1#ifndef FLIGHT_STATE_MACHINE_H
2#define FLIGHT_STATE_MACHINE_H
Detects the apogee (peak altitude) of a rocket flight using estimated altitude and vertical velocity.
Abstract interface for flight state machines driven by IMU/altimeter data.
Timestamped float measurement container.
Abstract interface for persisting timestamped data points.
Sliding-window launch detector based on acceleration magnitude.
StateMachine(IDataSaver *dataSaver, LaunchDetector *launchDetector, ApogeeDetector *apogeeDetector, VerticalVelocityEstimator *verticalVelocityEstimator)
Wire dependencies for the state machine.
uint8_t getState() const override
Retrieve the current state value.
int update(const AccelerationTriplet &accel, const DataPoint &alt) override
Process new sensor data and transition states if thresholds are met.
1D Kalman filter fusing altimeter and accelerometer data.