et al (2009) investigated the effect of canard and tail airfoil thickness on lift, drag and roll coefficient numerically and show that stability and control characteristic depend on canard vortex behavior and then the thickness of the canard in transonic speed regime. Cristina et al validated numerically the effect of the symmetric and asymmetric deflection angle of canard on aerodynamic characteristic.…”