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This requires a thermal hardware that accounts for up to 50% of RFCS mass budget.
For such applications, the use of a flat shape evaporator is very promising, limiting the volume and the mass of the thermal hardware.
This chapter outlines the design objectives and the requirements of the spacecraft components for the different modes of operation, and the tasks to be considered in the design process: the selection of the thermal hardware and the prediction of the temperatures in the spacecraft selected points.
The primary aim of the design was to develop thermal hardware components that can be manufactured simply and cost effectively.
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In this contribution the control design for a thermal hardware-in-the-loop test bench is described.
Hydrogen refueling of the mhH2LT is possible even without external sources of cooling water by making use of thermal management hardware already installed on the PEM fuel cell.
The integration of thermal hydraulic hardware tests with simulated neutronic response provides a bridge between electrically heated testing and testing with nuclear fuel elements installed.
Kinetics, thermodynamics, hydrodynamics, mixing, thermal requirements, hardware design and economics intertwine within the confines of the reactor and in turn are impacted by ancillary requirements of the entire process system.
A new spacecraft thermal control hardware composed of two parallel channels working for heat pipe (HP) and solid liquid phase change material (PCM), respectively, is suggested for the high heat dissipating component which works intermittently with short duty.
Based on thermal transport hardware and software, it was possible to calculate thermal conductivity directly from the applied heater power, resulting ∆T, and sample geometry using the equation: k=frac{Pl}{Sleft {T}_2-{T}_1right)} (1 where k is the thermal conductivity (W/Km), P is applied heater power (W), l is the height of measured sample (m) and S is the cross sectional area of sample (m2).
For this purpose, the available references and lessons learned by the National Technical University of Ukraine during the elaboration of thermal control hardware for micro-satellites Magion 4, 5, BIRD and autonomous thermal control systems for interplanetary missions VEGA, PHOBOS have been used.
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