Calculation the Heating Parameters for Entry Space Vehicle in Multiple Entry Angles

Abstract

When the space vehicles (space shuttle, missile, and satellite) are entered into the earth’s atmosphere, there are many forces acting on it, called aerodynamic forces. The drag force is important and which so much depended upon the velocity and air density. This force rabidly reduces vehicle velocity. As result for this, the kinetic energy of the vehicle is converted into heating energy. In this paper the heating parameters by various entry angles are calculate, and the effects this angle upon these parameters are studying. The heating parameters with various velocity and altitude are calculated. The calculations of these parameters is very important through entry and reentry operation for the vehicles, and from this we can select the region altitude which the maximum heating rate is occur in it. All one knowing the entry angle affects on altitude this region and from through it we can know the suitable angle for entry. From this study we noted, on smaller entry angle 5 deg the total heat load is more decrease, also the entry velocity decrease into 37 km/sec, while the heat rate in this angle is remain on this value 1 for other angle. Therefore lower entry angle is good through entry, but these lower angles are cause increase in flight time. This feature is not useful for entry vehicle, therefore must reduce of flight time by increase for entry angle into 20 deg for it be suitable for heating, entry velocity and flight time. While on high entry angle 90 deg the entry velocity and heating may reach to very high values and become very danger on vehicle although the flight time is very few.