# US 2010/0164754 A1 · System comprising two combined instruments mounted on board an aircraft and method implementing the system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2010/0164754 A1 - Document ID: US20100164754A1 - Status: Published application - Kind: A1 - Application number: 12/376,422 - Filed: 2007-07-18 - Published: 2010-07-01 - Earliest claimed: 2006-08-04 - Assignees: Thales - Inventors: Philippe Chesne; Yves Jaulain - Web page: https://patentgrep.com/patent/US20100164754A1 ## CPC - G01C 23/005: {Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32)} - G01C: MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY (measuring liquid level G01F; radio navigation, determining distance or velocity by use of propagation effects, e.g. Doppler effects, propagation time, of radio waves, analogous arrangements using other waves G01S) ## Abstract The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics. ## Claims ### Claim 1 A system comprising: two integrated electronics instruments mounted onboard an aircraft; a communication link between the two integrated electronics instruments, each integrated electronics instrument comprising: one or more inertial sensors to sense flight parameters, wherein said flight parameters include at least one of speed, altitude and attitude parameters; one or more anemobarometric sensors to sense said flight parameters; and one or more displays displaying either flight parameters or navigation parameters of the aircraft; and said system further comprising one or more selection modules in communication with one or more of the inertial sensors or the anemobarometric sensors, for choosing, from the inertial sensors or the anemobarometric sensors of the two integrated electronics instruments, one or more sensors for determining the flight parameters. ### Claim 2 (depends on 1) The system as claimed in claim 1, wherein the two integrated electronics instruments are substantially identical and wherein each integrated electronics instrument further comprises said selection module. ### Claim 3 (depends on 1) The system as claimed in claim 1, wherein each integrated electronics instrument comprises an apparatus to adjust the barometric pressure, and wherein the system includes an apparatus to provide the adjusted barometric pressure from one of the integrated electronics instruments to the other integrated electronics instrument, in order to provide the last adjustment made to barometric pressure. ### Claim 4 A method of determining flight parameters of an aircraft on a system, the system comprising: two integrated electronics instruments mounted onboard an aircraft; a communication link between the two integrated electronics instruments, each integrated electronics instrument comprising: one or more inertial sensors to sense flight parameters, wherein said flight parameters include at least one of flight, speed, altitude and attitude parameters; one or more anemobarometric sensors to sense said flight parameters; and one or more displays displaying either flight parameters or navigation parameters of the aircraft, wherein the method comprises the steps of: selecting from the inertial sensors or the anemobarometric sensors of the two integrated electronics instruments, one or more sensors to determine the flight parameters according to their availability, to produce determined flight parameters; and displaying the determined flight parameters on the display of any one or both of the integrated electronics instruments. ### Claim 5 (depends on 4) The method as claimed in claim 4, wherein, when equivalent sensors are available on the two integrated electronics instruments, the selecting step selects the sensors of a predetermined integrated electronics instrument. ### Claim 6 (depends on 4) The method as claimed in claim 4, further comprising the step of selecting a sensor of one integrated electronics instrument upon a failure of an equivalent sensor of the other integrated electronics instrument. ### Claim 7 (depends on 4) The method as claimed in claim 4, further comprising the step of enabling display of flight parameters on the display of one integrated electronics instrument, regardless of the sensors that are selected, upon a failure of a display of the other integrated electronics instrument. ### Claim 8 (depends on 2) The system as claimed in claim 2, wherein each integrated electronics instrument comprises an apparatus to adjust the barometric pressure, and wherein the system includes an apparatus to provide the adjusted barometric pressure from one of the integrated electronics instruments to the other integrated electronics instrument, in order to provide the last adjustment made to barometric pressure. ### Claim 9 (depends on 5) The method as claimed in claim 5, further comprising the step of selecting a sensor of one integrated electronics instrument upon a failure of an equivalent sensor of the other integrated electronics instrument. ### Claim 10 (depends on 6) The method as claimed in claim 6, further comprising the step of enabling display of flight parameters on the display of one integrated electronics instrument, regardless of the sensors that are selected, upon a failure of a display of the other integrated electronics instrument.