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New Crowdin translations - ko (#26487)

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Co-authored-by: Crowdin Bot <support+bot@crowdin.com>
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2026-02-18 16:44:57 +11:00
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docs/ko/flight_stack/controller_diagrams.md
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@@ -30,7 +30,7 @@ The diagrams use the standard [PX4 notation](../contribute/notation.md) (and eac
::: info
The IMU pipeline is:
gyro data > apply calibration parameters > remove estimated bias > notch filter (`IMU_GYRO_NF0_BW` and `IMU_GYRO_NF0_FRQ`) > low-pass filter (`IMU_GYRO_CUTOFF`) > vehicle_angular_velocity (_filtered angular rate used by the P and I controllers_) > derivative -> low-pass filter (`IMU_DGYRO_CUTOFF`) > vehicle_angular_acceleration (_filtered angular acceleration used by the D controller_)
gyro data > apply calibration parameters > remove estimated bias > notch filter (`IMU_GYRO_NF0_BW` and `IMU_GYRO_NF0_FRQ`) > low-pass filter (`IMU_GYRO_CUTOFF`) > vehicle_angular_velocity (\_filtered angular rate used by the P and I controllers_) > derivative -> low-pass filter (`IMU_DGYRO_CUTOFF`) > vehicle_angular_acceleration (\_filtered angular acceleration used by the D controller_)
![IMU pipeline](../../assets/diagrams/px4_imu_pipeline.png)
@@ -177,7 +177,7 @@ The angular position of the control effectors (ailerons, elevators, rudders, ...
또한 제어 표면은 고속에서 더 효과적이고 저속에서는 덜 효과적이기 때문에, 순항 속도에 맞게 조정된 컨트롤러는 속도 측정을 사용하여 조정됩니다(이러한 센서가 사용되는 경우).
:::info
If no airspeed sensor is used then gain scheduling for the FW attitude controller is disabled (it's open loop); no correction is/can be made in TECS using airspeed feedback.
If no airspeed sensor is used then gain scheduling for the FW attitude controller is disabled (it's open loop); no correction is/can be made in TECS using airspeed feedback.
:::
피드포워드 이득은 공기역학적 감쇠를 보상합니다.
@@ -187,7 +187,7 @@ If no airspeed sensor is used then gain scheduling for the FW attitude controlle
### Turn coordination
롤 및 피치 컨트롤러는 동일한 구조를 가지며, 종방향 역학과 횡방향 역학은 독립적으로 작동하기에 충분히 분리되어 있다고 가정합니다.
그러나, 요 콘트롤러는 항공기가 미끄러질 때 생성되는 측면 가속도를 최소화하기 위해 선회 조정 제약 조건을 사용하여 요 각속도 설정점을 계산합니다. The turn coordination algorithm is based solely on coordinated turn geometry calculation.
그러나, 요 콘트롤러는 항공기가 미끄러질 때 생성되는 측면 가속도를 최소화하기 위해 선회 조정 제약 조건을 사용하여 요 각속도 설정점을 계산합니다. The turn coordination algorithm is based solely on coordinated turn geometry calculation.
$$\dot{\Psi}_{sp} = \frac{g}{V_T} \tan{\phi_{sp}} \cos{\theta_{sp}}$$