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In this paper, a newly developed Active Noise Control (ANC) system is introduced, that effectively reduces road noise, which becomes a major issue with electrified vehicles, and that enhances vehicle interior sound levels matching seamless acceleration by electric drive. Conventionally, reducing road noise using ANC requires numerous sensors and speakers, as well as a processor with high computing power. Therefore, the increase in system cost and the complexity of the system are obstacles to its spread. To overcome these issues, this system is developed based on four concepts. The first is a modular system configuration with unified interface to apply to various vehicle types and grades. The second is the integration and optimal placement of noise source reference sensors to achieve both reduction in number of parts and noise reduction performance.

The thermal feasibility of BepiColombo MMO (Mercury Magnetospheric Orbiter) is shown. The temperatures of upper and lower decks on which instruments are located are controlled with in the allowable limit: -30 to 60 degrees C. The battery temperature is also controlled from 0 to 20 degrees C. Because MMO is spin-stabilized spacecraft, MMO requires the sun-shield and the radiator-shield in the cruise phase (Earth to Mercury) in which MMO is 3-axis stabilized, to avoid the exposure to the direct solar flux.

A scoping thermal analysis was done to evaluate the general feasibility of capillary pumped heat engines. The analysis was motivated by recent advances in nanoscale materials science that have made it increasingly practical to manufacture high porosity wicks with a median pore diameter on the order of a few nanometers. Capillary pumped heat engines are shown to be generally feasible for wick evaporation rates equivalent to about 1 watt per square centimeter when wick material thermal conductivity on the order of a few W/m-K is assumed. A compact heat engine architecture, referred to as an integrated capillary engine, is introduced.

The thermal design of the LUNAR-A spacecraft, investigating the internal structure of the moon, is a challenge due to the widely varying thermal environments. A passive thermal control philosophy of radiators, multilayer insulation (MLI) and heaters was used for the LUNAR-A thermal design. Verification of the design was performed separately for the major spacecraft modules which consisted of a main structure, a propulsion subsystem and penetrators. As consequence, acceptable thermal performance can be expected for all phases of the mission. This paper describes the thermal design, analysis, thermal model testing and in-orbit temperature predictions.

An effective thermal verification method for spacecrafts is introduced, in which their partial model or structural segment can be used in the test. The essence of this concept is to evaluate thermal design of the spacecraft by integrating a thermal vacuum test into thermal analyses system as a data generating subroutine. The measured temperature data are used for modification of the thermal mathematical model, which in turn requires to generate new test data for further refining of the model. Practically, the verification process is a kind of numerical simulation using the in-situ temperature measurements obtained from the thermal vacuum test run simultaneously with the simulation analysis. This direct coupling or “hybrid simulation” process is terminated when the thermal mathematical model is finalized to determine the spacecraft hardware design.