Propellant Slosh Force and Mass Measurement
We have used electrical capacitance tomography (ECT) to instrument a demonstration tank containing kerosene and have successfully demonstrated that ECT can, in real time, (i) measure propellant mass to better than 1% of total in a range of gravity fields, (ii) image propellant distribution, and (iii...
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Wiley
2018-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2018/3026872 |
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| author | Andrew Hunt Richard Foster-Turner Ross Drury |
| author_facet | Andrew Hunt Richard Foster-Turner Ross Drury |
| author_sort | Andrew Hunt |
| collection | DOAJ |
| description | We have used electrical capacitance tomography (ECT) to instrument a demonstration tank containing kerosene and have successfully demonstrated that ECT can, in real time, (i) measure propellant mass to better than 1% of total in a range of gravity fields, (ii) image propellant distribution, and (iii) accurately track propellant centre of mass (CoM). We have shown that the ability to track CoM enables the determination of slosh forces, and we argue that this will result in disruptive changes in a propellant tank design and use in a spacecraft. Ground testing together with real-time slosh force data will allow an improved tank design to minimize and mitigate slosh forces, while at the same time keeping the tank mass to a minimum. Fully instrumented Smart Tanks will be able to provide force vector inputs to a spacecraft inertial navigation system; this in turn will (i) eliminate or reduce navigational errors, (ii) reduce wait time for uncertain slosh settling, since actual slosh forces will be known, and (iii) simplify slosh control hardware, hence reducing overall mass. ECT may be well suited to space borne liquid measurement applications. Measurements are independent of and unaffected by orientation or levels of g. The electronics and sensor arrays can be low in mass, and critically, the technique does not dissipate heat into the propellant, which makes it intrinsically safe and suitable for cryogenic liquids. Because of the limitations of operating in earth-bound gravity, it has not been possible to check the exact numerical accuracy of the slosh force acting on the vessel. We are therefore in the process of undertaking a further project to (i) build a prototype integrated “Smart Tank for Space”, (ii) undertake slosh tests in zero or microgravity, (iii) develop the system for commercial ground testing, and (iv) qualify ECT for use in space. |
| format | Article |
| id | doaj-art-dfaf5095de034f99b76de89d8557ca3e |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-dfaf5095de034f99b76de89d8557ca3e2025-02-03T05:57:38ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742018-01-01201810.1155/2018/30268723026872Propellant Slosh Force and Mass MeasurementAndrew Hunt0Richard Foster-Turner1Ross Drury2Atout Process Limited, Ardearn, Wilverley Road, New Milton BH25 5TX, UKAtout Process Limited, Ardearn, Wilverley Road, New Milton BH25 5TX, UKFlow Measurement and Fluid Mechanics Research Centre, Coventry University, Priory Street, Coventry CV1 5FB, UKWe have used electrical capacitance tomography (ECT) to instrument a demonstration tank containing kerosene and have successfully demonstrated that ECT can, in real time, (i) measure propellant mass to better than 1% of total in a range of gravity fields, (ii) image propellant distribution, and (iii) accurately track propellant centre of mass (CoM). We have shown that the ability to track CoM enables the determination of slosh forces, and we argue that this will result in disruptive changes in a propellant tank design and use in a spacecraft. Ground testing together with real-time slosh force data will allow an improved tank design to minimize and mitigate slosh forces, while at the same time keeping the tank mass to a minimum. Fully instrumented Smart Tanks will be able to provide force vector inputs to a spacecraft inertial navigation system; this in turn will (i) eliminate or reduce navigational errors, (ii) reduce wait time for uncertain slosh settling, since actual slosh forces will be known, and (iii) simplify slosh control hardware, hence reducing overall mass. ECT may be well suited to space borne liquid measurement applications. Measurements are independent of and unaffected by orientation or levels of g. The electronics and sensor arrays can be low in mass, and critically, the technique does not dissipate heat into the propellant, which makes it intrinsically safe and suitable for cryogenic liquids. Because of the limitations of operating in earth-bound gravity, it has not been possible to check the exact numerical accuracy of the slosh force acting on the vessel. We are therefore in the process of undertaking a further project to (i) build a prototype integrated “Smart Tank for Space”, (ii) undertake slosh tests in zero or microgravity, (iii) develop the system for commercial ground testing, and (iv) qualify ECT for use in space.http://dx.doi.org/10.1155/2018/3026872 |
| spellingShingle | Andrew Hunt Richard Foster-Turner Ross Drury Propellant Slosh Force and Mass Measurement International Journal of Aerospace Engineering |
| title | Propellant Slosh Force and Mass Measurement |
| title_full | Propellant Slosh Force and Mass Measurement |
| title_fullStr | Propellant Slosh Force and Mass Measurement |
| title_full_unstemmed | Propellant Slosh Force and Mass Measurement |
| title_short | Propellant Slosh Force and Mass Measurement |
| title_sort | propellant slosh force and mass measurement |
| url | http://dx.doi.org/10.1155/2018/3026872 |
| work_keys_str_mv | AT andrewhunt propellantsloshforceandmassmeasurement AT richardfosterturner propellantsloshforceandmassmeasurement AT rossdrury propellantsloshforceandmassmeasurement |