Ramjet Application Possibilities for Increasing Fire Range of the Multiple Launch Rocket Systems Ammunition

• Main Authors: V. N. Zubov, P. F. Dzhevanshirov
• Format: Article
• Language: Russian
• Published: MGTU im. N.È. Baumana 2016-06-01
• Series: Aèrokosmičeskij Naučnyj Žurnal
• Subjects: multiple launch rocket system; satellite navigation system; ramjet; air intake; solid-fuel rocket motor
• Online Access: https://aerospace.elpub.ru/jour/article/view/18

The article considers a possibility to increase a flying range of the perspective rockets equipped with the control unit with aerodynamic controllers for the multiple launch rocket systems “Smerch”.To increase a flying range and reduce a starting mass of the rocket, the paper studies a possibility to replace the single-mode rocket engine used in the solid-fuel rocket motor for the direct-flow propulsion jet engine (DFPJE) with not head sector air intakes. The DFPJE is implemented according to the classical scheme with a fuel charged in the combustion chamber. A separated solid propellant starting accelerator provides the rocket acceleration to reach a speed necessary for the DFPJE to run.When designing the DFPJE a proper choice of not head air intake parameters is one of the most difficult points. For this purpose a COSMOS Flow Simulation software package and analytical dependences were used to define the following: a boundary layer thickness where an air intake is set, maximum permissible and appropriate angles of attack and deviation angles of controllers at the section where the DFPJE works, and some other parameters as well.Calculation of DFPJE characteristics consisted in determining parameters of an air-gas path of the propulsion system, geometrical sizes of the pipeline flow area, sizes of a fuel charge, and dependence of the propulsion system impulse on the flight height and speed. Calculations were performed both in thermodynamic statement of problem and in using software package of COSMOS Flow Simulation.As a result of calculations and design engineering activities the air intake profile is created and mass-dimensional characteristics of DFPJE are defined. Besides, calculations of the starting solid fuel accelerator were carried out. Further design allowed us to create the rocket shape, estimate its mass-dimensional characteristics, and perform ballistic calculations, which proved that achieving a range of 120 km for the rocket is possible.Thus, with restrictions imposed by the control unit, application of DFPJE allows us to increase a flying range of the rocket more than by 30% in comparison with the existing domestic samples.