Onboard Electrical Power System

The onboard electrical power system [1] has three distinct components, namely the battery, solar array, and voltage regulation circuitry. Critical devices and circuits used by these three components are clearly shown in Figure 2.1. 

Also an onboard electrical power supply, e.g., by photovoltaic cells or thermogenerators coimected to a lab-frame irradiation source, would introduce additional, frequency-independent degrees of freedom, enabling a multi-force manipulation of the processed liquids. Another extension of present centrifugal systems is the (wireless) data communication with the lab-frame workstation for an improved process control and analysis. 

Electrical Power. The electrical power system is responsible for power generation, capture, or storage, plus delivery of conditioned electrical power to all parts of the spacecraft. Power may be generated by onboard reactors such as fuel cells, or captured from sunlight by solar panels. Power from sunlight is stored in rechargeable batteries for later use when the spacecraft is in eclipse, or for times when power demand temporarily exceeds the total available from solar panels alone. Power-conditioning circuits are necessary to pro dde electricity at the volb e, current, and stability required by individual components. 

Onboard power sources. Electric power generated by them powers the instrumentation in space vehicles it serves system survival and the operation of electric jet engines of low propulsion. 

Installation of solar panels is required to charge the onboard batteries that are providing the electrical power to various electronics devices, stabilizing and attitude control sensors, space parameter monitoring instrument, lighting, and a host of other electrical systems that are vital in maintaining the desired performance of the satellite or spacecraft over the intended mission duration. 

Note These projected values are based on the data collected in the late 1960s for a spacecraft power system. Furthermore, these values show merely a trend in cost factor as a function of various redundant options and mission duration and must not be taken as guaranteed values for other spacecraft or comm unication or reconnaissance satellite. Electrical load requirements are a function of electrical and electronic sensors and devices operating onboard the spacecraft. Additional electrical power is required for attitude and stabilization control mechanisms, which is significantly greater than the electrical power required for onboard electronic sensors and electrical devices. 

Battery power requirements to some extent depend on the mass of the satellite, which includes the weight of microwave transmitters, receivers, antennas, signalprocessing equipment, electronic sensors, onboard electrical appliances, solar panels and associated components, and the stabilization system. Two distinct types of stabilization system design configurations and associated components for satellite control are shown in Figure 2.6. Table 2.12 summarizes the battery power requirement and other critical parameters of commercial and military communications satellites. 

SSPE (Sous-Systdme Puissance Electrique) electric power sub-system providing power generation and distribution onboard, and particitlarly to electrical equipment ... 

Energy systems in space technology are devices that convert one kind of energy into another to ensure the functioning of automated and piloted satellites, interplanetary probes, and other kinds of spacecraft. Multiple functions of any spacecraft require two distinctly different energy sources propulsion for launch and maneuvers, and electricity supply to power the onboard equipment. 

Power supply systems provide electricity to feed the onboard spacecraft equipment and can be classified by the primary energy sources chemical, solar, and nuclear. 

Nuclear power propulsion systems (NPPS) in contrast to onboard sources and NPPs discussed in o Sects. 59.2.1 and O 59.2.2, respectively, may perform both functions generate electric energy for the spacecraft s onboard needs and/or heat the propellant producing thrust (Pupko et al. 1991 Kolganov et al. 1993 Ponomarev-Stepnoi and Usov 1995 Ponomarev-Stepnoi et al. 1995, 1996, 2003, 2005). 

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