Determination of the Microacceleration Quasisteady Component onboard the International Space Station

Convection and heat/mass transfer processes under space flight conditions

“…The aim of the first stage is to compare the data of the theoretical models and measurements and also to prepare microacceleration data for use in the mathematical models. The microacceleration measurements (using an American accelerometer) made onboard the International Space Station with subsequent filtration of the high-frequency component and comparison with the calculations for the quasi-static component indicate sufficient agreement for use in hydrodynamic models [27]. Together with the convection measurements and mathematical modeling, this forms the basis for the realization of subsequent parts of the test.…”

“…At that stage, the component r ×ω ω ω was not taken into account in the calculations. Later, a quasistatic microacceleration component calculated with account for the measured parameters of the station motion was used (see [27] and the special issues of Fluid Dynamics and KI mentioned above). For real space flight conditions, 3D thermalconvection problems with account for the data on the quasistatic component for "Mir" station motion were solved in cubic [28] and cylindrical regions [29].…”

Conjugate Problems of Transport Phenomena under Quasi‐steady Microaccelerations in Realistic Spaceflight

“…Later, a quasi‐steady microacceleration component calculated by taking into account the measured parameters of the station motion was used (see Refs. 14 and 15 with references to previous works in this field). For real spaceflight conditions, 3D thermal convection problems with account for the data on the quasi‐steady component for MIR station motion were solved in cubic 16 and cylindrical 17 regions.…”

“…Quasi‐steady components of microacceleration onboard the orbital spacecraft induced by its motion around the mass center as a rigid body, gravity gradient, and atmospheric drag may be calculated with enough accuracy on the basis of the rotatory motion, using formulation given by 14,15,21 . This formulation allows one to calculate realistic quasi‐steady microacceleration fields for any times if any kind of information makes it possible to reconstruct actual motion of the spacecraft around its mass center.…”

“…(2). 14,15,21 This formulation allows one to calculate realistic quasi-steady microacceleration fields for any times if any kind of information makes it possible to reconstruct actual motion of the spacecraft around its mass center. Such information would contain three component detections of the angular velocity.…”