Дипломная работа: Проектирование двигательной установки и элементов конструкции второй ступени баллистической ракеты

Давление в камере сгорания6 МПа

Давление на срезе сопла0,02 МПа

Геометрическая степень расширения сопла26,24

Суммарная мощность ТНА

Частота вращения турбины11600 об/мин

Частота вращения насоса горючего11600 об/мин

Частота вращения насоса окислителя11600 об/мин

Abstract

As exhaust skilled work was designed project liquid missile engine second step ballistic rocket, as well as is calculated separate elements to designs second step. The Project consists of five sections: designing LME, designing element to designs second step, technological, economic and labor guard section.

In section of the designing LME are executed following problems: is made choice main parameter designed engine, heat calculation presented in the manner of final result, calculation of the pump окислителя and gas turbine, calculation to geometries and toughness cooling tract, calculation of the cooling the engine.

The technological process of the assembly of the farm of the service load was designed In technological section of the project, containing information about the sequences conducted operation during assembly. The Designed adjustment for assembly of the welding of the farm.

The Economic section contains the calculations of the expenses on development given project: salary of the designer, amortizations of the premises, equipment, software and etc.

In section labor guard reflected main moments to safety and ecological capacities of the project. The Considered factors surrounding ambiences, influencing upon designer, as well as measures on eliminating the action bad factor. Calculation made of the artificial illumination worker place. The Considered ways of the estimation and increasing to stability of the economic systems.

The General volume of the project contains in itself: 116 sheets of the explanatory note, executed on format A4 (the plus of Exhibit), containing in itself 38 tables and 33 drawings; 10 sheets of the graphic material, comprising of itself assembly drawings of the designed engine, the general type second step, drawings of the pump and turbines, as well as graphs heat flow and sharing the temperature on length CC.

Finally, after called on calculation were received following technical features LME:

Number of the cameras of combustion 1

Time of the work 169 sec.

Pulling of the engine in emptiness 208 kN

Specific pulse in emptiness 2817 м/с

Oxygen Nitric acid

Combustible Kerosene

Сcorrelation component fuel 4,75

Length engine 1,508 m

Pressure in camera of combustion 6 MPa

Pressure on cut sniffled 0,02 MPa

Geometric degree of the expansion sniffled 26,24

Total powers

Frequency of the rotation of the turbine 11600 turn/min

Frequency rotations of the pump combustible 11600 turn/min