Method for thermally gauging the tank of a spacecraft and a spacecraft equipped with means for implementing such a method
US11307077B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 8, 2017 |
| Grant date | Apr 19, 2022 |
| Priority date | — |
| Expiry date | Jul 14, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF17C13/026
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
Disclosed is a method for gauging the liquid propellant tank of a spacecraft during a phase of high-thrust along an axis, the tank being thermally conductive and having a known geometry. The method includes steps of: attaching, on a wall of the tank, a heating member and at least one temperature sensor in proximity to the heating member and in a plane of interest perpendicular to the thrust axis; during the high-thrust phase, heating the wall of the tank and acquiring temperature measurements of the wall of the tank at rapid frequency; determining the instant I when the temperature measured by the sensor changes, such change indicating the presence of the liquid-gas interface in the tank in the plane of interest; and determining the volume of liquid propellant present in the tank at instant I.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.