EP4085259A1 - Pressure altering surface and a dynamic pressure sensing apparatus - Google Patents
Pressure altering surface and a dynamic pressure sensing apparatusInfo
- Publication number
- EP4085259A1 EP4085259A1 EP20828084.2A EP20828084A EP4085259A1 EP 4085259 A1 EP4085259 A1 EP 4085259A1 EP 20828084 A EP20828084 A EP 20828084A EP 4085259 A1 EP4085259 A1 EP 4085259A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pressure
- aircraft
- domed
- altering surface
- static
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000012530 fluid Substances 0.000 claims abstract description 29
- 238000005259 measurement Methods 0.000 claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 9
- 230000003068 static effect Effects 0.000 claims description 62
- 238000004891 communication Methods 0.000 claims description 20
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000009530 blood pressure measurement Methods 0.000 claims description 5
- 230000003750 conditioning effect Effects 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims 1
- 239000000203 mixture Substances 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 241000238631 Hexapoda Species 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000000356 contaminant Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L13/00—Devices or apparatus for measuring differences of two or more fluid pressure values
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P1/00—Details of instruments
- G01P1/02—Housings
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
- B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
Definitions
- the present invention relates to a pressure altering surface for a dynamic pressure sensing apparatus for use in determining the airspeed of a vehicle, such as but not limited to an aircraft.
- Pitot-static systems for determining the airspeed of aircraft are well known, whereby air pressure measurements are obtained from a pitot tube and a static port, or a pitot-static tube, for conversion into an airspeed measurement that is displayed on an airspeed indicator.
- the pressure measured by the static port is static pressure.
- the pressure measured in the pitot tube is referred to as pitot pressure, and is a measure of ram air pressure into the tube.
- the instrument is connected to both the pitot and static pressure sources, whereby the ram air from the pitot tube enters a pressure diaphragm of the instrument, and the static pressure in the airtight casing surrounding the diaphragm is vented to the static port.
- ADC Air Data Computer
- a pressure altering surface for use in an airspeed measurement system of an aircraft, the pressure altering surface comprising a fluid engaging exterior surface, the fluid engaging outer surface having a portion that is substantially domed in profile and configured to induce a pressure drop in the vicinity of the apex of the dome.
- the domed portion has circular symmetry.
- the domed portion is a spherical dome.
- the domed portion is an oblate spheroidal dome.
- the terms “the dome” and “the domed portion” are synonymous and interchangeable.
- the pressure altering surface is the outer surface or airstream engaging surface of a pressure sensing apparatus.
- airflow passing over the vicinity of the apex of the dome is substantially transverse the dome.
- the dome projects substantially orthogonally relative to the incident airflow such that the velocity of the airflow is increased as it passes over the dome, the maximum velocity being reached at or proximate the apex of the dome.
- the pressure altering surface comprises a pressure sensing means associated with the domed portion.
- the pressure sensing means is configured to measure the total pressure (po) in the vicinity of the domed portion.
- the pressure sensing means associated with the domed portion is a surface mounted pressure sensor.
- the surface mounted pressure sensor is located substantially at the apex of the domed portion
- the pressure sensing means associated with the domed portion is a pressure sensor in fluid communication with an aperture provided in the dome.
- the aperture provided in the dome is located substantially at the apex of the dome.
- the pressure sensor is in fluid communication with the aperture in the dome via a conduit extending between the pressure sensor and the aperture.
- the pressure sensor in fluid communication with the aperture is configured to measure the total pressure (po) at the dome in the vicinity of its apex.
- the pressure sensor in fluid communication with the aperture in the dome is offset with respect to a longitudinal central axis of the aperture so that the conduit extending between the pressure sensor and the aperture slopes downwardly from the pressure sensor to the aperture in use.
- the fluid engaging exterior surface of the pressure altering surface is substantially in the form of a flush fitting mounting plate contoured to fit flush with a surrounding aircraft surface at the perimeter of the pressure altering surface.
- the mounting plate defines a portion of a surface of an aircraft fuselage.
- the domed portion projects outwardly from the fluid engaging outer surface to project proud of a surrounding aircraft surface in use.
- the domed portion is formed in the mounting plate so that its perimeter is fillet formed or blended with said mounting plate.
- the mounting plate may have any suitably shaped outline.
- the mounting plate has a substantially quadrilateral outline.
- the mounting plate has a substantially circular outline.
- the air flow conduit and associated pressure sensor are enclosed within a housing.
- the housing is demountably secured to the underside of the mounting plate.
- the pressure sensing means is configured to generate signals that are representative of the total pressure (po) measured.
- the pressure altering surface further comprises a static port, the static port being spaced apart from the domed portion.
- the static port is in communication with a static pressure sensor for the measurement of static pressure (p).
- the static pressure sensor is configured to generate signals that are representative of the static pressure (p) measured.
- the signals representative of total pressure (po) and/or of static pressure (p) are transmittable to a data processor, for example an Air Data Computer (ADC) of an aircraft.
- ADC Air Data Computer
- the pressure sensing means is in communication with signal conditioning and/or processing components to receive and condition/process the signal representative of total pressure (po) and/or of static pressure (p) prior to communication to the data processor or ADC.
- an airspeed measurement system for an aircraft comprising: an air data processor; and one or more pressure altering surfaces, wherein the or each pressure altering surface comprises a fluid engaging exterior surface, the fluid engaging outer surface having a portion that is substantially domed in profile and configured to induce a pressure drop in the vicinity of the apex of the dome.
- the domed portion has circular symmetry.
- the domed portion is a spherical dome.
- the domed portion is an oblate spheroidal dome.
- the airflow in the vicinity of the apex of the dome is substantially transverse the dome.
- the domed portion is configured to induce a pressure drop in the airflow over the sensing apparatus in use.
- the dome may be provided with a heating means to prevent or mitigate the formation of ice.
- the heating means is an electrical resistance heating element.
- the pressure altering surface comprises a pressure sensing means associated with the domed portion.
- the pressure sensing means is configured to measure the total pressure (po) in the vicinity of the domed portion.
- the pressure sensing means associated with the domed portion is a surface mounted pressure sensor.
- the surface mounted pressure sensor is located substantially at the apex of the domed portion
- the surface mounted pressure sensor is configured to measure the total pressure (po) at the dome in the vicinity of its apex.
- the pressure sensing means associated with the domed portion is a pressure sensor in fluid communication with an aperture provided in the dome.
- the aperture provided in the dome is located substantially at the apex of the dome.
- the pressure sensor is in fluid communication with the aperture in the dome via a conduit extending between the pressure sensor and the aperture.
- the pressure sensor in fluid communication with the aperture is configured to measure the total pressure (po) at the dome in the vicinity of its apex.
- the pressure sensor in fluid communication with the aperture in the dome is offset with respect to a longitudinal central axis of the aperture so that the conduit extending between the pressure sensor and the aperture slopes downwardly from the pressure sensor to the aperture in use.
- the fluid engaging exterior surface of the pressure altering surface is substantially in the form of a flush fitting mounting plate contoured to fit flush with a surrounding aircraft surface at the perimeter of the pressure altering surface.
- the mounting plate defines a portion of a surface of an aircraft fuselage.
- the domed portion projects outwardly from the fluid engaging outer surface to project proud of a surrounding aircraft surface in use.
- the domed portion is formed in the mounting plate so that its perimeter is fillet formed or blended with said mounting plate.
- the mounting plate may have any suitably shaped outline.
- the mounting plate has a substantially quadrilateral outline.
- the mounting plate has a substantially circular outline.
- the air flow conduit and associated pressure sensor are enclosed within a housing.
- the housing is demountably secured to the underside of the mounting plate.
- the pressure sensing means is configured to generate signals that are representative of the total pressure (po) measured.
- the pressure altering surface further comprises a static port, the static port being spaced apart from the domed portion.
- the static port is in communication with a static pressure sensor for the measurement of static pressure (p).
- the static pressure sensor is configured to generate signals that are representative of the static pressure (p) measured.
- the signals representative of total pressure (po) and/or of static pressure (p) are transmittable to the air data processor.
- the pressure sensing means is configured to generate signals that are representative of the total pressure (po) measured and is configured to transmit the signals representative of total pressure (po) to said data processor for use in calculation of airspeed.
- the pressure sensing means communicates with signal conditioning and/or processing components to receive and condition/process the signal representative of total pressure (po) and/or of static pressure (p) prior to communication to the data processor or ADC.
- a dynamic pressure measurement apparatus comprising a pressure altering surface in accordance with the aforementioned aspects of the invention.
- a method for determining the airspeed of an aircraft comprising the steps of: measuring total pressure (po) at a substantially domed surface of a pressure altering surface provided on a surface of an aircraft, wherein the domed surface projects outwardly from the surface of said aircraft; generating a signal representative of the total pressure (po) measured at the substantially domed surface of the pressure altering surface; generating a signal representative of the static pressure (p) measured at a static port; collecting at a location remote from the substantially domed surface and the static port the signals representative of the total pressure (po) and the static pressure (p); calculating at the remote location the dynamic pressure ( q ) at the substantially domed surface; and calculating the airspeed of the aircraft.
- the method for determining the airspeed of an aircraft may comprise the further step of measuring total pressure (po) at a domed surface of a second pressure altering surface provided at a corresponding location on an opposing side of an aircraft from the first pressure altering surface, wherein the domed surface of the second pressure altering surface projects outwardly from the surface of said aircraft; generating a signal representative of the total pressure (po) measured at the substantially domed surface of the second pressure altering surface; generating a signal representative of the static pressure (p) measured at a static port; collecting at a location remote from the substantially domed surface of the second pressure altering surface and the static port the signals representative of the total pressure (po) and the static pressure (p); calculating at the remote location the dynamic pressure (q) at the substantially domed surface of the second dynamic pressure sensing apparatus; and calculating the airspeed of the aircraft based on the measurements for dynamic pressure (q) obtained via the first and second domed surfaces.
- compositions, an element or a group of elements are preceded with the transitional phrase "comprising”, it is understood that we also contemplate the same composition, element or group of elements with transitional phrases “consisting essentially of”, “consisting”, “selected from the group of consisting of”, “including”, or “is” preceding the recitation of the composition, element or group of elements and vice versa.
- the words “typically” or “optionally” are to be understood as being intended to indicate optional or non- essential features of the invention which are present in certain examples but which can be omitted in others without departing from the scope of the invention.
- FIG. 1 is a schematic side elevation of an exemplary aircraft forward fuselage incorporating a pressure altering surface of a dynamic pressure sensing apparatus for use with in the airspeed measurement system of an aircraft;
- Figure 2 is a schematic plan view of the exemplary aircraft forward fuselage of Figure 1;
- Figures 3a, 3b and 3c are schematic perspective views of examples of a pressure altering surface in accordance with the invention.
- Figures 4 and 5 are schematic cross-section views of exemplary dynamic pressure measuring apparatuses comprising pressure altering surfaces in accordance with the invention.
- Figure 6 is a schematic perspective view of a pressure altering surface including a static pressure port.
- FIG. 1 With reference to Figures 1 and 2, there is shown a forward fuselage section of an exemplary aircraft 1 incorporating a pressure altering surface 10.
- the pressure altering surface 10 is located at a position on the fuselage which will vary depending on aircraft model.
- the pressure altering surface 10 may be the airstream-engaging surface of a dynamic pressure sensing apparatus.
- the pressure altering surface 10 comprises a mounting plate 11 having a fluid engaging exterior surface 12.
- the mounting plate is a flush fitting mounting plate, contoured to fit flush with the surrounding aircraft surface 2.
- the fluid engaging outer surface 12 has a substantially domed portion 13, the substantially domed portion projecting outwardly from the surface 12 so that it projects proud of the surrounding aircraft surface 2 in use.
- mounting plate 11 is shown having a substantially quadrilateral outline however it should be understood that the mounting plate is not limited to having a substantially quadrilateral outline but may have other suitably shaped outline, for example a substantially circular outline as shown in Figure 3b.
- mounting plate 11 may also comprise a plurality of suitably arranged mounting holes 20 to enable fastening of the dynamic pressure sensing apparatus to the structure of an aircraft.
- mounting holes 20 are countersunk.
- the domed portion 13 is formed in the mounting plate 11 so that its perimeter 14 is aerodynamically blended with said mounting plate 11.
- the aerodynamic blend helps mitigate stagnation of incident airflow at the transition between the domed portion and the surrounding mounting plate.
- the aerodynamic blend also ensures that the incident airflow moves smoothly over the domed portion.
- incident airflow is substantially transverse across the pressure altering surface as shown in Figure 2.
- the height of the dome 13 is such that it extends outwardly from the surface 2 of an aircraft 1.
- the domed portion 13 induces a pressure drop in the airflow in the vicinity of its apex in use. This is achieved by the dome causing the incident airflow to increase in velocity as it passes over the dome, the maximum velocity being reached at or proximate the apex of the dome.
- the domed portion 13 has circular symmetry. This assists in maintaining consistent flow characteristics of incident airflow over the dome 13 regardless of the angle of attack of the aircraft.
- the domed portion 13 is a spherical dome.
- the domed portion 13 is an oblate spheroidal dome.
- the domed portion is dimensioned dependent upon the aircraft type with which the pressure altering surface is to be used, with the radius of and/or height of the dome being tailored to enable accurate dynamic pressure measurement within the anticipated operating airspeed range of the aircraft.
- the trailing edge of the dome may be a faired, i.e. include a fairing, or may include a suitable aerodynamic feature to reduce the drag created by the dome.
- the dome 13 may be formed in the mounting plate by press forming, for example when the mounting plate 11 is made from aluminium or other metal or metal alloy.
- the domed portion 13 may be formed in the mounting plate by vacuum or other suitable forming means, for example where the mounting plate is made from composite or polymeric material.
- the dome may be provided with a heating means 21 to prevent or mitigate the formation of ice.
- the heating means may be any suitable heating means, for example, but not limited to, an electrical resistance heating element.
- the pressure altering surface apparatus comprises a pressure sensing means associated with the domed 13 portion.
- the pressure sensing means is configured to measure the total pressure (po) in the vicinity of the domed portion. Together, the pressure altering surface and the pressure sensing means provide a pressure sensing apparatus.
- the pressure sensing means associated with the domed portion may be a surface mounted pressure sensor 15b.
- Surface mounted pressure sensor 15b may include any suitable surface mounted pressure sensing device as will be understood by those of skill in the art.
- the surface mounted pressure sensor 15b may be located substantially at, near or overlapping the apex of the domed portion 13.
- Surface mounted pressure sensor 15b is configured to measure the total pressure (po) at the dome 13.
- the pressure sensing means associated with the domed portion 13 is a pressure sensor 17 (shown in Figure 4) in fluid communication with an aperture 15a provided in the dome.
- Aperture 15a may be located substantially at, near or overlapping the apex of the domed portion 13.
- aperture 15a is in fluid communication with a conduit 16, the conduit 16 extending from aperture 15a to pressure sensor 17.
- the conduit 16 and pressure sensor 17 are enclosed within a housing 18.
- Housing 18 may be demountably secured to the underside of the mounting plate 11. Housing 18 locates within the aircraft fuselage in use.
- conduit 16 slopes downwardly towards the aperture 15a when the apparatus is positioned at an in use orientation as shown in Figure 5.
- the pressure sensor 17 may be located or offset with respect to a longitudinal central axis 19 of the aperture 15a so that the conduit 16 slopes downwardly from the pressure sensor 17 to the aperture 15a when the apparatus is positioned at an in use orientation.
- the slope of the conduit 16 permits debris or water or other liquid contaminants to flow from the conduit 16 and out of the dome thus mitigating blockage of the conduit.
- Pressure sensor 17 is configured to measure the total pressure (po) at the dome 13.
- Pressure sensor 17 may include any suitable pressure sensing device as will be understood by those of skill in the art.
- the pressure sensor 17 or surface mounted pressure sensor 15b generates a signal that is representative of the total pressure (po) measured.
- This signal representative of total pressure is sent to a data processor, for example an Air Data Computer (ADC) 30 of an aircraft.
- the signal may be analogue or digital, or may be converted from analogue to digital by analogue to digital converter either before, or by, the data processor or ADC 30.
- Suitable signal conditioning and/or processing components may be provided to receive and condition/process the signals prior to communication to the data processor or ADC 30.
- the pressure altering surface 10 in accordance with the invention as described above may be the airstream engaging surface of a dynamic pressure sensing apparatus 50 in accordance with a further aspect of the invention, for example as indicated generally in Figures 4 and 5.
- the dynamic pressure will be a negative value as the airflow across the dome induces a pressure drop in conduit 16 or at the surface mounted pressure sensor 15b, where applicable.
- a static port 40 and associated static pressure sensor 41 spaced apart from the dome 13 as shown by way of example in Figures 1 and 4 provides a reference value corresponding to the static pressure (p), and a signal representative of the measured static pressure is also sent to the data processor ADC 30.
- Such a static port 40 and associated static pressure sensor 41 may be provided integrally with the pressure altering surface as shown by way of example in Figure 6, in which the static port 40 is formed in the mounting plate 11 at a position spaced apart from the domed portion 13.
- the data processor or ADC can calculate the dynamic pressure (q).
- a second pressure altering surface 10 may also be provided at a corresponding location B ( Figure 2) on the opposing side of an aircraft from the first pressure altering surface.
- readings for dynamic pressure can be obtained from both sides of an aircraft, which may differ due to the effect of an aircraft’s yaw angle, and the difference between the values measured or obtained from the first and second pressure altering surfaces 10 can be used to calculate the airspeed, or a yaw-angle compensated airspeed.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1918394.6A GB2589920A (en) | 2019-12-13 | 2019-12-13 | Pressure altering surface for a dynamic pressure sensing apparatus |
PCT/GB2020/053178 WO2021116694A1 (en) | 2019-12-13 | 2020-12-11 | Pressure altering surface and a dynamic pressure sensing apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4085259A1 true EP4085259A1 (en) | 2022-11-09 |
Family
ID=69186687
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20828084.2A Withdrawn EP4085259A1 (en) | 2019-12-13 | 2020-12-11 | Pressure altering surface and a dynamic pressure sensing apparatus |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP4085259A1 (en) |
GB (1) | GB2589920A (en) |
WO (1) | WO2021116694A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114735231B (en) * | 2021-12-30 | 2024-06-18 | 中国人民解放军93184部队 | Flight data acquisition device |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3318146A (en) * | 1966-02-14 | 1967-05-09 | Rosemount Eng Co Ltd | Pressure sensing instrument for aircraft |
US3673866A (en) * | 1970-01-15 | 1972-07-04 | Viktor Borisovich Alperovich | Pitot tube probe for taking total head and static pressure of air flow |
US4096744A (en) * | 1975-09-05 | 1978-06-27 | Rosemount Inc. | Pressure sensor for determining airspeed, altitude and angle of attack |
GB1579638A (en) * | 1977-06-24 | 1980-11-19 | Secr Defence | Airstream pressure sensing probes |
DE3544144A1 (en) * | 1985-12-13 | 1987-06-25 | Eduard Prof Dr Ing Igenbergs | METHOD AND DEVICE FOR DETERMINING A FLOW ANGLE ON VEHICLES |
US4718273A (en) * | 1985-12-31 | 1988-01-12 | The Garrett Corporation | Combination alpha, static and total pressure probe |
US7389686B2 (en) * | 2006-03-22 | 2008-06-24 | Honeywell International Inc. | Methods and systems for determining air data parameters |
FR3021116B1 (en) * | 2014-05-13 | 2018-12-07 | Airbus Operations | MEASURING SYSTEM FOR MEASURING THE SPEED OF AN AIRCRAFT |
-
2019
- 2019-12-13 GB GB1918394.6A patent/GB2589920A/en not_active Withdrawn
-
2020
- 2020-12-11 EP EP20828084.2A patent/EP4085259A1/en not_active Withdrawn
- 2020-12-11 WO PCT/GB2020/053178 patent/WO2021116694A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
WO2021116694A1 (en) | 2021-06-17 |
GB201918394D0 (en) | 2020-01-29 |
GB2589920A (en) | 2021-06-16 |
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