In general, according to the Russian Gost standard, the SPACE PROPULSION engine SYSTEM includes injection subSYSTEMs, a thrust chamber, a heat transfers and cooling SYSTEM, a launch SYSTEM, a feeding SYSTEM, a thrust vector control SYSTEM, and fuel and oxidizer tanks, which due to overlap and penetration The manifolds between the engine reservoirs and the fuel SYSTEM are usually designed as a pair. In the conducted investigations, in addition to knowing the elements of the circuit and how to arrange the circuit, it also leads to knowing the requirements, goals, and main requirements of the SYSTEM design. Then, based on the studies, the circuit design of the feeding SYSTEM and the selection of its elements have been done. By using simple fluid relations, the pressure drop of each of these elements is calculated and extracted by establishing the pressure energy balance of the reservoirs. After that, taking into account the remaining mass of pressurized gas in the tanks, the total required mass of pressurized gas has been calculated. Considering the cryogenic (super-cold) propellants in this project, considerations for the design of routes and tanks will be more important, and finally, after presenting pressure changes in both fuel and oxidizer routes, piping and instrumentation diagrams have been discussed. One of the main goals of this research is to design based on standards to achieve high reliability. In this article, the types of feeding SYSTEMs, ahead problems, and challenges are discussed. Finally, the two-dimensional model of this subSYSTEM will be presented based on the country's TRL level.

Designing SPACE PROPULSION SYSTEMs as one of the important subSYSTEMs of the SPACEcrafts and upper stage SPACE launch SYSTEMs needs to bypass different and complicated steps. In this article the comprehensive process of designing liquid fuel low-thrust SPACE PROPULSION SYSTEMs was illustrated. In the presented pattern, first of all according to the requirements and mission constraints, the main characteristics of the SYSTEM were determined and then other characteristics were extracted. Finally, for the evaluation of the presented pattern, a low- thrust SPACE PROPULSION SYSTEM was designed based on a special mission and the results were compared with a real model. Comparison between the designed SPACE PROPULSION SYSTEM and the real one showed an appropriate accuracy of the presented pattern.

The purpose of this paper is to present the cost estimation model for Cryogenic/Semi-Crogenic SPACE PROPULSION SYSTEMs. Therefore, the SPACE PROPULSION SYSTEM selection from fuel and oxidizer type aspect and achieving the maximum performance and minimum cost has been performed. Then, the fuel and oxidizer pair samples based on the mass – energy specifications (engine weight- specific impulse) and engine operation cycle type with respect to the mission possibility has been determined. To this end, the algorithm for implementing and using the proposed cost estimation model has been designed. In this algorithm, the proposed cost estimation model is developed based on the existing cost estimation relationship and verified by comparing the existing models. Finally, the outputs in the algorithm are cost-performance (specific impulse) graph for the seven fuels and oxidizer pairwise, engine selection based on achieving maximum specific impulse and providing the design SPACE searches for the cost and time optimization in the SPACE projects.

Due to increasing environmental pollution and cost of energy, various solutions such as manufacturing hybrid vehicles have been proposed to optimize the energy consumption of vehicles. hybrid hydraulic PROPULSION SYSTEM is used in heavy duty vehicles due to low cost maintenance and high power density compared to electric hybrid propusion SYSTEM. In this study a hydraulic hybrid PROPULSION SYSTEM with series structure and friction brake removal approach is investigated. The proposed hydraulic circuit has the ability to control pressure and flow. This feature causes the braking torque to be applied in all driving conditions by a hydraulic circuit. The pressure and flow control algorithm is explained in two ways according to the driving conditions and the accumulator pressure .In the first case, the braking torque is provided only by changing the flow and in the second case by simultaneously changing the flow and pressure .To confirm the performance of the proposed structure, by applying the desired forces to the pedal, the deceleration is simulated in AMESIM software. The control algorithm has been implemented in this software and the braking capability and the amount of energy stored during braking in different braking modes have been investigated.

This paper presents numerical calculations for podded PROPULSION SYSTEM using vortex theory and potential panel method. The method discretizes the surface boundary of the body (propeller+pod+strut) and obtained the vortex and propeller surface and potential on strut and pod. A model propeller and strut are considered for these calculations and the results of pressure distribution, flow field around the propeller and hydrodynamic characteristics of the propeller are given. The calculated hydrodynamic characteristics of the propeller are compared with the experimental data and it is shown in good agreement with them.

In this paper, a particular PROPULSION SYSTEM including, liquid rocket engine, fuel and oxidizer tank and related pressurizing SYSTEM, have been surveyed. The procedure is based on a nonlinear mathematical model which has been simulated in Matlab Simulation environment. In PROPULSION SYSTEMs, identifying SYSTEM performance is essential, because if we can accept ability describe the dynamic behavior of the SYSTEM components in nominal and transient regimes; we can reduce the associated costs during design and development. Following, results of PROPULSION SYSTEM hot test are compared with model that shows acceptable accuracy of simulator code. In addition to leading research, how to use this model to identify the causes of failure is shown. Match analysis and compatibility testing, after disassembling objective observations show considerable performance model for similar applications.

In this paper, the hydromagnetic PROPULSION SYSTEM in marine application is taken into account. If the conduction fluid channel is exposed to a magnetic field and an electric field perpendicular to the fluid flow, under the interaction of electric current and magnetic field, a force is generated to flow the fluid, which is the basis of hydromagnetic PROPULSION SYSTEMs. Hydromagnetic PROPULSION SYSTEMs have a variety of applications which the most important ones are molten metal transfer SYSTEM, small hydromagnetic pumps and marine PROPULSION SYSTEM. Therefore, in this research, a literature review is performed and 70 valid scientific references in this field are studied and presented. Various classifications of the hydromagnetic thrust SYSTEM are presented based on the installation location, type of electric field, type of fluid conducting channel, etc. The operating applications of hydromagnetic thrust SYSTEMs are presented for all types of marine and submarine cargos. This paper can be a benchmark for future researches on hydromagnetic PROPULSION SYSTEMs.

The Monopropellant Hydrazine PROPULSION SYSTEM is one of the most widely used types of single-agent PROPULSION SYSTEMs to control the position or correction of satellites in orbits. This SYSTEM consists of combustion chamber subSYSTEMs (catalyst bed, catalyst, nozzle, and cap), fuel and fuel tank, high-pressure tank, control valves, and interface pipes. In this paper, the MPHP SYSTEM (as a case study) is described in detail, and then critical risks are identified by creating FMECA tables on the case study in the design phase. Based on the proposed FMCEA flowchart, potential failure modes are identified. In the next step, decisions and corrective actions are formulated regarding the inherent failures of the SYSTEM. Finally, the necessary measures to reduce the risks will be taken according to the SYSTEM's failure modes, and the reduction of the identified risks to an acceptable level is presented. The attained results show that the catalyst decomposition chamber, catalyst bed, inlet flow control valve, and propellant management facilities units have the highest risk index values (RPN), respectively. For this purpose, corrective measures have been suggested for each of these.