# US 9,038,458 B2 · Monitoring device for repair patches, repair kit, and method for monitoring a repair patch > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,458 B2 - Document ID: US9038458B2 - Status: Granted - Kind: B2 - Application number: 13/811,635 - Filed: 2011-07-14 - Published: 2013-08-01 - Granted: 2015-05-26 - Earliest claimed: 2010-07-23 - Assignees: EADS Deutschland GmbH - Applicants: Thomas Becker; Ulrich Prechtel; Jirka Klaue; Martin Kluge; Jordi Sabater; Josef Schalk - Inventors: Thomas Becker; Ulrich Prechtel; Jirka Klaue; Martin Kluge; Jordi Sabater; Josef Schalk - Web page: https://patentgrep.com/patent/US9038458B2 ## CPC - G01M 17/00: Testing of vehicles (testing fluid tightness G01M3/00; testing elastic properties of bodies or chassis, e.g. torsion-testing, G01M5/00; testing alignment of vehicle headlight devices G01M11/06; testing of engines G01M15/00) - B29C 73/10: using patches sealing on the surface of the article (B29C73/14 takes precedence) - B64D 43/00: Arrangements or adaptations of instruments - B64F 5/40: Maintaining or repairing aircraft - B64F 5/60: Testing or inspecting aircraft components or systems - G01M 5/0041: {by determining deflection or stress} - B64C 2001/0072: {from composite materials} - B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration} - Y02T 50/40: Weight reduction - G01M: TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A monitoring device for a repair patch that can be placed on or in a wall of an aircraft to repair a defect has a sensor device for detecting properties of the repair patch placed in the wall, an energy supply device for supplying energy at least to the sensor device, and a communication device so as to read out the sensor data. A repair kit that can be placed in or on a wall of an aircraft to repair defects comprises a repair patch for repairing a defect in or on a wall of an aircraft and also comprises a monitoring device. A method for monitoring a repair patch in or on a wall of an aircraft by means of a monitoring device comprises the steps of detecting a measurement phase on the basis of the amount of energy provided by the energy supply device, measuring load parameters in and/or on the repair patch during the measurement phase, and reading out the load parameters. ## Claims ### Claim 1 A monitoring device for a repair patch configured for placement on or in a wall of an aircraft to repair a defect, the monitoring device comprising: a sensor that is disposed in contact with or adjacent to the repair patch, the sensor being configured to detect properties of the repair patch that is placed on or in the wall and provide sensor data; an energy supply device configured to supply energy at least to the sensor device; a communication device configured to read out the sensor data; and a data processing device configured to monitor the energy output of the energy supply device to identify a predetermined flight phase of the aircraft based on the energy output and to perform a measurement operation during which the data processing device records the sensor data during the predetermined flight phase. ### Claim 2 (depends on 1) The monitoring device as claimed in claim 1, wherein the energy supply device includes a thermoelectric generator. ### Claim 3 (depends on 2) The monitoring device as claimed in claim 2, wherein the thermoelectric generator includes a heat storage device. ### Claim 4 (depends on 1) The monitoring device as claimed in claim 1, further comprising a data storage device configured to store the sensor data. ### Claim 5 (depends on 1) The monitoring device as claimed in claim 1, wherein the communication device is configured for wireless communication. ### Claim 6 (depends on 1) The monitoring device as claimed in claim 1, wherein the data processing device is configured to process the sensor data. ### Claim 7 (depends on 6) The monitoring device as claimed in claim 6, wherein the data processing device is configured to process the sensor data by compressing the sensor data for storage in a data storage device. ### Claim 8 (depends on 1) The monitoring device as claimed claim 1, wherein the sensor device is configured to ascertain a mechanical stress as one of the properties. ### Claim 9 (depends on 1) The monitoring device as claimed in claim 1, wherein the communication device is supplied via an external energy source. ### Claim 10 (depends on 1) The monitoring device as claimed in claim 1, wherein the wall is an outer wall of the aircraft and the sensor device is configured to detect the properties of the repair patch placed on or in the outer wall. ### Claim 11 (depends on 1) A repair kit comprising the repair patch and the monitoring device as claimed in claim 1. ### Claim 12 (depends on 1) A method for monitoring a repair patch in or on a wall of an aircraft by using a monitoring device as claimed in claim 1, the method comprising: detecting a measurement phase on the basis of the amount of energy provided by the energy supply device; measuring load parameters at least one of in and on the repair patch during the measurement phase; and reading out the load parameters. ### Claim 13 (depends on 12) The method as claimed in claim 12, wherein the measurement phase is present during a flight phase during which the aircraft reaches a cruising altitude. ### Claim 14 (depends on 12) The method as claimed in claim 12, further comprising storing the measured load parameters initially in a data storage device for reading out during a reading out operation at a later time. ### Claim 15 (depends on 2) The monitoring device as claimed in claim 2, further comprising a data storage device configured to store the sensor data. ### Claim 16 (depends on 2) The monitoring device as claimed in claim 2, wherein the communication device is configured for wireless communication. ### Claim 17 (depends on 2) The monitoring device as claimed in claim 2, wherein the data processing device is configured to process the sensor data. ### Claim 18 (depends on 2) The monitoring device as claimed in claim 2, wherein the sensor device is configured to ascertain a mechanical stress as one of the properties. ### Claim 19 (depends on 1) The monitoring device as claimed in claim 1, wherein the data processing device is configured to refrain from recording the sensor data during a flight phase of the aircraft other than the predetermined flight phase.