# US 12,113,401 B2 · Method and system for activating an electric machine in an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,113,401 B2 - Document ID: US12113401B2 - Status: Granted - Kind: B2 - Application number: 17/674,660 - Filed: 2022-02-17 - Published: 2023-08-17 - Granted: 2024-10-08 - Earliest claimed: 2022-02-17 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Frederic Lacaux; Kamiar J. Karimi; Eugene V. Solodovnik; Vyacheslav Khozikov - Web page: https://patentgrep.com/patent/US12113401B2 ## CPC - H02K 5/225: {Terminal boxes or connection arrangements (specially adapted for submersible motors H02K5/132)} - H02K 11/20: for measuring, monitoring, testing, protecting or switching (rectifiers H02K11/04; power electronics H02K11/33) - B64D 47/00: Equipment not otherwise provided for - H02K 11/33: Drive circuits, e.g. power electronics (H02K11/38 takes precedence) - H02P 27/08: with pulse width modulation - H02P 29/024: Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load - B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration} - B64D 2221/00: Electric power distribution systems onboard aircraft - H02K: DYNAMO-ELECTRIC MACHINES (dynamo-electric relays H01H53/00; conversion of DC or AC input power into surge output power {H03K3/53}) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - H02P: CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS ## Abstract A discrete signal interlock system for activating an electric machine in an aircraft includes a first controller, a second controller, and a power source coupled via a single wiring harness bundle to a motor controller that is operatively connected to the electric machine. The motor controller includes a first circuit that is electrically coupled to a driver enabler of the motor controller, and a second circuit that is electrically coupled to a driver of the motor controller. The single wiring harness bundle encloses a first signal cable electrically coupling the first controller to the first circuit, a second signal cable electrically coupling the second controller to the second circuit, a first power cable electrically coupled to the first circuit, and a second power cable electrically coupled to the second circuit. Activation of the motor controller requires activation of the driver in concert with activation of the driver enabler. ## Claims ### Claim 1 A discrete signal interlock system for controlling an electric machine in an aircraft, comprising: a first controller, a second controller, a power source, a single wiring harness bundle, and a motor controller, wherein the power source is coupled via the single wiring harness bundle to the motor controller that is operatively connected to the electric machine; wherein the motor controller includes a first circuit electrically coupled to a driver enabler of the motor controller and a second circuit electrically coupled to a driver of the motor controller; wherein the driver enabler and the driver act in concert to operate the motor controller to control the electric machine; wherein the single wiring harness bundle encloses a first signal cable electrically coupling the first controller to the first circuit, a second signal cable electrically coupling the second controller to the second circuit, a first power cable electrically coupled to the first circuit, and a second power cable electrically coupled to the second circuit; wherein activation of the first circuit requires a first signal being transmitted from the first controller to the first circuit via the first signal cable; wherein activation of the second circuit requires a second signal being transmitted from the second controller to the second circuit via the second signal cable; and wherein activation of the motor controller requires activation of the driver in concert with activation of the driver enabler. ### Claim 2 (depends on 1) The discrete signal interlock system of claim 1, wherein the first signal comprises a constant active voltage signal; and wherein the second signal comprises a pulsewidth modulated signal. ### Claim 3 (depends on 2) The discrete signal interlock system of claim 2, the pulsewidth modulated signal of the second signal has a duty cycle that is greater than 40%. ### Claim 4 (depends on 2) The discrete signal interlock system of claim 2, wherein the pulsewidth modulated signal of the second signal includes a first duty cycle that commands the motor controller to control the electric machine at a fast motion, and a second duty cycle that commands the motor controller to control the electric machine at a slow motion. ### Claim 5 (depends on 1) The discrete signal interlock system of claim 1, wherein the first signal comprises a first pulsewidth modulated signal; and wherein the second signal comprises a second pulsewidth modulated signal. ### Claim 6 (depends on 5) The discrete signal interlock system of claim 5, wherein the first pulsewidth modulated signal is out of phase with the second pulsewidth modulated signal. ### Claim 7 (depends on 1) The discrete signal interlock system of claim 1, wherein the first signal and the second signal comprise high-impedance active DC signals. ### Claim 8 (depends on 1) The discrete signal interlock system of claim 1, wherein a fault in the wiring harness bundle disables activation of the motor controller by deactivating one of the driver or the driver enabler. ### Claim 9 A discrete signal interlock system for controlling an electric machine in an aircraft, comprising: a first controller and a first power source coupled via a first wiring harness bundle to an input power relay switch that is interposed between an AC power source and a motor controller that is operatively connected to the electric machine; and a second controller and a second power source coupled via a second wiring harness bundle to a second circuit operatively connected to the motor controller that is operatively connected to the electric machine; wherein the input power relay switch and the second circuit act in concert to operate the motor controller to control the electric machine; wherein the first wiring harness bundle includes a first signal cable electrically coupling the first controller to the input power relay switch, and a first power cable electrically coupled to the input power relay switch; wherein the second wiring harness bundle encloses a second signal cable electrically coupling the second controller to the second circuit, and a second power cable electrically coupled to the second circuit; wherein activation of the input power relay switch requires a first signal being transmitted from the first controller to the input power relay switch via the first signal cable; wherein activation of the second circuit requires a second signal being transmitted from the second controller to the second circuit via the second signal cable; and wherein activation of the motor controller requires activation of the input power relay switch and activation of the second circuit. ### Claim 10 (depends on 9) The discrete signal interlock system of claim 9, wherein the first signal comprises a constant active voltage signal; and wherein the second signal comprises a pulsewidth modulated signal. ### Claim 11 (depends on 10) The discrete signal interlock system of claim 10, wherein the pulsewidth modulated signal of the second signal has a duty cycle that is greater than 40%. ### Claim 12 (depends on 10) The discrete signal interlock system of claim 10, wherein the pulsewidth modulated signal of the second signal includes a first duty cycle that commands the motor controller to control the electric machine at a fast motion, and a second duty cycle that commands the motor controller to control the electric machine at a slow motion. ### Claim 13 (depends on 9) The discrete signal interlock system of claim 9, wherein the first signal comprises a first pulsewidth modulated signal; and wherein the second signal comprises a second pulsewidth modulated signal. ### Claim 14 (depends on 13) The discrete signal interlock system of claim 13, wherein the first pulsewidth modulated signal is out of phase with the second pulsewidth modulated signal. ### Claim 15 (depends on 9) The discrete signal interlock system of claim 9, wherein a fault in the wiring harness bundle deactivates one of the input power relay switch or the second circuit to disable activation of the motor controller. ### Claim 16 An aircraft, comprising, comprising: a moveable surface operatively controlled by an electric machine; and a discrete signal interlock system arranged to control the electric machine; wherein the discrete signal interlock system includes: a first controller, a second controller, and a power source coupled via a single wiring harness bundle to a motor controller that is operatively connected to the electric machine; wherein the motor controller includes a first circuit electrically coupled to a driver enabler of the motor controller and a second circuit electrically coupled to a driver of the motor controller; wherein the driver enabler and the driver act in concert to operate the motor controller to control the electric machine to move the moveable surface; wherein the single wiring harness bundle encloses a first signal cable electrically coupling the first controller to the first circuit, a second signal cable electrically coupling the second controller to the second circuit, a first power cable electrically coupled to the first circuit, and a second power cable electrically coupled to the second circuit; wherein activation of the first circuit requires a first signal being transmitted from the first controller to the first circuit via the first signal cable; wherein activation of the second circuit requires a second signal being transmitted from the second controller to the second circuit via the second signal cable; and wherein activation of the motor controller requires activation of the driver in concert with activation of the driver enabler. ### Claim 17 (depends on 16) The aircraft of claim 16, wherein the first signal comprises a constant active voltage signal; and wherein the second signal comprises a pulsewidth modulated signal. ### Claim 18 (depends on 16) The aircraft of claim 16, wherein the first signal comprises a first pulsewidth modulated signal; and wherein the second signal comprises a second pulsewidth modulated signal. ### Claim 19 (depends on 18) The aircraft of claim 18, wherein the second pulsewidth modulated signal of the second signal includes a first duty cycle that commands the motor controller to control the electric machine to move the moveable surface at a fast motion, and a second duty cycle that commands the motor controller to control the electric machine to move the moveable surface at a slow motion. ### Claim 20 (depends on 16) The aircraft of claim 16, wherein the moveable surface comprises one of a flap, an aileron, an elevator, or a stabilizer, and wherein occurrence of a fault in the wiring harness bundle deactivates one of the driver or the driver enabler to prevent inadvertent movement of the moveable surface.