What we measure

One sensing platform, applied across the sealed systems that decide a mission. Fill and slosh in tanks, combustion inside chambers, and flow through feed lines, all read from the outside.

One platform, many geometries

The platform separates hardware, sensor heads and data, so customers integrate without rebuilding. One shared core reads every geometry, from spacecraft tanks to feed lines to combustion chambers.

RING SENSOR HEAD

Spacecraft tanksFill, slosh and gauging

Propellant mass, phase boundaries and slosh in sealed spacecraft tanks, resolved in any gravity. Remaining propellant decides a satellite’s working life; reading it keeps hardware in service longer.

COLLAR SENSOR HEAD

Feed systemsFlow, entrainment and phase

Flow behaviour, gas entrainment and phase in propellant feed lines, read through the pipe wall.

BAND SENSOR HEAD

Combustion chambersImaging and acceptance

Internal combustion imaging over a full firing, from ignition to flameout, for propulsion test and acceptance programmes.

The Vira platform

Core hardware

One shared electronics core drives every sensor head, so a new geometry needs only a new sensor head.

Data layerReconstruction and outputs

The measured field solved into the interior and returned as live numbers and images.

Adjacent markets like liquefied gases and hydrogen are later-stage optionality, not near-term products.

The hardware behind the product lines

Real hardware from the heritage programme and founder research that Evandor’s Vira lines build on. Electrode arrays sit around each vessel and read the interior through the wall.

CAD model of the twin-tank sensing assembly, with electrode arrays around each spherical tank and feed valves on the baseplate — Twin-tank sensing assembly, CAD. Electrode arrays around each tank, feed and drain valves on the baseplate.

The twin-tank sensing assembly as built, with electrode arrays cabled around both tanks — The same assembly as built, electrode arrays cabled for test.

Portable combustion imaging system in its flight case: measurement unit, electrode ring sensor and cabling in cut foam — Combustion imaging system in its carry case, ring sensor and measurement unit; the portable kit behind the combustion line.

The MACAW hybrid rocket motor firing with the ECT sensor head installed around the combustion section — The same sensor class firing on the MACAW hybrid rocket motor. Founder-authored research, Kingston University London.

Measurement accuracy

The first three figures come from the published ECT record and describe the measurement class, not a qualified Evandor product; they are also definition-sensitive. The final row sets them against the gauging methods flying today.

Accuracy

Measurement

Source

<1%

Average mass in a real satellite tank, slosh resolved to within ±0.1%.

Heritage satellite tank programme

0.3–0.9%

Full-tank-mass uncertainty in microgravity gauging.

Parabolic-flight campaign

±0.2%

Bubbled-gas agreement in cryogenic liquid nitrogen.

Cryogenic LN2 test programme

2–5%

Current industry standard: published end-of-life errors of about 4.6% for bookkeeping, 4.8% for the pressure-volume-temperature method and 1.9% for thermal gauging.

Industry standard, published gauging-accuracy analyses

Figures are attributed to their source programmes. Spaceflight work may be export-controlled.

Tell us what you need to measure

Tell us the vessel and the measurement; we will say what the sensing resolves today.

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