# US 10,865,944 B2 · Determining a gas volume in a tank device

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- Number: US 10,865,944 B2
- Document ID: US10865944B2
- Status: Granted
- Kind: B2
- Application number: 16/026,255
- Filed: 2018-07-03
- Published: 2019-01-10
- Granted: 2020-12-15
- Earliest claimed: 2017-07-06
- Assignees: Arianegroup SAS
- Applicants: ArianeGroup GmbH
- Inventors: Johannes Sebald
- Web page: https://patentgrep.com/patent/US10865944B2

## CPC

- F17C 13/028: {having the volume as the parameter}
- F02K 9/50: using pressurised fluid to pressurise the propellants
- F02K 9/56: Control
- F17C 13/008: {for use under microgravity conditions}
- F17C 13/023: {having the mass as the parameter}
- F17C 13/025: {having the pressure as the parameter}
- F17C 13/026: {having the temperature as the parameter}
- F17C 13/04: Arrangement or mounting of valves (valves per se F16K {; snap-coupling of nipples F16L37/00})
- G01F 22/02: involving measurement of pressure
- F17C 2201/0185: with separating membrane
- F17C 2205/0326: electrically actuated
- F17C 2205/0338: Pressure regulators
- F17C 2223/0161: cryogenic, e.g. LNG, GNL, PLNG
- F17C 2250/0421: Mass or weight of the content of the vessel
- F17C 2250/0426: Volume
- F17C 2250/043: Pressure
- F17C 2250/0439: Temperature
- F17C 2270/0197: Rockets
- F17C: VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES (storing fluids in natural or artificial cavities or chambers in the earth B65G5/00; construction or assembling of bulk storage containers employing civil-engineering techniques E04H7/00; variable-capacity gas-holders F17B; liquefaction or refrigeration machines, plants, or systems F25)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- G01F: MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME

## Abstract

A tank device for a tank liquid comprises a pressure vessel with a first chamber for the tank liquid and second chamber arranged in an interior of the tank. The first and second chamber are closed off with respect to each other and are in operative connection via at least one membrane which separates the first and second chambers and is capable of vibration. The tank device further comprises a controllable element for effecting a pressure surge in the pressure vessel, a pressure sensor for detecting a pressure vibration resulting from the pressure surge and a temperature sensor for measuring a temperature prevailing in the pressure vessel. An evaluation device of the tank device is configured to determine a current gas volume in the pressure vessel from a respectively detected pressure vibration and a measured temperature to thereby calculate the mass of the tank liquid.

## Claims

### Claim 1

A tank device for a tank liquid, wherein the tank device comprises:
a pressure vessel, in an interior of which a first chamber for the tank liquid and a second chamber are constructed, wherein the first and the second chamber are closed off with respect to each other and are in operative connection by means of at least one membrane, which separates the first and second chambers and is configured to vibrate;
at least one controllable element for effecting a pressure surge in the pressure vessel;
a pressure sensor for detecting a pressure vibration in at least one of the first or second chambers resulting from the pressure surge;
a temperature sensor for measuring a temperature in the pressure vessel, and
an evaluation device configured to determine a gas volume in the pressure vessel from a detected pressure vibration and a measured temperature, wherein the controllable element comprises a controllable valve, via which a gas for effecting a pressure surge is let into the first chamber or is drained out of the first chamber.

### Claim 2 (depends on 1)

The tank device according to claim 1, wherein the controllable valve is connected to a gas supply for driving the tank liquid out of the pressure vessel or to a gas outlet for pressure regulation.

### Claim 3 (depends on 1)

The tank device according to claim 1, further comprising a valve for at least one of gas supply or gas drainage into or out of the second chamber.

### Claim 4 (depends on 1)

The tank device according to claim 1, wherein the evaluation device is further configured to determine a volume of tank liquid in the pressure vessel.

### Claim 5 (depends on 1)

The tank device according to claim 1, wherein the evaluation device is further configured to determine a mass of tank liquid in the first chamber.

### Claim 6 (depends on 1)

The tank device according to claim 1, wherein the tank liquid is a cryogenic fuel.

### Claim 7 (depends on 1)

The tank device according to claim 1, wherein the pressure sensor is at least one of constructed as a piezo sensor or is configured to be used for excitation.

### Claim 8 (depends on 1)

The tank device according to claim 1, wherein a housing of the second chamber is fastened internally on the pressure vessel or is part of the pressure vessel.

### Claim 9

A rocket for use in space, comprising
a power unit, and
at least one tank device for a tank liquid, wherein the tank device comprises:
a pressure vessel, in an interior of which a first chamber for the tank liquid and a second chamber are constructed, wherein the first and the second chamber are closed off with respect to each other and are in operative connection by means of at least one membrane, which separates the first and second chambers and is configured to vibrate;
at least one controllable element for effecting a pressure surge in the pressure vessel;
a pressure sensor for detecting a pressure vibration in at least one of the first or second chambers resulting from the pressure surge;
a temperature sensor for measuring a temperature in the pressure vessel, and
an evaluation device configured to determine a gas volume in the pressure vessel from a detected pressure vibration and a measured temperature,
the tank being configured to supply the rocket with fuel,
wherein the controllable element comprises a controllable valve, via which a gas for effecting a pressure surge is let into the first chamber or is drained out of the first chamber.

### Claim 10

A method for determining a gas volume in a pressure vessel of a tank device, wherein the pressure vessel has a first chamber for a tank liquid and a second chamber wherein the first and the second chamber are closed off with respect to each other and are in operative connection by means of at least one membrane which separates the first and second chambers and is capable of vibration, and wherein the method comprises:
exciting a pressure vibration in the first chamber by means of at least one of
supplying gas into the first chamber by means of a controllable valve of the pressure vessel,
draining gas out of the first chamber by means of a controllable valve of the pressure vessel;
detecting a pressure vibration in at least one of the first or second chamber;
measuring a temperature in the pressure vessel; and
determining the gas volume in the pressure vessel from a detected pressure vibration and a measured temperature.

### Claim 11 (depends on 10)

The method according to claim 10, additionally comprising determining a volume of the tank liquid in the first chamber.

### Claim 12 (depends on 10)

The method according to claim 10, additionally comprising determining a mass of the tank liquid in the first chamber.

### Claim 13 (depends on 10)

The method according to claim 10, additionally comprising setting up a volume of the second chamber before the excitation of the pressure vibration.

### Claim 14 (depends on 10)

The method according to claim 10, wherein the excitation of the pressure vibration is carried out under a weightlessness condition of a rocket containing the tank device.

### Claim 15 (depends on 10)

The method according to claim 10, wherein the excitation of the pressure vibration is carried out under a micro-gravitational condition of a rocket containing the tank device.

### Claim 16 (depends on 10)

The method according to claim 10, wherein the excitation of the pressure vibration is carried out during acceleration of a rocket containing the tank device.

### Claim 17 (depends on 10)

The method according to claim 10, wherein the tank liquid is a cryogenic fuel.