Rotor track and balance with improved linear optimization
A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value.
1. A method for reducing vibrations in an airframe of an aircraft, comprising:
determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe;
determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value;
receiving, with the processor, information indicative of a flight response to the initial adjustment solution;
combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response;
determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and
determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value comprising (i) determining an initial control adjustment matrix in response to the determining of the initial adjustment solution and (ii) determining a measured vibration matrix from the initial control adjustment matrix.
2. The method of claim 1 , further comprising updating the measured vibration matrix to form an updated vibration matrix.
3. The method of claim 2 , wherein the updating of the measured vibration matrix further comprises:
calculating a weighted least squares on the initial control adjustment matrix.
4. The method of claim 1 , wherein the determining of the predicted adjustment solution further comprises:
determining predicted vibration values for an adjustment to a pitch control rod, a trim tab, a hub weight, or combinations thereof.
5. The method of claim 1 , wherein the determining of the predicted adjustment solution further comprises:
determining a performance value for the predicted adjustment solution.
6. The method of claim 5 , wherein the determining of the performance value further comprises:
determining a value indicative of a difference between an estimated vibration measurement and the desired vibration level.
7. The method of claim 1 , wherein the determining of the predicted adjustment solution further comprises:
receiving signals from multiple sensors coupled to the airframe, the received signals being indicative of harmonic vibration measurements for one per rev vibration, two per rev vibrations, three per rev vibrations, or combinations thereof.
8. The method of claim 1 , wherein the determining of the predicted adjustment solution further comprises:
updating the initial control adjustment matrix to form an updated control adjustment matrix.
9. A system for reducing vibrations in an airframe of an aircraft, comprising:
rotors, each rotor comprising a plurality of blades, wherein each of the plurality of blades is associated with a sensor;
a processor; and
memory having instructions stored thereon that, when executed by the processor, cause the system to:
determine, with the processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe;
determine, with the processor, an initial adjustment solution for the aircraft in response to the receiving of the information on the initial error value;
receive, with the processor, information indicative of a flight response to the initial adjustment solution;
combine, with the processor, disturbance signals indicative of vibration noise with the flight response information;
determine, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and
determine, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value,
wherein the processor is configured to determine an initial control adjustment matrix in response to the determining of the initial adjustment solution, and
wherein the processor is configured to determine a measured vibration matrix from the initial control adjustment matrix.
10. The system of claim 9 , wherein the processor is configured to update the measured vibration matrix to form an updated vibration matrix.
11. The system of claim 10 , wherein the processor is configured to calculate a weighted least squares on the initial control adjustment matrix.
12. The system of claim 9 , wherein the processor is configured to predict vibration values for an adjustment to a pitch control rod, a trim tab, a hub weight, or combinations thereof.
13. The system of claim 9 , wherein the processor is configured to determine a performance value for the predicted adjustment solution.
14. The system of claim 13 , wherein the processor is configured to determine a value indicative of a difference between an estimated vibration measurement and the desired vibration level.
15. The system of claim 9 , wherein the processor is configured to receive signals from multiple sensors coupled to the airframe, the received signals being indicative of harmonic vibration measurements for one per rev vibration, two per rev vibrations, three per rev vibrations, or combinations thereof.
16. The system of claim 9 , wherein the processor is configured to update the initial control adjustment matrix to form an updated control adjustment matrix.
17. A method for reducing vibrations in an airframe of an aircraft, comprising:
determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe;
determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value;
receiving, with the processor, information indicative of a flight response to the initial adjustment solution;
combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response;
determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and
determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value comprising (i) determining a performance value for the predicted adjustment solution and (ii) determining a value indicative of a difference between an estimated vibration measurement and the desired vibration level.