An Incorrect Force Mitigation System (IFMS) capable of detecting and mitigating incorrect forces applied to a structure of an aircraft, the IFMS having at least an Active Vibration Control system and a Structural Health Monitoring system for structural health monitoring and protection of an aircraft structure, the IFMS comprising: the AVC system, comprising: at least one force generator; at least one sensor configured to generate a signal upon detecting a structural vibration; a controller in electronic communication with each of the at least one FG and the at least one sensor, wherein the controller is configured to receive the signal, generate at least one force command, and electronically communicate the at least one force command to the at least one FG, the electronic communication providing for cancelling the structural vibration; the IFMS characterized by: a Structural Health Monitoring system comprising at least one structural health sensor configured to measure a structural load, a strain, or a vibration of the aircraft structure and a SHM controller, wherein the at least one structural health sensor is separate from the at least one sensor of the AVC system; a communication interface disposed between the AVC system and the SHM system for facilitating bi-directional electronic communications therebetween; and wherein the controller is configured to process information communicated from the AVC system and the SHM system, correlate the structural vibration detected by the at least one sensor of the AVC system with the structural load, strain, or the vibration communicated from the SHM system to the AVC system, and adjust force commands generated at the controller for mitigating incorrect force generation, thereby mitigating an incorrect force applied to the aircraft structure by the at least one force generator. the AVC system, comprising: at least one force generator; at least one sensor configured to generate a signal upon detecting a structural vibration; a controller in electronic communication with each of the at least one FG and the at least one sensor, wherein the controller is configured to receive the signal, generate at least one force command, and electronically communicate the at least one force command to the at least one FG, the electronic communication providing for cancelling the structural vibration; at least one force generator; at least one sensor configured to generate a signal upon detecting a structural vibration; a controller in electronic communication with each of the at least one FG and the at least one sensor, wherein the controller is configured to receive the signal, generate at least one force command, and electronically communicate the at least one force command to the at least one FG, the electronic communication providing for cancelling the structural vibration; the IFMS characterized by: a Structural Health Monitoring system comprising at least one structural health sensor configured to measure a structural load, a strain, or a vibration of the aircraft structure and a SHM controller, wherein the at least one structural health sensor is separate from the at least one sensor of the AVC system; a communication interface disposed between the AVC system and the SHM system for facilitating bi-directional electronic communications therebetween; and wherein the controller is configured to process information communicated from the AVC system and the SHM system, correlate the structural vibration detected by the at least one sensor of the AVC system with the structural load, strain, or the vibration communicated from the SHM system to the AVC system, and adjust force commands generated at the controller for mitigating incorrect force generation, thereby mitigating an incorrect force applied to the aircraft structure by the at least one force generator. a Structural Health Monitoring system comprising at least one structural health sensor configured to measure a structural load, a strain, or a vibration of the aircraft structure and a SHM controller, wherein the at least one structural health sensor is separate from the at least one sensor of the AVC system; a communication interface disposed between the AVC system and the SHM system for facilitating bi-directional electronic communications therebetween; and wherein the controller is configured to process information communicated from the AVC system and the SHM system, correlate the structural vibration detected by the at least one sensor of the AVC system with the structural load, strain, or the vibration communicated from the SHM system to the AVC system, and adjust force commands generated at the controller for mitigating incorrect force generation, thereby mitigating an incorrect force applied to the aircraft structure by the at least one force generator.