Combined Propulsion System Research Articles

Launching Earth radiation monitoring satellites using the combined thrust

The paper considers the problem of launching satellites into the orbits for Earth radiation monitoring using the upper stage previously inserted into a reference circular orbit and equipped with a combined propulsion system, i.e. chemical rocket engines and electric rocket propulsion system (ERPS). The combined launch scheme implies formation of the intermediate orbit using the chemical rocket engines and further successive satellites insertion into the target orbits using the electric rocket propulsion system. Calculation of the satellite group launch trajectory parameters is provided, single accompanying and two more in cluster formation, to the given elliptical orbits. The spacecraft flight is approximated at the chemical rocket engines operation phase by a pulse action using the double-pulse apsidal maneuvers; and the spacecraft flight trajectory in the ERPS phase is calculated under the condition of minimizing the flight time with the Pontryagin maximum principle. The results obtained demonstrate technical feasibility of the task of launching satellites into specified orbits using the combined thrust, as well as advantages of a combined scheme for launching a payload in order to reduce flight duration compared to using the ERPS throughout the entire flight.

Techno-economic model-based design space exploration of ‘combined’ ship propulsion systems

The architecture of a ship propulsion system, developed during early stages of the overall ship design process, has a very large impact on the overall design and performance of the ship. The design space exploration to arrive at the final ship propulsion architecture can be a rather complex process for high-performance 'combined' ship propulsion systems designed to achieve multiple, often conflicting, design objectives. This paper proposes a novel process for the process of design space exploration based on a model-based ‘Techno-economic & Environmental Risk Assessment’ (TERA) approach, executed using a hybrid ‘Multiple-Criteria Decision-Making’ (MCDM) procedure, to select a compromise solution from competing propulsion system architectures populating the design space. The process utilizes a combination of performance data generated from performance simulation of developed models, as well as comparative expert opinions-based metrics for information not available early in the ship design process for selection of a 'compromise solution'. The paper includes an illustrative example of application of the proposed process for design space exploration for a combined propulsion system architecture for a notional destroyer.

Methodology of designing a space transport system including a “DM” chemical upper stage and an electric rocket transport module

The article is devoted to the development of a methodology for designing a space transport system that has, in comparison with traditional injection scenarios, higher characteristics of the mass of the payload to be launched into high-energy orbits, including a geostationary one. The method is implemented by the systematization of design calculations and proposals for the rational design of interorbital vehicles with a combined propulsion system and the development of an algorithm for creating an electronic model of an interorbital vehicle in an automated designing PTC Creo system. The article considers algorithms for calculating the design parameters of the electric rocket transport module and ballistic parameters of the spacecraft flight to the target orbit. A method of forming conceptual design of an electric rocket transport module based on the obtained design parameters is also proposed. An electronic model of an electric rocket module was developed in a three-dimensional modeling system. The model displays the structural design of the module in accordance with the design parameters obtained and satisfies the design requirements imposed by other components of the space transport system. The proposed method makes it possible to design a space transport system that includes a DM upper stage and an electric rocket transport module designed to implement a combined payload injection scenario.

MAIN DIRECTIONS FOR THE DEVELOPMENT OF SHIP ELECTROTECHNICS AND AUTOMATION

In recent decades, the level of electrification and automation of ships has grown significantly. This is due to the increased requirements for technical, operational and technical and economic characteristics on the part of shipowners. The implementation of the requirements has become possible due to the development of related branches of science, engineering and technology: materials science, power converter technology, microprocessor electronics, and information technology. The main directions of development of ship electrical engineering and automation, namely, improvement of power generation and distribution systems, improvement of electric propulsion systems and propulsion systems, improvement of automation systems are considered in the paper. The expediency of using valve generator sets and the transition to electric power distribution on direct current is shown. Static power sources of new generation are actively developing and spreading both in industry and in maritime transport. Good control characteristics, no restrictions on the number of reverses and minimum speed, high efficiency when operating at fractional loads, high torque overload capacity on the propeller significantly expand the scope of modern AC electric propulsion systems. The desire to combine the advantages of different types of propulsion systems has stimulated the creation of combined (hybrid) propulsion systems. Combined installations incorporate a traditional thermal main engine and a propulsion electric motor. The activation of one or another engine is carried out depending on the mode of operation and the speed of the vessel. The introduction of information technologies makes it possible to automate the management and control of maintenance and repair of ship equipment. The modern development of software and hardware and algorithmic support makes it possible to create unmanned ships that can be controlled remotely and move independently (autonomously) according to predetermined algorithms, including algorithms for divergence from other ships at sea. It is concluded that the main tasks within the framework of the directions for development of ship electrical engineering and automation are increasing the energy efficiency of the process for generating electricity by introducing valve generator sets, introduction of innovative sources of electricity with high rates of efficiency and environmental friendliness, including static sources of electricity, the use of rowing electric motors with permanent magnets and inductor type, the use of combined propulsion systems with reversible electric propulsion systems, and increasing the level of automation through the introduction of information technology and artificial intelligence.

Analysis and Comparison of Ship Propulsion Systems

One of the highest cost of building the ship refers to the ship’s propulsion system. It is therefore very important to know all the types and specificities of propulsion systems for the optimal selection. This paper presents the conventional and the combined propulsion systems, where are briefly given their characteristics and specificities. Special attention is given to the combined propulsion systems, whose extensive use is still under expectation. At the end, the paper discusses the cost calculation of a marine propulsion system of selected passenger cruiser and comparison to the possible alternative system.

АНАЛИЗ ПРИМЕНЕНИЯ ГАЗОВЫХ РАКЕТНЫХ ДВИГАТЕЛЕЙ В ДВИГАТЕЛЬНЫХ УСТАНОВКАХ КОСМИЧЕСКИХ АППАРАТОВ

In order to determine directions for improving the energy characteristics of spacecraft propulsion systems due to the combined of cold gas and electric thrusters, the authors analyzed the design schemes and energy characteristics of cold gas thruster used on spacecraft. Propellant sharing in a combined propulsion system, as well as a single engine design combining cold gas and electric thrusters, is a promising technology. At the same time, it is emphasized that at the current time the main tasks in the development of combined propulsion systems are to ensure the compatibility of the operation of an electric rocket engine with the propulsion of a cold gas thruster

ОПТИМАЛЬНЕ КЕРУВАННЯ СУДНОВИМИ КОМБІНОВАНИМИ ПРОПУЛЬСИВНИМИ КОМПЛЕКСАМИ

Стаття присвячена розв’язанню задачі оптимального керування судновими комбінованими пропульсивними комплексами з диференційними привод-генераторними агрегатами з метою підвищення їх ефективності. У роботі виконано аналіз структури суднового пропульсивного комплекса як гідромеханічної системи, що включає корпус судна і пропульсивну установку, в якій енергія робочого тіла перетворюється в упор, що приводить в рух корпус судна, обґрунтовано перспективність впровадження комбінованих пропульсивних комплексів, в яких застосовуються кілька різнотипних двигунів, що працюють на один або кілька рушіїв. Розглянуто математичну модель процесу керування судновим комбінованим пропульсивним комплексом, що дозволяє проводити аналіз роботи валогенераторної установки з диференційним привод-генераторним агрегатом, як при ходовому, так і при аварійному режимі функціонування. Формалізовано завдання керування судновими комбінованими пропульсивними комплексами на основі критерія узагальненої оцінки якості їх функціонування, що враховує відхилення ходового навантаження пропульсивного комплексу при обмеженнях щодо відхилення потужності бортової мережі від бажаної та сформульовано задачу оптимального керування судновими комбінованими пропульсивними комплексами за мінімумом відхилень механічної потужності при обмеженнях щодо забезпечення живлення споживачів. Запропоновано новий метод оптимального керування частотним перетворювачем генератора опори, що забезпечує мінімізацію визначеного критерію із дотриманням відповідних обмежень. Алгоритм оптимального керування комбінованого пропульсивного комплекса включає: етапи аналізу значень заданої та діючої механічної потужності на гвинті судна; визначення електричної потужності, що виробляється допоміжною енергетичною установкою судна та споживаної у відповідному режимі; обчислення керування перетворювачем частоти, що забезпечує за рахунок підтримання відповідної потужності генератора опори мінімум відхилення потужності на гвинті при забезпеченні необхідного енергетичного балансу електромережі судна. Враховуючи випадковий характер навантажень, як з боку електричної енергосистеми, так і безпосередньо рухової установки, що ускладнює реалізацію представленого алгоритму оптимального управління в реальному часі, обґрунтовано доцільність застосування нечітких алгоритмів для підвищення ефективності процесів керування. Отримані результати можуть бути використані при побудові високоефективних систем керування судновими комбінованими пропульсивними комплексами для покращення якісних показників електричної енергії в судновій енергетичній системі та забезпечення працездатність суднової енергосистеми при аварійних ситуаціях. Ключові слова: математична модель, судновий пропульсивний комплекс, диференціальний привод, валогенератор, оптимальне керування, регулятор.

MARSZUG—A Space Train for Regular Delivery of Astronauts onto Mars

A project of the space train MARSZUG intended for regular delivery of astronauts to Mars is considered. In the first stage of the flight, the astronauts with the help of the carrier rocket equipped with a chemical rocket engine are delivered to the international space station (ISS). To deliver astronauts from Earth’s orbit to Mars orbit, a space train design consisting of two rockets, which have superconductive magnetoplasma electric engine MARS, has been developed. For the first time, a combined propulsion system MARS-M has been developed for the train movement, allowing carrying out the pitching, yaw and rotation of the rocket. This greatly simplifies the rocket control system and increases its reliability. The energy source of the electric engines is a sliding solar panel made of gallium arsenide. Working substance to create reactive thrust of electrorocket engines—hydrogen is stored in a liquid state in the cryogenic tank located along the longitudinal axis of the rocket. In the nasal part of the front electric rocket, a shaft rotating in a superconductive bearing is located. The shaft has a cylindrical nozzle, on which with the help of docking units two takeoff-landing capsules TLC-1 and TLC-2 are installed with which help landing and takeoff from the surface of Mars is carried out. This allows astronauts to constantly stay during the flight under the influence of gravity. To refuel the space train with liquid hydrogen in the orbit of Mars, the design of a space refueler with a chemical rocket engine is developed. The developed space train is able to regularly deliver astronauts to the surface near the northern pole of Mars.

Rational acceleration control of an all-wheel drive vehicle

Problem. The improvement of ability rating of vehicles is a topical task which provides the promptness of transportation, improves the performance efficiency of vehicles by means of increasing the vehicle average speed. High dynamic characteristics are provided by mounting the powerful power units and by using the combined propulsion systems and powering cars recently. Using cars with driving wheels’ electric drive helps not only decrease energy consumption, but also increases car stability by regulating distribution of traction moments between the front and rear axles. Goal. The goal is to increase the course-keeping ability and power efficiency during the acceleration of all-wheel drive electric cars. Methodology. The provision of stability of vehicle movement is reached by the redistribution of total tangential reaction of a vehicle wheels. The power consumption of a power unit is determined with the help of rational law of the acceleration ramp changing during the acceleration that provides the most possible increase of line speed. Results. The relations allow to create the algorithm of control of vehicle front and rear wheels’ electric motors during the acceleration with the minimum of additional engine power consumption while accelerating with the maximum intensity that can be implemented both for electric cars and for cars with combined propulsion systems. Originality. The laws of driveline engine tractive effort torque control during the acceleration are obtained at the limit of a clutch fade of drive wheels with the road that determines the performance of maximum acceleration by cars. Practical value. Increasing of vehicle energy efficiency and providing of safety of traffic.Key words: electric car; stability of movement; power consumption; tractive effort torque.

Development of a robust solver to model the flow inside the engines for high-speed propulsion

The demand for discovering new commercial routes as well as the possibility to shortening civilian long-haul flights boosted the interest of civil hypersonic vehicle designs. Among all the multiple projects started by the various nations, the European community funded project STRATOFLY aims at refining the baseline LAPCAT II-MR2.4 design for further improvements. The new aircraft would enable a flight shorter that 3 hours from Brussels to Sydney, carrying 300-passengers above the already crowed atmosphere. The wide Mach range operability, up to Mach 8, demands the use of multiple engines, leading to a highly integrated propulsion system. The current study is focused on the development of new CFD platform to estimate the performance of the combined propulsion system during the supersonic to hypersonic transition. In order to control the complex flow physics, highfidelity CFD simulations remain the fundamental tools for the preliminary investigations. On the current framework, an advanced robust compressible solver has been develop d in order to handle the different flow regimes. The new tool solves Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations by employing cell-centered Finite Volume Method constructed on openFoam toolbox. Two innovative high-order discretization schemes, with different abilities, based on approximated Riemann solvers were developed for capturing the flow physics within high-speed propulsion systems. Advanced time discretization has been taken into account to increase the temporal accuracy. At the end, the whole implementation has been validated in multiple test cases, ranging from incompressible to hypersonic regimes, confirming its excellent stability, robustness and accuracy.

Sailing and Sailing Rigs in the Ancient Mediterranean: implications of continuity, variation and change in propulsion technology

Ships and boats form the foundations of the maritime connectivity that is a central part of our understanding of the ancient Mediterranean. While the general chronological sequence of sail and sailing-rig development is well established, the implications are less-well discussed. This article sets out how sails and sailing rigs developed in antiquity, with emphasis on the Greco-Roman world. Subsequently, instances of innovation are defined. Why specific pieces of maritime technology were, or were not, widely adopted is considered. Long-term technological continuity can be comprehended, and a shared maritime culture of sailing in the ancient Mediterranean is suggested.

Choosing an efficient option of the combined propulsion system and flight profile of the INTERHELIO-PROBE spacecraft

The paper is devoted to the design features of the prospective Russian INTERHELIO-PROBE spacecraft using, depending on the configuration version, an electric or chemical propulsion system as a sustainer. The scientific goal of the mission is the study of near-solar space from close distances (60–70 solar radii). The paper presents the description of several versions of the spacecraft options depending on the installed propulsion system, as well as the main characteristics of the flight profile depending on the engine type.

Анализ целесообразности применения водородного топлива для двигателей ближне- и среднемагистральных самолетов

An analysis of circuit design for a perspective propulsion system for short and medium range aircrafts has been carried
 out. It has been shown that use of traditional schemes engines working at aviation kerosene TC-1 will not allow match the
 ICAO ecological requirements for an aircraft of 2025-2035. Transition to hydrogen or liquefied natural gas allows match
 ICAO requirements for CO2 emissions. However it will lead to an essential transportation value addition (due to hydrogen
 and liquefied natural gas production and storage infrastructure). Application of the combined propulsion systems using
 both kerosene and cryogenic fuel will allow increase fuel efficiency and reduce CO2 emission by 16% for hydrogen and by
 2.5–4.5% for methane. In such a case partial transition to hydrogen fuel will allow match ICAO requirements at the current
 freight charge.

H2O2-케로신 로켓을 초기 가속장치로 갖는 새로운 램젯 추진기관

본 연구에서는 RBCC (Rocket Based Combined Cycle)엔진이나 기존 램제트 추진기관의 초기 추력 제공에 과산화수소 가스발생기를 이용하는 새로운 추진시스템을 제안하였고, 기초 연구 수행으로서 촉매 분해된 과산화수소 제트에 케로신을 분사하여 자연발화 및 연소 특성을 연구하였다. 과산화수소는 촉매 베드를 통하여 분해된 후 축소노즐을 통해 연소실로 분사됐으며 이 제트에 인젝터를 통하여 수직으로 케로신을 액상으로 분무하였다. 연소실내에서의 온도와 압력을 측정하여 점화를 확인하고 자연발화 특성을 조사하였다. 400°C의 연소실 온도와 연료와 산화제 혼합비 0.6이상에서 자연발화와 안정적인 연소가 가능하였다. 이 결과를 통하여 램제트의 새로운 초기 가속장치의 가능성을 확인할 수 있었다. New concept ramjet propulsion system with liquid bipropellant rocket using "Green Propellant" hydrogen peroxide for launch stage is proposed. In this novel concept, hydrogen peroxide gas generator produces hot oxygen at launch stage and kerosene injects to this jet in combustor. For basic study of this new concept ramjet system, investigation of auto-ignition characteristics and combustion of decomposed hydrogen peroxide and kerosene was conducted. In various test cases, auto-ignition and stable combustion was verified. The combustion temperature of 400°C and Fuel/Oxidizer mixture ratio of 0.6 were the limit of auto ignition. Through the experiment results, the possibility of novel concept combined propulsion system using hydrogen peroxide gas generator is ascertained.

Transport capabilities of a spacecraft with chemical and electric propulsion at insertion of satellites into geostationary orbit with use of Moon's swingby

The possibility of using chemical and electric propulsion and Moon's swingby for insertion of spacecraft into the geostationary orbit (GEO) is analyzed in the present research. Using Moon's swingby for transfer of a spacecraft with a combined propulsion system is the original idea of the present analysis. The purpose of this research is to estimate transport capabilities and advantages of application of a combination of the chemical and electric engines at the injection into GEO with use of Moon's swingby. It is shown that the use of Moon's swingby can increase a spacecraft mass in GEO at a small duration of insertion.

Steady Performance Measurements of a Turbofan Engine With Inlet Distortions Containing Co- and Counterrotating Swirl From an Intake Diffuser for Hypersonic Flight

The influence of distorted inlet flow on the steady and unsteady performance of a turbofan engine, which is a component of an air-breathing combined propulsion system for a hypersonic transport aircraft, is reported in this paper. The performance and stability of this propulsion system depend on the behavior of the turbofan engine. The complex shape of the intake duct causes inhomogeneous flow at the engine inlet plane, where total pressure and swirl distortions are present. The S-bend intakes are installed axisymmetrically left and right into the hypersonic aircraft, generating axisymmetric mirror-inverted flow patterns. Since all turbo engines of the propulsion system have the same direction of rotation, one distortion corresponds to a corotating swirl at the low pressure compressor (LPC) inlet while the mirror-inverted image counterpart represents a counterrotating swirl. Therefore the influence of the distortions on the performance and stability of the ‘CO’ and ‘COUNTER’ rotating turbo engine are different. The distortions were generated separately by an appropriate simulator at the inlet plane of a LARZAC 04 engine. The results of low-frequency measurements at different engine planes yield the relative variations of thrust and specific fuel consumption and hence the steady engine performance. High-frequency measurements were used to investigate the different influence of CO and COUNTER inlet distortions on the development of LPC instabilities.

An advanced arrangement of the combined propulsion, levitation and guidance system of superconducting Maglev

The PLG (combined propulsion, levitation and guidance) method was proposed for a more favorable Maglev ground coil system, combining the functions of propulsion, levitation, and guidance of the vehicle into one coil. Research and development is currently being conducted on this method. In this paper, the characteristics of a newly-structured system for the PLG method is examined. The discussed characteristics include propulsion, levitation-guidance, vehicle dynamics in the cases of problems with the superconducting magnets, and the magnetic field on board the vehicle.

A novel combined lift and propulsion system for a steel plate conveyance by electromagnets

A novel lift and propulsion system using alternating-current electromagnets is proposed. The proposed system can simplify the configuration of a non-contacting conveyance system for a steel plate by magnetic force. Both finite element analysis and experiments were carried out. After investigating the basic characteristics of the proposed electromagnetic linear actuator, magnetic levitation experiments with four controlled electromagnets were performed and stable levitation was realized though about 65% of the total mass of the steel plate was supported by uncontrolled alternating-current electromagnets. The results indicate that the proposed system can produce not only the strong levitation force but also the propulsion force on a steel plate.

5643522 Method and system for curing fiber reinforced composite structures

Combined propulsion systems for hypersonic application have become new challenges for industrial and research organizations. In France, SNECMA and SEP, which have just joined together for a common effort on hypersonics within Hyperspace, and ONERA have been involved, under CNES (French space agency) contracts, in the assessment of new propulsion concepts for reusable winged launchers (SSTO or TSTO). As potential solutions for the airbreathing propulsion, some turbojet-type engines are presented: •—the twin spool turbojet or turbofan with reheat•—the turbojet with reheat•—the twin-duct turbojet ramjet•—the precooled turbojet with reheat.All these engines have been sized for a flight Mach number under seven with a cryogenic fuel (liquid hydrogen). Mainly due to total temperature and pressure encountered along the trajectory, the systems will have to withstand severe physical constraints. Coupled with performance and size requirements, like specific thrust and maximum air capture area, these operating conditions have been taken into account in order to select each engine cycle and technical arrangement. Performance and mass criteria make it possible to compare these systems and to emphasize their distinctive features among the propulsion concepts envisioned for the future reusable winged launchers (including airbreathing combined engines under study in France). The first step of the final selection, leading to the best adaptation between the engine and the vehicle, will then be tackled. This will be particularly enhanced by the analysis of potential advantages or technical difficulties, like thrust-to-weight ratio or needs of variable geometry and heat exchangers. The twin-duct turbojet ramjet, for example, is probably one of the best candidates for the first stages of propulsion of a reusable winged launcher.

Test run of combined propulsion, levitation and guidance system at Miyazaki test track

AbstractIn commercializing the superconducting Maglev system it is important to reduce the cost, especially that of ground coils constructed along the whole length of the guideway. For this purpose we have examined the combined propulsion, levitation and guidance system (PLG system) which can generate levitation, guidance and propulsion forces by the same coil. This paper describes the test run of the PLG system, whose ground coils (PLG coil) are constructed in one part of the Miyazaki test track. In designing the PLG coil, we make clear the magnitudes of the force acting both under normal and unusual conditions because the electromagnetic force, which levitates, guides, and propels the vehicle, directly acts on the magnet winding of the PLG coil. In the experiment, we examine both the performance of the vehicle and the force of a PLG coil. The measurement of the force at the PLG coil gives not only propulsion force and levitation force directly, but also guidance stiffness by sifting the measured coil. Good correlation recognized between the calculation and the experiment in the propulsion force, levitation force, and guidance stiffness proves that the required characteristics can be expected from the PLG system even under combination of propulsion, levitation and guidance.