Проектный анализ аэродинамических схем спускаемых аппаратов капсульной формы численным методом по ньютонианской теории обтекания

The article objective is to review the basic design parameters of space capsule (SC) to select a rational shape at the early stages of design. The choice is based on the design parameters such as a volume filling factor (volumetric efficiency of shape), aerodynamic coefficients, margin of stability, and centering characteristics. The aerodynamic coefficients are calculated by a numerical method based on approximate Newton's theory. A proposed engineering technique uses this theory to calculate aerodynamic characteristics of the capsule shapes. The gist of the technique is in using a developed programme to generate capsule shapes and provide numerical calculation of aerodynamic characteristics. The accuracy of the calculation, performed according to proposed technique, tends to the results obtained by analytical integral dependencies according to the Newtonian technique. When considering the stability of the capsule shapes the paper gives a diagram of the aerodynamic forces acting on the SC in the descent phase, and using the aerodynamically-shaped SC "Soyuz" as an example analyses a dangerous moment of flow at adverse angles of attack. After determining a design center-of-mass position to meet the stability requirements it is necessary at the early stage, before starting the SC layout work, to evaluate the complexity of bringing the center-of-mass to the specified point. In this regard have been considered such design parameters of the shape as a volume-centering and surface-centering coefficients. Next, using the above engineering technique are calculated aerodynamic characteristics of capsule shapes similar to the well-known SC "Soyuz", "Zarya 2" and the command module "Apollo". All calculated design parameters are summarized in the table. Currently, among the works cited in foreign publications concerning the contours of winged configuration of the type "Space Shuttle" some papers are close to the proposed technique. Application of the proposed engineering technique allows a multi-fold increasing rate of the capsule shape analysis at an early designing stage. Reviewed design parameters can be further considered as the optimality criteria when choosing the SC shape, and the engineering technique can be further extended to a full-fledged programme on the numerical selection of the optimal aerodynamic solutions with continuously transferred results for engineering development of the SC.