GB2588597A - Monitoring system for aircraft - Google Patents

Monitoring system for aircraft Download PDF

Info

Publication number
GB2588597A
GB2588597A GB1915218.0A GB201915218A GB2588597A GB 2588597 A GB2588597 A GB 2588597A GB 201915218 A GB201915218 A GB 201915218A GB 2588597 A GB2588597 A GB 2588597A
Authority
GB
United Kingdom
Prior art keywords
hydraulic accumulator
gas
temperature
accumulator
aircraft
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.)
Pending
Application number
GB1915218.0A
Other versions
GB201915218D0 (en
Inventor
Bidmead Ashley
Becher Florian
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations Ltd
Original Assignee
Airbus Operations Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Operations Ltd filed Critical Airbus Operations Ltd
Priority to GB1915218.0A priority Critical patent/GB2588597A/en
Publication of GB201915218D0 publication Critical patent/GB201915218D0/en
Publication of GB2588597A publication Critical patent/GB2588597A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B1/00—Installations or systems with accumulators; Supply reservoir or sump assemblies
    • F15B1/02—Installations or systems with accumulators
    • F15B1/04—Accumulators
    • F15B1/08—Accumulators using a gas cushion; Gas charging devices; Indicators or floats therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
    • B60T17/06—Applications or arrangements of reservoirs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
    • B60T8/17—Using electrical or electronic regulation means to control braking
    • B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
    • B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/40—Transmitting means with power amplification using fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/22—Operating mechanisms fluid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B64C25/44—Actuating mechanisms
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • 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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B19/00—Testing; Calibrating; Fault detection or monitoring; Simulation or modelling of fluid-pressure systems or apparatus not otherwise provided for
    • F15B19/005—Fault detection or monitoring
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T2270/00—Further aspects of brake control systems not otherwise provided for
    • B60T2270/40—Failsafe aspects of brake control systems
    • B60T2270/406—Test-mode; Self-diagnosis
    • 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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2201/00—Accumulators
    • F15B2201/20—Accumulator cushioning means
    • F15B2201/205—Accumulator cushioning means using gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2201/00—Accumulators
    • F15B2201/50—Monitoring, detection and testing means for accumulators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2201/00—Accumulators
    • F15B2201/50—Monitoring, detection and testing means for accumulators
    • F15B2201/51—Pressure detection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/20—Fluid pressure source, e.g. accumulator or variable axial piston pump
    • F15B2211/21—Systems with pressure sources other than pumps, e.g. with a pyrotechnical charge
    • F15B2211/212—Systems with pressure sources other than pumps, e.g. with a pyrotechnical charge the pressure sources being accumulators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/60—Circuit components or control therefor
    • F15B2211/63—Electronic controllers
    • F15B2211/6303—Electronic controllers using input signals
    • F15B2211/6306—Electronic controllers using input signals representing a pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/60—Circuit components or control therefor
    • F15B2211/63—Electronic controllers
    • F15B2211/6303—Electronic controllers using input signals
    • F15B2211/6343—Electronic controllers using input signals representing a temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/80—Other types of control related to particular problems or conditions
    • F15B2211/857—Monitoring of fluid pressure systems
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/16—Mechanical energy storage, e.g. flywheels or pressurised fluids

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Transportation (AREA)
  • General Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Supply Devices, Intensifiers, Converters, And Telemotors (AREA)

Abstract

A monitoring system (fig.1,100), for an aircraft hydraulic accumulator 210, has a controller (fig.1,110) configured to determine a characteristic of the accumulator on the basis of a first determined temperature and a first determined pressure of a gas 212 in the accumulator; the characteristic may be a volume of fluid, and/or an amount of energy stored, in the accumulator. Preferably, a second temperature and second pressure of the gas are determined to determine a rate of change in the characteristic. The controller may perform an action based on the characteristic, such as output a signal with information representing the characteristic and/or issuing a warning. The system may have an accumulator body temperature sensor 120 coupled to a surface of the accumulator; the body temperature is used by the controller to determine the gas temperature. A pressure sensor 130 may be used to determine the pressure. Also claimed is a hydraulic accumulator system for an aircraft with a temperature sensor arranged to sense a temperature of the accumulator body 211, this indicating a temperature of the gas in the accumulator.

Description

MONITORING SYSTEM FOR AIRCRAFT
TECHNICAL FIELD
[0001I The present invention relates monitoring systems for aircraft comprising hydraulic accumulators, and to methods of determining characteristics of hydraulic accumulators of aircraft.
BACKGROUND
[0002] Hydraulic systems on aircraft, such as hydraulic braking systems, typically. comprise at least one hydraulic accumulator. The hydraulic accumulator absorbs, releases and stores energy in the hydraulic system. The hydraulic accumulator may store and release energy for operating certain components of the hydraulic system, such as brake actuators of a hydraulic braking system, or door actuators of a landing gear bay door, for example.
[0003] Generally, an amount of hydraulic fluid in at least a part of the hydraulic system may reduce over time, for instance due to small leaks, or as hydraulic fluid is transferred between different parts of the hydraulic system. For example, hydraulic fluid may be transferred from an auxiliary, or emergency, line of the hydraulic system to a main line of the hydraulic system. The fluid may then be prevented from returning to the auxiliary line, for instance by a non-return valve, thereby leading to a reduced amount of fluid in the auxiliary line of the hydraulic system.
[0004] Conventionally" the amount of fluid in the hydraulic system, or an amount of energy stored in the hydraulic accumulator, may be determined by detecting a pressure of the fluid in the hydraulic system. Fluid may be added to the hydraulic system, such as to the hydraulic accumulator:, if the amount of hydraulic fluid drops below a threshold value. Adding fluid to the hydraulic system or components thereof may be referred to as refilling the hydraulic system or components thereof If a rate of reduction of hydraulic fluid in the system is high, this may indicate a fault in the hydraulic system.
[0005] There is a need for a system for reliably determining an amount of stored in a hydraulic accumulator.
SLINIM.MCI [0006] A first aspect of the present invention provides a monitoring system for monitoring a hydraulic accumulator of an aircraft, the monitoring system comprising a controller that is configured to: determine a first gas temperature of a gas in the hydraulic accumulator; determine a first gas pressure of the gas in the hydraulic accumulator; and determine a characteristic of the hydraulic accumulator on the basis of the first gas temperature and the first gas pressure.
[0007] Optionally the controller is configured to: determine a second gas temperature of the gas; determine a second gas pressure of the gas; and determine a change or rate of change in the characteristic of the hydraulic accumulator, on the basis of the first and second gas temperatures and the first and second gas pressures [0008] Optionally, the controller is configured to determine the first gas temperature and the first gas pressure at a first time, and to determine the second gas temperature and the second gas pressure at a second time, wherein the change or rate of change is over a period starting at the first time and ending at the second time.
[0009] Optionally: the period has a length of up to one minute: more than one minute, more than ten minutes, or more than thirty minutes.
[0010] Optionally, the characteristic of the hydraulic accumulator comprises one or both of a volume of fluid in the hydraulic accumulator and all amount of energy stored in the hydraulic accumulator.
[0011] Optionallt the controller is configured to perform an action on the bask of the characteristic of the hydraulic accumulator.
[0012] Optionally, the action to be performed comprises one or both of outputting a signal comprising information representative of the characteristic; and causing issuance of a warning.
[0013] Optionally, the controller is configured to perform the action on the eQsis of the change or rate of change in the characteristic of the hydraulic accumulator.
[0014] Optionally, the monitoring system comprises a display to display information relating to the hydraulic accumulator to a user or operator, the controller is configured to output the signal comprising information representative of the characteristic to the display, and the display is configured to display information relating to the characteristic on the basis of the signal.
[0015] Optionally" the signal is representative of the change or rate of change in the characteristic.
[0016] Optionally, the monitoring system comprises a temperature sensor arrangement configured to sense a first body temperature of a body of the hydraulic accumulator, wherein the first body temperature is indicative of the first gas temperature.
[0017] Optionally, the temperature sensor arrangement is configured to sense a second body temperature, wherein the second body temperature is indicative of the second gas temperature.
[0018] Optionally, the monito!ring system comprises a pressure sensor arrangement configured to sense a first fluid pressure of fluid in the hydraulic accumulator, wherein the first fluid pressure is indicative of the first gas pressure [0019] Optionally, the pressure sensor arrangement is configured to sense a second fluid pressure of the fluid in the hydraulic accumulator, wherein the second fluid pressure is indicative of the second gas pressure [0020] Optionally, at least a part of the pressure sensor an ge cut is coupled to a port of the hydraulic accumulator.
[002]1 Optionally, the controller is configured to determine the first gas temperature on the basis of the first body temperature.
[0022] Optionally, the controller is configured to detennine the first gas pressure on the basis of the first fluid pressure.
[00231 Optionally. at least a pint of the temperature sensor arrangement is coupled to a surffice of the Hydraulic accumulator.
[0024] Optionally. Lire surface is an outer surface of ihe hydraulic accumulator.
[0025] Optionally, the temperature sensor arrangement is removably coupled to the surface of the hydraulic accumulator.
[0026] Optionally, the controller is configured to cause pressurisation of the hydraulic accumulator and determine the first gas temperature and the first gas pressure a predetermined period of time after causing pressurisation of the hydraulic accumulator.
[0027] Optionally, the hydraulic accumulator is an aircraft braking system hydraulic accumulator, [0028] A second aspect of the present invention provides a method of determin g a characteristic of a hydraulic accumulator of an aircraft, the method comprising: determining a first gas temperature of a gas in the hydraulic accumulator; determining a first gas pressure of the gas in the hydraulic accumulator; and determining the characteristic of the hydraulic accumulator on the basis of the first gas temperature and the first gas pressure.
[0029] Optionally, the method comprises determining a second gas temperature of the gas, determining a second gas pressure of the gas, and determining a change or rate of change in the characteristic of the hydraulic accumulator, on the basis of the first and second gas temperatures and the first and second gas pressures [0030] Optionally, the method comprises deternm irst gas temperature and the first gas pressure at a first time, and determining the second gas temperature and the second gas -pressure at a second time, Nyherein the change or rate of change is over a period starting at the first time and ending at the second time.
[0031] Optionally, he period has a length of up to one minute, more than one minute, more than ten minutes, or more than thirty minutes.
[0032] Optionally" the characteristic of the hydraulic accumulator compri, s one or both of a volume of fluid in the hydraulic accumulator and an amount of enere, stored in the hydraulic accumulator.
[0033] Optionally, the method comprises sensing a first body temperature of a body of the hydraulic accumulator and determining the first gas temperature on the basis of the first body temperature.
[0034] Optionally, the method further comprises sensing a first fluid pressure of a fluid in the hydraulic accumulator and determining the first gas pressure on the basis of the first fluid pressure.
[0035] Optionally, the method comprises sensing a. second body temperature of the body of the hydraulic accumulator and determining the second gas temperature on the basis of the second body temperature.
[0036] Optionally, the method comprises sensing a second fluid pressure of the fluid in the hydraulic accumulator and determining the second gas pressure on the basis of the second fluid pressure.
[0037] Optionally; the method comprises determining a change or rate of change in status of the hydraulic accumulator, on the basis of the first and second gas temperatures and pressures 10038 nally, the method comprises performing an action on the basis of the characteristic of the hydraulic accumulator.
[0039] Oplionallv, performing the action comprises one or both of outputting a signal comprising information representative of the characteristic and causing issuance of a warning.
10040] Optionally, the method comprises performing the action on the basis ofthe change or rate of change in the characteristic of the hydraulic accumulator.
[0041] Optionally, the method comprises outputting the signal comprising information representative of the characteristic to a display, and displaying information relating to the characteristic on the basis of the signal on the display.
[0042] Optionally, the signal is representative of the change or rate of change hi the characteristic.
[0043] Optionally, the method comprises press sing the hydraulic accumulator, and determining the first gas temperature and the first gas pressure a predetermined period of time after the pressurising the hydraulic accumulator, [0044] Optionally, the hydraulic accumulator is an aircraft braking system hydraulic accumulator.
[0045] A third aspect of the present invention provides on-transitory co mpute r--readable storage medium storing instructions that, if executed by a controller of a monitoring system of an aircraft, cause the controller to carry out the method according to the second aspect of the present invention.
[0046] A fourth aspect of the present invention provides an aircraft system for an aircraft, the aircraft system comprising: a braking system that is configured to brake a landing gear of the aircraft, the braking system comprising a hydraulic accumulator; and a monitoring system comprising a temperature sensor arrangement configured to sense a body temperature of a body of the hydraulic accumulator, a pressure sensor arrangement configured to sense a fluid pressure of fluid in the hydraulic accumulator, and a controller that is configured to: determine a gas temperature of a gas in the hydraulic accumulator, on the basis ofthe body temperature; determine a gas pressure ofthe gas in the hydraulic accumulator, on the basis of the fluid pressure; and determine a characteristic of the hydraulic accumulator on the basis of the nas temperature and the gas pressure.
[0047] Optionally the controller is configured to: determine a second gas temperature of the gas: determine a second gas pressure of the gas; and determine a change or rate of change in the characteristic of the hydraulic accumulator, on the basis of the first and second gas temperatures and the first and second gas pressures.
[0048] Optionally, the controller is configured to determine the first gas temperature and the first gas pressure at a first time, and to determine the second gas temperature and the second gas pressure at a second time, wherein the change or rate of change is Over a period starting at the first time and ending at the second time.
[0049] Optionally, the period has a length of up to one minute, more than one minute, more than ten minutes, or more than thirty minutes.
[0080] Optionally, the characteristic of the hydraulic accumulator comprises one or both of a volume of fluid in the hydraulic accumulator and an amount of energy stored in the hydraulic accumulator.
[0051] Optionally, the controller is configured to perform action on the basis of the characteristic of the hydraulic accumulator.
[0052] Optionally, the action to be pet-fin/lied comprises one or both of outputting a signal comprising information representative of the characteristic; and causing issuance of a warning.
[0053] Optionally the the controller is configured to perform the action on the basis of the change or rate of change in the characteristic of the hydraulic accumulator.
[0054] Optionally, the monitoring system comprises a display to display information relating to the hydraulic accumulator Co a user or operator, the controller is configured to output the signal comprising information representative of the characteristic to the display, and the display is configured to display information relating to the characteristic on the basis of the signal.
[0055] Optionally, the signal is representative of the change or rate of change iii th characteristic.
[0056] Optionally, the monitoring system comprises a temperature sensor arrangement configured to sense a first body temperature of a body of the hydraulic accumulator, wherein the first body temperature is indicative of the first gas temperature.
[0057] Optionally, the temperature sensor arrangement is configured to sense a second body temperature, wherein the second body temperature is indicative of the second gas temperature.
[0058] Optionally, the morn( comprises a pressure sensor arrangement configured to sense a first fluid pressure of fluid in the hydraulic accumulator, wherein the first fluid pressure is indicative of the first gas pressure.
[0059] Optionally, the pressure sensor arrangement is configured to sense a second fluid pressure of the fluid in the hydraulic accumulator, wherein the second fluid pressure is indicative of the second gas pressure [0060] Optionally:, at least a part of the pressure sensor an go cut is coupled to a port of the hydraulic accumulator.
[006]1 Optionally, the controller is configured to determine the first gas temperature on the basis of the first body temperature.
[0062] Optionally, the controller is configured to detennine the first gas pressure on the basis of the first fluid pressure.
[00631 Optionally, at least a part of the temperature sensor arrangement is coupled to a surfilec of the hydraulic accumulator.
[0064] Optionally, the surface is an outer surface of the hydraulic accumulator.
[0065] Optionally, the temperature sensor arrangement is removably coupled to the surface of the hydraulic accumulator.
[0066] Optionally, 'the hydraulic accumulator is in aircraft braking system hydrau accumulator.
[00671 A fifth aspect of the present invention provides an accumulator system for an aircraft, the accumulator system comprising: a hydraulic accumulator haying a body; and a. temperature sensor arrangement that is configured to sense a temperature of the body of the hydraulic accumulator, wherein the temperature of the body is indicative of a. temperature of a gas in the hydraulic accumulator.
100681 Optionally, the hydraulic accumulator is an aircraft braking system hydraulic accumulator.
[0069] Optionally, the temperature sensor arrangement has any one or more of the features discussed above as being optional in the temperature sensor arrangement of the monitoring system of the first aspect or the aircraft system of the fourth aspect.
[0070] A sixth aspect of the present invention provides an aircraft comprising the monitoring system according to the first aspect, or the aircraft system according to the fourth aspect" or the accumulator system according, to the fifth aspect, or the non-transitory computer-readable storage meditnn according to the third aspect of-the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[00711 Embodiments of the invention will now be described, by way ofexample [0072] Figure 1 shows a schematic view of an L.xanlple of an aircraft system; [0073] Figure 2 shows a schematic view of an example of a hydraulic accumulator of the aircraft system according to Figure 1; [0074] Figure 3 is a flow diagram showing an example of a method of determining a characteristic of the hydraulic accumulator of Figure 2; [0075] Figure 4 shows a schematic diagram of an example of a non-transitory computer-readable storage medium; and 00761 Figure 5 is a schematic front Mew of an example of an aircraft.
DETAILED DESCRIPTION
[0077] Aircraft and aircraft systems are;acidly exposed to a range of temperatures, particularly but not exclusively during a flight of the aircraft. Such exposure may cause a variation in a gas temperature of gas in the hydraulic accumulator, which may affect a pressure of hydraulic fluid in the hydraulic system. 'This presents challenges in accurately determining an amount of fluid in the hydraulic system, or an energy stored in a hydraulic accumulator of the hydraulic system, for example. Examples described herein are concerned with providing improved systems that address tins issue.
100781 Figure 1 shows a schematic view of an aircraft system 10 according to an example. Broadly speaking, the aircraft system 10 comprises a monitoring system 100, a braking system 20 and a display 300. The monitoring system 100 comprises a controller 110, a temperature sensor arrangement 120, and a pressure sensor arrangement 130. The braking system 20 is for braking the wheels of at least one landing gear of an aircraft. The braking system 20 comprises a hydraulic system 200 communicatively coupled to the monitoring system 100. In other examples, the hydraulic system 200 may be any other hydraulic system of the aircraft, such as a hydraulic system for extending or retracting a 'landing gear of the aircraft, a hydraulic system for opening or closing a landing gear bay door of the aircraft, or a hydraulic system for operating control surfaces of the aircraft.
[0079] The controller 110 may take any suitable Rum. The controller 110 may comprise a processor, such as a microprocessor. Broadly speaking, the controller 110 is configured to determine a first gas temperature of a gas in the hydraulic accumulator, determine a first gas pressure of the gas in the hydraulic accumulator, and determine a characteristic of the hydraulic accumulator on the basis of the first gas temperature and the first gas pressure.
[0080] The hydraulic system 200 comprises hydraulic fluid and a hydraulic accumulator 210. In some examples, the hydraulic system 200 comprises any one or a combination of a valve; an actuator; a pump; a reservoir; a filter, and the like. The hydraulic system may comprise any other components typically found in a hydraulic system of an aircraft. the present example, the hydraulic accumulator 210 is configured to provide backup pressure to brakes of the aircraft braking system 20. In other examples, the hydraulic accumulator 210 is for storing, absorbing and/or releasing energy in any other hydraulic system of the aircraft, as noted above. In some examples, components of the hydraulic system 200, such a valve or an actuator, are operated electro-mechanically. Power may be supplied to the hydraulic system 200 from a power supply (not shown), such as an caginc-driven power supply, or an energy storage device, such as a battery.
[00811 Figure 2 snows a schematic diagram of the hydraulic accumulator 210. The hydraulic accumulator 210 is a sealed hydraulic accumulator 210 comprising a steel body 211. The body 211 may be made of any other suitable material, such as a ferrous material or non-ferrous material, in other examples. The hydraulic accumulator 210 comprises a piston 214 (although the piston 214 could be replaced by a bladder, diaphragm or other fluid separating device), with hydraulic fluid 213 on one side of the piston 214 and compressed gas 212 on the other side of the piston 214. The hydraulic accumulator 210 comprises a connector 215 (or port 215) for fluid connection ofthe one side of the piston 214 with a fluid line of the hydraulic system 200.
[0082] In the present example, the hydraulic accumulator 210 is prc-charged with a volume of gas 212 and sealed so that the gas cannot leak from the hydraulic accumulator 210. The hydraulic accumulator 210 may be sealed by welding at least apart of the body 211 of the hydraulic accumulator 210. In the present example, except for the connector 215, there are no connections or ports to the interior of the hydraulic accumulator 210. For instance, there arc no ports for refilling or replacing the gas 212 in the hydraulic accumulator 210, or for detecting certain characteristics of the hydraulic accumulator 210 such as a temperature of the gas 212 or a position of the piston 214. In this way, the present invention avoids the need for an intrusive sensor, such as a linear variable differential transformer (LIDVI), for sensing a position of the piston 214, for example. An intrusive sensor would require an opening to be provided in the body 211 for the sensor to pass through. The hydraulic fluid 213 and/or the gas 212 may escape through such an opening. By avoiding the need for an intrusive sensor, a risk of compromising the integrity of the hydraulic accumulator 210 may be reduced [0083] In the present example, the pressure sensor arrangement 130 comprises a single pressure sensor 130, which is connected to the connector 215. The pressure sensor 130 is configured to sense a fluid pressure in the hydraulic accumulator 210, which is indicative of a gas pressure of the gas 212 in the hydraulic accumulator 210. For example, the pressure sensor 130 is configured to sense a fluid pressure of the hydraulic fluid 213, which is indicative of the gas pressure of the gas 212. In some examples, there may be more than one pressure sensor 130, and each may be connected to a different part of the hydraulic system 200 [0084] In the present example, the temperature sensor arrangement 120 comprises a single temperature sensor 120, which is coupled to an outer surface of the hydraulic accumulator 210. The temperature sensor 120 is configured to sense a body temperature of the body 211 of the hydraulic accumulator 210, which is indicative of a gas temperature of the gas 212 in the hydraulic accumulator 210. hi the present example, the body 211 of the hydraulic accumulator 21.0 is made of steel, and the temperature sensor 120 is magnetically coupled to the body 211. In some examples, the body 211 is am other suitable ferrous material, and the temperature sensor 120 is magnetically coupled to the body 211. in other examples, the body 211 is made of any other suitable material, and comprises a. ferrous portion on an outer surface of the body 211, to which the temperature sensor 120 is magnetically coupled. In other examples, the temperature sensor 120 is othenvise mounted. or bonded to the surface of the hydraulic accumulator by any other suitable mechanism. In same examples, the temperature sensor 120 is removably coupled to the surface of the hydraulic accumulator 210. hi this way, the temperature sensor I 20 may be coupled to the hydraulic accumulator during a maintenance procedure, for instance when the aircraft is on the ground, and then removed, and optionally be reused later.
[0085] In some examples, emperature sensor arrangement 120 comprises more than one temperature sensor, each temperature sensor coupled to the surface of the hydraulic accumulator 210 as described above. In some examples, the temperature sensor arrangement 120 comprises an electrical temperature sensor, such as a thcrmistor, a resistance temperature detector, or a themmeouple, tar example. In other examples, the temperature sensor arrangement 120 comprises an infrared temperature sensor, such as an infrared camera, frar instance.
[0086] As noted above, the controller 110 is configured to determine a characteristic of the hydraulic accumulator on the basis of a gas temperature and a gas pressure. In the present example, the controller 110 is configured to determine the gas temperature and the gas pressure on the basis of a body temperature sensed by the temperature sensor arrangement 120 and a fluid pressure sensed by the pressure sensor arrangement 130, respectively. For example, the temperature sensor 120 and the pressure sensor J 30 may each be configured to send a respective signal to the controller, the respective signals comprising information representative of the body temperature and the fluid pressure. The controller 110 may then receive the respective signals and determine the gas temperature and the gas pressure on the basis of the respective signals.
[0087] In some examples, the characteristic of the hydraulic accumulator comprises one or both of a volume of fluid in the hydraulic accumulator 210 and an amount of energy stored in the hydraulic accumulator 210. In the present example, the volume of fluid in the hydraulic accumulator 210 is a volume of the gas 212 in the hydraulic accumulator 210. In some examples, the gas 212 may be an ideal gas, and the controller may determine the volume of the gas 212 using the ideal gas relationship, PV=RT, where P is the gas pressure of the gas 212. T is the gas temperature of the gas 212. V is the volume of the gas 212 and R is constant pertaining to the gas 212. In some examples, the volume of the gas 212 in the hydraulic accumulator 210 may be used to determine an amount of energy stored in the hydraulic accumulator 210.. for instance by the controller or an operator consulting a look-up table. In other examples, the controller may determine the amount of energy stored in the hydraulic accumulator 210 on the basis of the gas temperature and the gas pressure.
[0088] Determining the gas temperature and the gas pressure of the gas 212 in the hydraulic accumulator 210 may enable a more accurate determination of a volume of the gas 212 and/or an amount of energy stored in the hydraulic accumulator 210. For example, where an ambient temperature external to, and remote from, the hydraulic accumulator 210 is different to a temperature of the gas 212, a de-termination of a volume of fluid or an amount of energy stored in the hydraulic accumulator on the basis of the fluid pressure and the ambient temperature may be inaccurate.
[0089] in some examples, the controller 110 is configured to determine a first and a second gas temperature of the gas, determine a first and a second gas pressure of the gas 212, and determine a change or rate of change in the characteristic of the hydraulic accumulator 210 on the basis of the first and second gas temperatures and the first and second ins pressures. In some examples, the controller is configured to determine the first gas temperature and the first gas pressure at a first time, and to determine the second gas temperature and the second gas pressure at the second time. In this way, the change or rate of change in the characteristic of the hydraulic accumulator is over a period starting at the first time and ending at the second time, in some examples, the period has a length of up to one minute, more than one minute, more than ten minutes, or more than thirty minutes. In some examples, the change or rate of change in the characteristic of the hydraulic accumulator is a reduction or rate of reduction in the characteristic of the hydraulic accumulator.
[0090] In this way, since the temperature of a gas in a hydraulic accumulator is considered, examples of the present invention may provide a more accurate way of determining a volume of the gas 212, and/or WA amount of energy, stored in the hydraulic accumulator 210. Moreover, examples of the present invention may provide a more accurate way of determining a change or rate of change in a volume of the gas 212, and/or an amount of energy stored in the hydraulic accumulator 210. This may be, for example, to reduce a time taken to complete maintenance of the hydraulic system 200, for instance after a lauding of the aircraft. In such examples, the temperature of the gas 212 may be lower than an ambient temperature external to the hydraulic accumulator 210, or lower than a temperature of the hydraulic flu id 213, and so the gas 212 may be heating up.
Therefore, the second gas temperature may be higher than the first;as temperature, and the second gas pressure may be higher than the first gas pressure. If the hydraulic system 200 is leaking, a reduction in fluid pressure and amount of energy stored in the hydraulic accumulator 210 due to the leak may be masked by the increase in gas pressure, and therefore the leak may not be accurately detected. Determining the first and second gas temperatures and the first and second gas pressures enables the monitoring system 100 to accurately determine a change or rate of change in the volume of the gas 212 and/or an amount of energy stored in the hydraulic accumulator 210, thereby to improve the efficiency of a maintenance procedure, for example.
[00911 In the present example, the first and second gas temperatures are deterim ied on the basis of corresponding; first and second body temperatures of the body 211 of the hydraulic accumulator 210. Additionally, the first and second gas pressures are determined on the basis of corresponding first and second fluid pressure of fluid in the hydraulic accumulator 210. hi the present example, the temperature sensor arrangement 120 comprises a single temperature sensor 120, as described above, configured to sense the first and second body temperatures, and the pressure sensor arrangement 130 comprises a single pressure sensor 130, as described above, configured to sense the first and second pressures.
[0092] in sonic examples, the controller 110 is configured to perform an action on the basis of the characteristic or the change or rate of change of the characteristic of the hydraulic accumulator 210. In some examples, the action comprises one or both of outputting a signal comprising information representative of the characteristic; and causing issuance of a. warning.
[0093] The display' 300 is configured to display information relating to the hydraulic accumulator to a user or operator. The display may provide a visual indicator to the user or operator, such as maintenance crew or flight crew. in some examples, the controller is configured to output the signal comprising information representative of the characteristic to the display, and the display is configured to display information relating to the characteristic on the basis of the signal. For example, the display may be configured to display an indication of a volume of fluid or an amount of energy stored in the accumulator at any given time. In some examples, the signal is representative of the change or rate of change:31 the characteristic, and the display is configured to display information relating to the change or rate of change in the characteristic on the basis of the signal. For example, the display may be configured to display the change or rate of change in the volume of the gas 212 or the amount of energy stored in the hydraulic accumulator 210 over the period starting at the first time and ending at the second time.
[NM In some examples, the information representative of the characteristic is stored in data storage on the aircraft, and the data storage is accessible by a maintenance crew during maintenance of the aircraft. In other examples, the signal is sent wirelessly to a location remote from the aircraft so as to be viewed by maintenance crew or other operators remote from the aircraft.
100951 In sonic examples, the controller may cause issuance of a warning, for example by the display 300 or another warning device (not shown), to indicate that an energy in the system is below a predetermined threshold, for example, in other examples, the controller may cause issuance of the warning to indicate that a change or rate of change in energy in the hydraulic accumulator exceeds a predetemnned threshold, for example. The warning may be an audible warning such as a beep, ring or buzz, and/or a visual warning such as a flashing light or illuminated indicia, and/or a tactile warning such as a vibration.
[00961 Figure 3 is a flow diagram showing an example of a method 800 of determining a characteristic of a hydraulic accumulator of an aircraft. In some examples, the method 800 is performed by a controller of a monitoring system for monitoring the hydraulic accumulator of the aircraft, such as the monitoring system 100, so that the method is a method of operating a controller, such as the controller 110, to determine the characteristic of the hydraulic accumulator of the aircraft. The method 800 comprises: determining 810 a first gas temperature of a gas in the hydraulic accumulator; determining 820 a first gas pressure of the gas in the hydraulic accumulator; and determining 830 the characteristic of the hydraulic accumulator on the basis of the at least one first ga temperature and the at least one first gas pressure.
[0097] In some examples, the method comprises sensing 805 a first body temperature of a body of the hydraulic accumulator and determining 810 the first gas temperature on the basis of the first body temperature. In some examples, the method comprises sensing 815 a first fluid pressure of a fluid in the hydraulic accumulator and determining 820 the first gas pressure on the basis of the first fluid pressure.
[0098] In some examples, the method comprises determining 840 a second gas temperature of the gas, determining 850 a second gas e of the gas, and determining 855 a change or rate of change in the characteristic of the hydraulic accumulator, on the basis of the first and second gas temperatures and the first and second gas pressures. in some examples, the method comprises determining 810 the first gas temperature and determining 820 the first gas pressure at a first time, and determining 840 the second gas temperature and determining 850 the second gas pressure at a second time, wherein the change or rate of change is over a period starting at the first time and ending at the second time.
100991 In some examples, the method comprises sensing 835 a second body temperature of the body of the hydraulic accumulator and determining 840 the second gas temperature on the basis of the second body temperature. In some examples, the method comprises sensing 845 a second fluid pressure of the fluid in the hydraulic accumulator and detennining 850 the second gas pressure on the basis of the second fluid pressure.
101001 In some examples, the method comprises performing 860 an action on the basis of the characteristic or the change or rate of change of the characteristic of the hydraulic accumulator. in some examples, the performing 860 the action comprises one or both of: outputting a signal comprising information representative of the characteristic or the change or rate of change in the characteristic; and causing issuance of a warning, as described above with reference to Figure I in some examples, the method comprises outputting the signal comprising information representative of the characteristic to a.
display, and displaying information relating to the characteristic on the basis of the signal on the display, as described above with reference to Figure 1 [01011 In some examples, the method comprises pressurising 801 the hydraulic accumulator, and determining 810 the first gas temperature and determining 820 the first gas pressure a predetermined period of time after the pressurising 801 the hydraulic accumulator. In some examples, the predetermined period of time is up to I minute, up to 5 minutes, up to 10 minutes, or up to 30 minutes after the pressurising 801 the hydraulic accumulator. Inthis way, the body of the hydraulic accumulator may have time to adjust to a temperature indicative of the gas temperature of the gas in the hydraulic accumulator.
[0102] Figure 4 shows a schematic diagram of a non-transitory computer-readable storage medium 900 according to an example. The non--transitory computer-readable storage medium 900 stores instructions 930 that, if executed by a processor 920 of a controller 910 of an aircraft, cause the processor 920 to perform one of the methods described herein. In some examples, the controller 910 is the controller 110 described above with reference to Figure 1 or a variant thereof described herein_ The instructions 930 comprise: determining a first gas temperature of a gas M the hydraulic accumulator; determining a first gas pressure of the gas in the hydraulic accumulator; and determining a characteristic of the hydraulic accumulator on the basis of the at least one first gas temperature and the at least one first gas pressure. The instructions 930 may comprise instructions to perform any of the methods 800 described above with reference to Figure [0103] Figure 5 is a schematic front view of an aircraft 1. The aircraft I comprises an aircraft system 10 as discussed herein, such as the aircraft system 10 discussed herein with reference to Figure I or any variant thereof discussed herein. The aircraft 1 also comprises a hydraulic system 200 as discussed herein, such as the hydraulic system 200 discussed herein with reference to Figure 1 or any variant thereof discussed herein The aircraft 1 also comprises the non-transitory computer-readable storage medium 900 discussed herein with reference to Figure 4.
[0104] Examples of the invention address the issue of reliably determining a characteristic of a hydraulic accumulator, such as volume of gas or an amount of enemy stored in the hydraulic accumulator, on the basis of a gas temperature and gas pressure in the hydraulic accumulator, particularly when it is not possible to sense the gas temperature directly. Determining the gas temperature, for example on the basis of a body temperature of a body of the hydraulic accumulator, enables the accurate determination of the characteristic regardless of variations in ambient temperature external to the hydraulic accumulator, for example.
[0105] It is to he noted that the term "or' as used herein is to be interpreted to meai "and/or", unless expressly stated otherwise.
[0106] Although the invention has been described above with reference to particular examples, it will be appreciated that various changes or modification may be made without departing from the scope of the invention as defined by the appended claims. S:

Claims (16)

  1. A monitoring system for monitoring a hydraulic accumulator of an aircraft,, the monitoring system comprising a controller that is configured to: determine a first gas temperature of a gas in the hydraulic accumulator; determine a first gas pressure of the gas in the hydraulic accumulator; and determine a characteristic of-the hydraulic accumulator on the basis of the first gas temperature and the first gas pressure.
  2. The monitoring system according to claim I, wherein the controller is configured to: determine a second gas temperature of the gas; determine a second gas pressure of the gas; and determine a change or rate of change in the characteristic of the hydraulic accumulator, on the basis of the first and second gas temperatures and the first and second gas pressures.
  3. Tie monitoring system according to either claim 1 or claim 2. wherein the characteristic of the hydraulic accumulator comprises one or both of a volume of fluid in the hydraulic accumulator and an amount of energy stored in the hydraulic accumulator.
  4. Fhe monitoring system according to any one of the preceding claims, wherein the controller is configured to perform an action on the basis of the characteristic of the hydraulic accumulator, wherein, the action to be performed comprises one or both of outputting a signal comprising infimmation representative of the characteristic; and causing issuance of a warning.
  5. The monitoring system according to any one of the preceding claims, comprising a. temperature sensor arrangement configured to sense a first body temperature of a body of the hydraulic accumulator, wherein the first body temperature is 'indicative of the first gas temperature.
  6. The monito 0. system according to claim 5, wherein the controller is configured to determin first gas temperature on the basis of the first body temperature.
  7. The monitoring system accordi o either claim claim 6, wherein at least a part of the temperature sensor arrangement is coupled to a surface of the hydraulic accumulator.
  8. The monnonng system according to claim 7, wherein the temperature sensor arrangement is removably coupled to the surface of the hydraulic accumulator.
  9. The monitoring system according to any one of the preceding claims, wherein the hydraulic accumulator is an aircraft braking system hydraulic accumulator.
  10. M. A method ofdetermining acharacteristic of a hydrauhc accumulator of an aircraft.the method comprising: determining a first gas temperature of ag s in the hydraulic accumulator; determining a first gas pressure of the gas in th ydraulic accumulator; and determining the characteristic of the hydraulic accumulator on the basis of the first gas temperature and the first gas pressure.
  11. I I. The method according to claim 10, further comprising sensing a. first body temperature of a body of the hydraulic accumulator and determining the first ga.s temperature on the basis of the first body temperature.
  12. 12. The method according to either claim 10 or claim II, further comprising pressurising the hydraulic accumulator, and determining the first gas temperature and the first gas pressure a predetermined period of time after the pressurising the hydraulic accumulator. 2?
  13. 13. A non-transitory computer-readable storage medium storing instruiftions that, if executed by a controller of a monitoring system of an aircraft., cause the controller to carry out the method according to any one of claims 10 to 12.
  14. 14. An aircraft system for an aircraft, the aircraft system comprising: a braking system that is configured to brake a landing gear of the aircrafl the braking system comprising a hydraulic accumulator; and a monitoring system comprising a temperature sensor arrangement configured to sense a body temperature of a body of the hydraulic accumulator, a pressure sensor arrangement configured to sense a fluid pressure of fluid in the hydraulic accumulator, and a controller that is configured to: determine a gas temperature of a gas in the hydraulic accumulator, on the basis of the body tempera:nue; determine a gas pressure of the gas in the hydraulic accumulator, on the basis of the fluid pressure, and determine a characteristic of the hydraulic accumulator on the basis of the gas temperature and the gas pressure.
  15. 15. An accumulator system for an aircraft, the accumulator system comprising: a hydraulic accumulator haying a. body; and a temperature sensor arrangement that is configured to sense a temperature of the body of the hydraulic accumulator, wherein the temperature of the body is indicative of a temperature of a. gas in the hydraulic accumulator,
  16. 16. An aircraft comprising die monitoring system according to any one of claims 1 to 9 or the aircraft system according to claim 14 or the accumulator system according to claim 15 or the non-transitory computer-readable storage medium according to claim 13
GB1915218.0A 2019-10-21 2019-10-21 Monitoring system for aircraft Pending GB2588597A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1915218.0A GB2588597A (en) 2019-10-21 2019-10-21 Monitoring system for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1915218.0A GB2588597A (en) 2019-10-21 2019-10-21 Monitoring system for aircraft

Publications (2)

Publication Number Publication Date
GB201915218D0 GB201915218D0 (en) 2019-12-04
GB2588597A true GB2588597A (en) 2021-05-05

Family

ID=68728379

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1915218.0A Pending GB2588597A (en) 2019-10-21 2019-10-21 Monitoring system for aircraft

Country Status (1)

Country Link
GB (1) GB2588597A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4092276A1 (en) * 2021-05-21 2022-11-23 Roth Hydraulics GmbH Method for monitoring the state of a hydraulic storage device and hydraulic storage device
US20240002041A1 (en) * 2021-10-15 2024-01-04 Jetzero, Inc. Systems and methods for controlling landing gear of an aircraft

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10192954B4 (en) * 2000-07-21 2007-12-27 Firma Hans Heynen Method and device for measuring the gas pressure in gas spring or gas storage balls
US20130291952A1 (en) * 2012-05-07 2013-11-07 Caterpillar, Inc. System and Method to Detect Accumulator Loss of Precharge
US20170213400A1 (en) * 2014-07-24 2017-07-27 Goodrich Corporation Pitch trim actuator servicing monitoring system and method
US20180209451A1 (en) * 2015-06-18 2018-07-26 Sikorsky Aircraft Corporation Systems and methods for maintaining hydraulic accumulators
US20190106095A1 (en) * 2017-10-05 2019-04-11 Goodrich Corporation Brake control system channel protection

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10192954B4 (en) * 2000-07-21 2007-12-27 Firma Hans Heynen Method and device for measuring the gas pressure in gas spring or gas storage balls
US20130291952A1 (en) * 2012-05-07 2013-11-07 Caterpillar, Inc. System and Method to Detect Accumulator Loss of Precharge
US20170213400A1 (en) * 2014-07-24 2017-07-27 Goodrich Corporation Pitch trim actuator servicing monitoring system and method
US20180209451A1 (en) * 2015-06-18 2018-07-26 Sikorsky Aircraft Corporation Systems and methods for maintaining hydraulic accumulators
US20190106095A1 (en) * 2017-10-05 2019-04-11 Goodrich Corporation Brake control system channel protection

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4092276A1 (en) * 2021-05-21 2022-11-23 Roth Hydraulics GmbH Method for monitoring the state of a hydraulic storage device and hydraulic storage device
US20240002041A1 (en) * 2021-10-15 2024-01-04 Jetzero, Inc. Systems and methods for controlling landing gear of an aircraft

Also Published As

Publication number Publication date
GB201915218D0 (en) 2019-12-04

Similar Documents

Publication Publication Date Title
EP2097303B1 (en) Freight car event recorder
US9469319B2 (en) On-board brake system diagnostic and reporting system
GB2588597A (en) Monitoring system for aircraft
AU645717B2 (en) Adaptive air brake control system
US8661875B2 (en) System and method to detect accumulator loss of precharge
EP3693235B1 (en) Determining integrity of braking control system
AU2010200385B2 (en) System and method for control of distributed power rail vehicle
US9267403B2 (en) Device for monitoring the sealing of a rotorcraft transmission box by suction
RU2671803C2 (en) Vehicle brake management device
CN104514771A (en) Hydraulic accumulator pre-charge pressure detection for hydraulic braking system
US11345466B2 (en) Controller for an aircraft braking system
US10843676B2 (en) Compressed-air brake assembly for a rail vehicle
AU724203B2 (en) Modified airflow algorithm with compensation for variations in main reservoir air pressure and ambient airflow
DE102009001357A1 (en) Method for operating a hydraulic hybrid vehicle
CA2984423C (en) Train brake safety monitoring and fault action system
GB2588596A (en) Control system for aircraft
US20220169224A1 (en) Hydropneumatic valve having a mechatronic module
RU2391234C2 (en) Method of testing car braking system
GB2546790A (en) Hydraulic accumulator monitoring system