Парирование нештатных ситуаций при пусках исследовательских баллистических ракет с созданием резервных условий входа объекта испытаний в атмосферу

Abstract

The article is devoted to solving the problem of determining and implementing backup conditions for the research ballistic missiles entry with the test objects in the inflight emergency situations. A test object is understood as a descent vehicle entering the atmosphere and moving at the speed close to the first cosmic velocity. In emergency situations during launch and on the active trajectory leg, backup entry conditions are making it possible to carry out the guaranteed flight testing, albeit with less efficiency, but with exception of the launch emergency completion and complete failure in fulfilling the flight test tasks. Detailed study of this problem is quite suitable for practical implementation and goes far beyond the scope of this work, since it requires design studies, including aerodynamic, dynamic, thermal and strength calculations, as well as the development of additional onboard and prelaunch algorithms. This paper notes only certain main features in decision making to terminate or continue the flight after the emergency situations for а research ballistic missile with liquid rocket engines and solid propellant rocket engines. Mathematical apparatus of the external ballistic design is used to solve the problem.