Spacecraft Power Supply System Research Articles

Solar-hydrogen power supply system and multichannel median signal selector for spacecraft miniaturization

Solar-hydrogen energy systems for spacecraft reliably provide energy for carrying out various kinds of unscheduled work on board and for eliminating emergency situations. Surplus energy is constantly accumulated on board in the form of the chemical energy of cryogenic hydrogen.The solar-hydrogen spacecraft power supply system is based on the principle of partial conversion of excess energy generated on board into gaseous and cryogenic hydrogen.The efficiency of converting sunlight into hydrogen is 14%. Solar-hydrogen energy systems are also called rechargeable hydrogen cells. They consist of solar panels that generate electricity, water tanks and a membrane that separates hydrogen and oxygen. The power supply system implements three modes in its operation. Mode A - the planned amount of electrical energy generated by solar cells is consumed to meet the needs of the spacecraft in the normal mode. Mode B - from the excess electricity in excess of the energy consumption on board, the solar panels generate electricity, with the help of which water is electrolyzed. The resulting hydrogen is stored in special tanks and can be used during the peak period of energy consumption. Mode C - part of the hydrogen can be liquefied by the onboard cryogenerator and it can be used to generate electricity in fuel cells in super-peak power consumption situations: accidents, repairs, experiments that require a lot of energy. The efficiency of converting sunlight into cryogenic hydrogen is 5%.The article considers a new version of the median signal selection element, which provides the possibility of practically unlimited scaling of the number of input signals without loss of performance, as well as the ability to monitor malfunctions or failures in the operation of the selection element itself.The experiments have shown that the implementation of a selection element for 7 inputs takes no more than 432 logical cells on the Altera Cyclone IV EP4CE115F29C7 FPGA, which is much less than the amount occupied by the analogs discussed in the article. In this case, the delay in calculating the median signal does not exceed one FPGA cycle.

Comparative analysis of methods for regulating the frequency characteristics of simulators of electrical characteristics of spacecraft power supply systems

Comparative analysis of methods for regulating the frequency characteristics of simulators of electrical characteristics of spacecraft power supply systems

Prospects for the development of charger-discharge devices of spacecraft power supply systems

Power supply system (PSS) is designed to ensure uninterrupted autonomous power supply of on-board equipment in all modes and at all stages during the active life of spacecraft. Lots of PSS makes up a significant proportion of the mass spacecraft and improvement of specific energy characteristics PSS this leads to a synergistic effect when the mass and energy consumption resources available for the payload are simultaneously increased, which increases efficiency of spacecraft generally. The article considers the evolution of structural and circuit solutions for PSS spacecraft, its energy-converting equipment and the effect of these changes on energy-mass characteristics PSS. It is shown that a significant effect on energy and mass characteristics PSS provide structural and circuit design solutions for charger and discharge devices of energy-converting equipment and the choice of voltage value accumulator batteries (AB). The development of the element base, the creation of programmable digital devices capable of functioning under the influence of space factors and the emergence of new circuit design and management solutions for pulse converters that have occurred in the last decade opens up new opportunities for improvement of the PSS of spacecraft. In the article as a charger and discharge device PSS reviewed pulse voltage converter (PVC) with a new modulation strategy, with the ability to reverse the flow of energy and the ability to work in a step-up mode with high efficiency. Its application as a single charger-discharge device (CDD) allows for a significant improvement in performance CDD and PSS in general, such as efficiency, energy mass, reliability and a number of others. Ability PVC to reverse the flow of energy and the possibility of working in a step-up mode opens up the possibility to abandon the use of AB with a voltage lower than the voltage at the main output PSS and switch to using AB with an average discharge voltage close to the voltage at the main output PSS. Such a structural and circuit design solution CDD and AB will allow you to increase efficiency of CDD up to 99 % and additionally improve energy and mass characteristics PSS.

A reliable spacecraft power supply subsystem based on discrete water cycle multi-objective optimization

The successful execution of spacecraft missions relies heavily on the performance and reliability of their power supply subsystems. Achieving optimal component size and configuration is crucial for efficient power generation, distribution, and storage. Designing an efficient power supply subsystem for spacecraft missions is a complex and multi-objective optimization problem. Traditional optimization techniques, such as genetic algorithm and particle swarm optimization, have been employed, but their limitations in handling discrete variables and achieving global optima necessitate the exploration of alternative methods. In this context, this research paper explores the application of discrete water cycle algorithm (DWCA) optimization as a novel approach for optimizing the component size and configuration of spacecraft power supply subsystems. By emulating the dynamic flow and distribution of water, DWCA seeks to efficiently explore the design space and identify optimal solutions.Through comprehensive experimentation and comparative analysis, this research demonstrates that the proposed DWCA outperforms/surpasses other traditional optimization techniques in optimizing component size and configuration for spacecraft power supply subsystems. It consistently determines designs that are more efficient in power generation and storage. Moreover, DWCA enhances the efficiency and reliability of spacecraft power supply systems, especially in mission-critical scenarios. The successful optimization of spacecraft power supply subsystems is paramount to the overall success of space missions. Therefore, this advancement contributes significantly to the ongoing efforts to ensure the success of future space missions.

A Mixed Safety and Reliability Evaluation Method for the Spacecraft Power Supply System

A spacecraft power distribution system is a multi-parameter, strongly coupled complex system, and the safety of a spacecraft power distribution system directly affects the working status of the spacecraft. In order to achieve better research results in the safety analysis system of spacecraft energy systems, it is very necessary to establish an assessment method for the safety of spacecraft power distribution systems. Previous research mainly focuses on the safety assessment of power systems or aircraft power systems and has not formed a relatively complete assessment method for the safety of spacecraft power distribution systems. This paper proposes a comprehensive evaluation method for the safety of spacecraft power distribution systems. It combines objective and subjective evaluation methods to comprehensively evaluate the safety of spacecraft power distribution systems. The objective parameters of the spacecraft power distribution system are processed and objectively evaluated; Subjective evaluations are obtained using analytic hierarchy. The proposed method can reasonably evaluate the safety of spacecraft power distribution systems and assist in the selection of different spacecraft power distribution systems.

Optimization of switching losses of the Weinberg converter

DC-DC converters are widely used in hybrid power supply systems. A buffer source of electrical energy (most often a battery bank) and its charging and discharging devices are integral parts of such systems. In systems where the battery bank voltage is less than the DC-bus voltage and galvanic isolation is not required, the Weinberg converter is widely used as a discharge device, for example, in spacecraft power supply systems. The current trend in the development of hybrid power supply systems is to increase the power density of the system. Increasing the operating frequency is the simplest and most effective way to increase the power density of converter. A differential characteristic of this converter is the zero-current switching (ZCS) of transistors, which occurs due to the influence of the leakage inductance of coupled-inductors and the leakage inductance of the transformer. The paper presents an analysis of the influence of leakage inductances on the operation of the converter and a method of determining a level of turn on switching losses of transistors, which allows to ensure the necessary level of efficiency of the converter. The results of simulation modeling of the converter confirm the effectiveness of this method.

Development of a simulation model in the power conversion channel out of the solar-hydrogen power supply system installed in the spacecraft with implementation on the basis of FPGA

The article describes the method of synthesis of the simulation model of pulse converters with the control system, intended for implementation in FPGA. The technique is based on the structural representation of integro-differential and algebraic equations and the method of switching breaking functions. The models you develop allow you to bring modeling time closer to real. The method is described by an example of a solar battery energy conversion channel of an automatic spacecraft power supply system. The paper considers the possibility of implementing a solar-hydrogen energy supply scheme. This concept involves the accumulation of excess energy in the form of chemical energy on board the spacecraft.

Application of the reversible step-up and step-down pulse converter as a charging and discharging device in an autonomous system of electric power supply

Formulation of the problem. The structure shown in Figure 1 is widely used to build spacecraft power supply systems. It contains a solar battery in series and voltage regulator, which a load is connected to its output. To supply power to the load when the solar panel has no or insufficient capacity, the power supply system uses a battery pack which is charged and discharged by means of a charge-discharge device connected between the output of the voltage regulator and the battery pack. The power supply can be used to build power supply systems for a wide range of autonomous objects, such as unmanned aerial vehicles with long flight times, unattended weather stations, and environmental monitoring stations. In a power supply system with the structure shown in Figure 1, each of the devices can stabilize the output voltage: a voltage regulator, a discharge device and a battery charger. In such a power supply system, the operation of the charger and the discharger are separated in time, allowing them to function together. The use as a charge-discharge boost-decrease reversible pulse voltage converter with a high efficiency allows minimizing the number of elements in the power circuit of the device due to the possibility of reversing the energy flow reversal, which will improve the weight and size characteristics of the system and increase to increase its reliability. The purpose is to show the feasibility of using a converter with a high efficiency factor and the possibility of reversing the energy flow as a charge-discharge device as part of the power supply system of an autonomous object. To develop a model and confirm the possibility of operating the pulse converter as a charger in two modes: in the mode of providing a given charging current of the battery and in the mode of charging the battery with a decreasing current at a given voltage on the battery. Results. The expediency of using a reversible pulse converter with a high efficiency factor and the possibility of reversing the energy flow as a charger in the power supply system of an autonomous object is shown. A model has been developed and confirmed of the converter as a charger in two modes: in the mode of providing a given charging current of the battery and in the mode of charging the battery with a decreasing current at a given voltage on the battery pack. Practical Significance. The use of a reversible pulse converter as a single charge-discharge converter in the power supply system of an autonomous object will improve the mass-size characteristics, efficiency and reliability of the power supply system and increase life time of active operation of autonomous object as a whole Keywords: power supply system, autonomous object, solar battery, accumulator battery, pulse converter, charge-discharge device.

Basic aspects of topological technology of automated on-board equipment layout in space vehicle compartments using the example of “Yantar-2k” Earth remote sensing space vehicle

The article presents the theoretical foundations of automated design of on-board equipment layout in spacecraft compartments in terms of topology. The purpose of the work is to create a flexible arrangement model that would allow solving the problem for any configuration of the structure, taking into account the engineering and operational restrictions imposed on the objects located in a limited space. The technology is formalized according to the methods of the foundations of topology and in this work is demonstrated for a two-dimensional case by comparing it with a reference design-layout scheme. The functional, installation, dimensional, thermal, vibroacoustic requirements are taken into account with the mass-centering restrictions of the layout. In the course of the study, a new approach to describing the design process of assembling on-board equipment was obtained, which can be fully digitized and then integrated into known computer-aided design systems. It has been verified using the example of the power supply system of the Yantar-2k spacecraft.

АЛГОРИТМ ОПРЕДЕЛЕНИЯ ПАРАМЕТРОВ РЕГУЛЯТОРА, УДОВЛЕТВОРЯЮЩИХ ТРЕБОВАНИЯМ ПЕРЕХОДНОГО ПРОЦЕССА В ПОНИЖАЮЩЕМ ПРЕОБРАЗОВАТЕЛЕ ПОСТОЯННОГО НАПРЯЖЕНИЯ

The relevance Any modern simulator of an integral part of the spacecraft power supply system (SC PSS) is an energy-converting complex and is a continuous- discrete, non-stationary system with a variable structure. In order to fully simulate all modes of solar and storage batteries, as well as all types of electrical load, simulators must be developed consisting of several interconnected subsystems that form the overall structure of the simulator. During the tests, depending on the current mode of operation, one of the necessary (not in demand) subsystems at a given time is connected (disconnected), i.e. simulators are systems with a variable structure. Taking into account the power of the PSS of the spacecraft, simulators of the components of the PSS should have no less than the rated power, and therefore they must be created on the basis of power converters of electricity, since the latter have the best efficiency of possible energy-converting electrical systems. In addition, modern power conversion systems are impossible without the use of electronic computing tools — lower-level controllers and computers, on the basis of operating systems of which a fullfledged control software package is deployed. Thus, a modern simulator of the PSS component is a continuous-discrete impulse system. Taking into account the requirements for reliability and the period of active operation imposed on modern solar power plant simulators, it should be borne in mind that over long periods of operation, the parameters of electronic components degrade, on the basis of which power converters are built. Thus, the simulators of the PSS components of the spacecraft are non-stationary systems with long periods of active operation. Thus, at present, it is relevant to consider approaches to determining continuous linear models of power converters of electrical energy in order to synthesize the controllers of their control systems, which form the basis for constructing any simulator of an integral part of the PSS of a spacecraft. Aim of research To form a multilevel computer model of a DC converter and determine the values of the coefficients of the voltage and current PID controllers that provide optimal switching between its operating modes. Research methods Method of multilevel component chains, method of coordinate descent. Results In the format of the method of multilevel component circuits, a multilevel model is formed that provides the determination of the values of the parameters of the coefficients of the voltage and current PID controllers, at which the optimal switching between the modes of its operation is observed in the DC buck converter.

Research on Three-Port Converter for New Aerospace Energy Architecture

The traditional design method of spacecraft power systems based on customization and the combination of two-port converters can no longer meet the increasing application demands of having high power and being modular and versatile. Three-port DC converter, standardized to form a redundant parallel power supply system with a distributed model, is a possible solution to meet the design requirements of the above spacecraft power supply system. In this paper, a three-port converter is designed to complete the MPPT control of the PV array at the input end to maximize the power generated by the PV array, complete the battery charge and discharge control, realize the bidirectional conversion and transmission of the battery charge and discharge power, and complete the control of the load voltage at the output end to ensure the stable and reliable power supply of the load. If the integrated DC converter is used to realize the power transmission and conversion between the three ports at the same time, the volume and weight of the system can be greatly reduced, and then the power density of the system can be improved.

Design of universal power supply and distribution ground test system based on modularity

To solve the problems of high functional requirement, complex structure and poor versatility of manned spacecraft power supply and distribution ground test equipment, a modular universal ground power supply system (PSS) is designed. The functions of the system cover the functions of wire instruction opening, parameter measurement and state detection of the interface between the manned spacecraft and the ground equipment, and realize the universal and extensible configuration. This paper provides a general architecture design method for complex manned spacecraft power supply and distribution ground test system.

Influence of space vehicle remote power supply on thermal regimes of solar batteries

The issues of ensuring the functioning of an additional energy-receiving channel for the onboard power supply system of a low-orbit spacecraft are considered. To compensate for the shortage of electricity on board the spacecraft, various options for remote power supply from the system of space power stations transmitting energy to the solar battery by laser radiation during periods of its forced inactivity are possible. Long shadow-sunlight periods of time are a distinctive feature of functioning of low-orbit spacecraft. During these periods the solar battery is idle, and, in addition, even in the daylight portion of the spacecraft's orbit, the energy output from the spacecraft may be reduced to almost zero during the operation of some special systems that require special modes of spacecraft orientation. Reception of energy from a CES with energy flux density higher than that of the solar flux may lead to overheating of the solar battery panel of conventional design, a decrease in its efficiency and even to its failure. Therefore, the analysis of thermal modes of reception and conversion of laser radiation energy which affect the energy efficiency of the solar battery is an important aspect of remote power supply. Relationships of a mathematical model for estimating the available power supply from the solar battery operating in the mode of optimizing control of its power are proposed. The results of approbation of the model for maintaining the safe thermal mode of the solar battery panels during remote power supply of the spacecraft are presented.

СТРУКТУРНО-ФУНКЦИОНАЛЬНАЯ СХЕМА ЦИФРОВОГО ДВОЙНИКА ИСПЫТАТЕЛЬНОГО КОМПЛЕКСА СИСТЕМЫ ЭЛЕКТРОСНАБЖЕНИЯ КОСМИЧЕСКИХ АППАРАТОВ НА ОСНОВЕ МНОГОУРОВНЕВОЙ КОМПЬЮТЕРНОЙ МОДЕЛИ

Relevance Space exploration with the help of automatic spacecraft — satellites for various purposes, deep space exploration devices, has been going on for decades. Despite this, even with the current level of reliability, spacecraft fail without having exhausted the entire period of active existence. The basic part, the so-called platform of the spacecraft, as a rule, consists of its life-supporting systems: a temperature control system, an orientation system, a propulsion system, an on-board computer control system. A failure in the operation of each of them leads to an emergency situation on board, but it is enough for any part of the power supply system to fail so that the device eventually turns out to be completely inoperable. In this regard, the power supply system of the spacecraft must be subjected to high-quality ground testing, undergo several stages of testing, from autonomous to complex as part of the spacecraft. In order to confirm the predicted reliability and operability of the spacecraft power supply system, the nominal and limit modes of its operation should be simulated in ground conditions. But, for obvious reasons, the use of on-board solar and battery batteries in ground conditions, as well as the entire complex of service and useful electrical loads, is difficult and ineffective. Therefore, in order to carry out a full-fledged ground experimental testing, a special class of control and verification equipment is used – hardware and software complexes that simulate the operating modes of the power supply system, consisting of simulators of solar, rechargeable batteries and onboard electrical load, automated connection control systems. Aim of research To bring the structure of the digital twin of the spacecraft power supply system and implement a computer model of the digital twin to automate the tasks of designing, developing and ground testing of the power supply system. Research methods The method of component circuits, methods of system analysis. Results The structure of the digital twin of the spacecraft power supply system is given. A computer model of a digital double has been implemented in the domestic environment of multilevel computer modeling of MARS. The digital twin was integrated into the test bench of the power supply system by interacting with real databases and a control computer Keywords: spacecraft power supply system, ground tests, control and verification equipment, battery simulator, solar battery simulator, electric load simulator, automation of the test process, digital twin

Determination of the Solar-Battery-Simulator Modulus of Impedance for Spacecraft Power-Supply Systems

Determination of the Solar-Battery-Simulator Modulus of Impedance for Spacecraft Power-Supply Systems

High Specific Energy Design of Power Supply and Distribution System for Chang'e-5 Orbiter

Limited by the loading capability of launch vehicle, the deep space probe is required to reduce its own weight. Based on the most advanced space power supply technology in China, the power supply and distribution system of Chang’e-5 orbiter adopts ultra-high energy density solar cells and batteries, and invents a new bus topology. Through a series of lightweight power distribution system design, the power to weight ratio of the whole probe reaches the domestic leading level. The power supply and distribution system of spacecraft has passed the ground verification and flight test on in orbit, therefore can be referred for the follow-up research and design of high specific energy of power supply and distribution system of spacecraft.

The Design and Investigation of Space Photovoltaic Array Hardware-simulator

A hardware part of space photovoltaic array simulation system is designed in this paper, to realize the actual output characteristics of photovoltaic array. In this paper, the design of a PV array emulator (PVAE) is presented. By analyzing the V-I characteristic curve of solar cell given by the previous software, the simulation scheme is developed. Secondly, the control scheme of the proposed emulator based on DC-DC converter is discussed in detail, than the transfer function of the whole system is established, at last the digital controller based on DSP is designed. A prototype 200W PVAE based on full bridge DC-DC converter has been made, the experimental results show the validity of the controller design. The application of the PVAE can greatly shorten the research and design cycle of photovoltaic array power supply system of spacecraft, improve the research efficiency and credibility of research results.

Math model of a power beam feeding a spacecraft under conditions of intermittent power supply

The paper discusses transmission, reception, conversion and consumption of energy of laser and microwave radiation from Earth or space power plants. It proposes a classification of advanced systems for remote supply of power to spacecraft (SC). It addresses practicability of using remote power supply to SC under various operational conditions. The paper formulates the problem of evaluating the capability of the existing SC power supply systems to receive and convert emissions from additional sources. An analysis of criteria for the quality of pulsed or rapidly varying flow of energy into a SC power supply system. It reviews the structures of typical channels of power consumption in a SC power supply system. An equivalent circuit replacing receivers of pulsed or rapidly changing radiation is described. A math model is proposed for a power consumption channel operating under conditions of intermittent power supply to photovoltaic converters. Math modeling results are presented and analyzed. Key words: space power plant, solar array, onboard power supply system, power consumption channel, voltage converters.

Резонансный преобразователь энергии солнечной батареи в системе электропитания малого космического аппарата

The operation of a solar cell resonant converter at operating modes in the power supply system of a small spacecraft is investigated. The resonant converter with pulse-code regulation simulation model has been developed, and the operation point by stabilizing charge current mode and stabilizing output voltage mode is considered. The converter regulating characteristics in various operating modes are obtained.

Method of vibration power spectral density calculation for spacecraft attached large-size and small-mass equipment units

During the lift-off and the ascent phase, spacecraft (SC) large-size attached equipment is impacted by intensive vibrations, largely due to acoustic pressures. To ensure a reliable in-orbit operation of all SC systems the modes of vibration loads shall be assessed as much as reliable (using experimentally-confirmed mathematical models). Determination of the vibroacoustic response parameters of the equipment structure is a very important issue for such equipment units (elements) which have a large surface square with a relatively small mass. Among such structures are folded solar arrays (SA) and reflector type antennae dishes (ART). The purpose of this study is to validate the calculation methodology of vibration power spectral density (PSD) for low and medium frequency band (25-400 Hz), and apply it for the aforesaid structures in the lift-off and flight phases as part of the integrated launch vehicle in the area of maximum ram effects, when the acoustic pressure levels, and therefore their impact on the vibroacoustic response of these structures are maximum. The target goal has been implemented using the example of the solar array and reflector type antenna being used in the spacecraft power supply system and onboard radio system of one of RSC Energia-developed spacecraft. Key words: environment air, spacecraft, solar array, reflector type antennae dish, dynamic model, sound pressure level, acoustic pressure, structure vibroacoustic response.