Aircraft attitude control

Zolotukhin, Yu. N.; Nesterov, A. A.

doi:10.3103/s8756699015050040

Cited by 8 publications

(3 citation statements)

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“…The analysis in [2] emphasizes the feedback decoupling theory on the time domain and its application to roll attitude control. The attitude control is also studied in [3] where the automatic control is developed by using the method of calculating the torque driving the aircraft to a prescribed attitude. A well-known controller called the "Proportional-Integral-Derivative controller or PID controller" is presented for pitch attitude control in [4]; this research uses many different tuning methods to obtain the optimum parameter's value of the PID.…”

Section: Introductionmentioning

confidence: 99%

“…The reduced matrices of lateral-directional dynamics servo state-feedback system, H rLD and H LD , are identical with H rL and H L , respectively. The total servo statefeedback gain matrix for both systems (K sL and K sLD ) is applied to the integrated dynamics, Equation (3), to obtain the proposed aircraft flight stabilizer system, as shown in Figure 3. The aircraft flight stabilizer system in Figure 3 uses CDM to determine the total servo state-feedback gain matrix.…”

mentioning

confidence: 99%

“…, respectively. The total servo state-feedback gain matrix for both systems ( sL K and sLD K ) is applied to the integrated dynamics, Equation(3), to obtain the proposed aircraft flight stabilizer system, as shown in Figure3.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Aircraft Flight Stabilizer System by CDM Designed Servo State-Feedback Controller

Asa

Yamamoto

2021

Aerospace

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This research presents an automatic flight control system whose advantage is its ease of modification or maintenance while still effectively meeting the system’s performance requirement. This research proposes a mixed servo state-feedback system for controlling aircraft longitudinal and lateral-directional motion simultaneously based on the coefficient diagram method or CDM as the controller design methodology. The structure of this mixed servo state-feedback system is intuitive and straightforward, while CDM’s design processes are clear. Simulation results with aircraft linear and nonlinear models exhibit excellent performance in stabilizing and tracking the reference commands for both longitudinal and lateral-directional motion.

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Section: Introductionmentioning

confidence: 99%

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confidence: 99%