- #Solidworks flow simulation angle of attack software
- #Solidworks flow simulation angle of attack series
Since the attitude angle of attack may reach 15° during the BM flight, the use of the approximation method will cause large deviations.įig. This makes the method labour-consuming for realtime simulation of missile and aerospace environment.īesides, the method is applied only in case of low transient disturbances and small angles of attack when the function of linear variation of aerodynamic characteristics depending on kinematic parameters is true.
#Solidworks flow simulation angle of attack series
− methods based on the use of simplified dependences of ADC on the angle of attack :Īccording to (10), using the method based on the expansion of aerodynamic coefficients into Taylor’s series requires a large amount of discrete values, including those for determining partial derivatives, which also include wellknown dependence on the rotation speed, angle of control surface deviation (if any), etc. − method based on representation of the specified dependence in the form of Taylor’s series There are some well-known methods of approximation of the dependence of aerodynamic characteristics (ADC) on the angle of attack and Mach number, including: Thus, to obtain the BT current velocity estimation error of not more than 10 m/s, the approximation meansquare error shall be less than 0.005.Īccording to equation (1), aerodynamic forces and moments affect trajectory parameters in a longer flight segment. 1, when the drag coefficient changes by 0.1, the difference in velocity at the 30th second at an altitude of about 30 km may exceed 200 m/s. 1 shows the dependence of BT velocity variation on time with the increment equal to Δt = 1, at different values of c x.Īccording to the diagram shown in Fig. Dependence (9) is the recurrence formula, where the input element – velocity V k – 1, will be substituted with velocity V k calculated at the previous step, with relevant altitude recalculation as per formula (4).įig. Thus, we have determined the dependence of the current velocity on the aerodynamic drag coefficient. Where Δt – increment, k ∈ N – discrete value of flight time, s. Taking into account (3) and (4), equation (2) has the following form: In this respect, the following assumption is taken: we suppose that during the 30-second flight in the non-powered atmospheric segment velocity V в for a short period of time Δt = 1 s and angle θ вх changes but slightly within 30 s. Where H k – 1 – initial BT altitude at a given time t, V в(k – 1) = V k – 1sin θ вх – vertical velocity at a given time t, θ вх = 15° – atmospheric entry angle. In its turn, the altitude – time dependence can be expressed as follows: Where – density at the ground level, H k – current altitude. According to, the density – altitude dependence can be represented as follows: Based on the above, the weight is assumed to be constant m = const. Let us analyse the non-powered (atmospheric) segment of the trajectory. To estimate the influence of aerodynamic coefficients on the velocity, the following relationship may be used: Where V X, V Y, V Z, R X, R Y, R Z, P X, P Y, P Z, g X, g Y, g Z – components of velocity, total aerodynamic force, thrust force and gravity acceleration, respectively, in projections on the axes of the Earth-fixed launch site coordinate system, m – ballistic missile (BM) weight.
#Solidworks flow simulation angle of attack software
The main component of the integrated aerospace environment simulation system is the software module of airspace attack weapons (ASAW) motion dynamics, intended for implementing the following system of differential equations of ballistic target (BT) motion: The integrated simulation system is widely used for theoretical studies.
This methodology implies the use of experimental and theoretical research methods. The methodology based on the principles of systematic approach and integrated goaloriented planning is the foundation for solving the problem of ASD system integration verification.
One of such methods is the experimental and theoretical method combining full-scale tests of individual system components and simulation of the whole system. Since testing with full-scale prototypes is very expensive and technically complicated, and sometimes even infeasible, alternative methods of research in this field need to be found. To provide effective performance of the aerospace defence (ASD) strategic system, its integrated equipment and systems shall be tested on a regular basis.
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