• kylin05 Fixed wing patrol navigation flight control system
  • kylin05 Fixed wing patrol navigation flight control system
  • kylin05 Fixed wing patrol navigation flight control system
  • kylin05 Fixed wing patrol navigation flight control system

kylin05 Fixed wing patrol navigation flight control system

PWM output channel
8
sbus channe
1
voltage test channel
3
serial port
3 RS232 ,1 RS422
CAN port
1
Satellite Positioning System
GPS/GLONASS
Attitude Angle Measurement Range
pitch: ±90°,roll : ±180°
Attitude Angle Measurement
Attitude Measurement Accuracy
10m
Airspeed Measurement Range
0~80m/s
  • kylin05 Fixed wing patrol navigation flight control system
  • kylin05 Fixed wing patrol navigation flight control system

Description

kylin05 Fixed wing patrol navigation flight control system

Flight Control Characteristics

  • A navigation flight control system designed specifically for patrol

missiles.

  • Supports hand-throwing takeoff, ejection takeoff, tube ejection

takeoff, parachute descent, and other take-off and landing modes, can be

connected to remote control receiver.

  • It integrates GNSS module, MEMS inertial measurement unit,

barometric altimeter, and airspeed meter, capable of measuring the

position, speed, airspeed, barometric height, altitude, attitude, heading,

angular velocity, acceleration, voltage, number of positioning stars, flight

time, journey, distance from home, and other information about the

aircraft.

  • It has functions such as take-off climb, route flight, hover in place,

fixed-point hover, one-key fly to target point, semi-increased stability

flight (using the joystick to control roll), homing, loss of star protection,

chain disconnection protection, low voltage protection, etc.

  • Supports pass-through pod control; when used with our

company's pod, it can follow the flight, target point guidance, target

position estimation, lock and attack target; in training mode, it can exit

the attack mode and pull up to hover before hitting.

  • No need for magnetic compass calibration, it can take off after

positioning

Highly integrated multi-function design
Reduced system size and wiring complexity Improved reliability and environmental adaptability
Optimized cost-to-performance ratio

High-Precision Inertial Measurement System

The system is equipped with a high-performance gyroscope and accelerometer, enabling precise detection of angular velocity and linear acceleration. The controller features low bias, excellent stability, and strong anti-interference capabilities, ensuring reliable motion sensing.

The gyroscope supports an angular velocity range of ±200°/s, with low zero-point deviation and minimal nonlinearity, ensuring accurate attitude measurement. The accelerometer provides multi-axis measurement capabilities, maintaining high sensitivity and stability even under dynamic conditions.

Gyroscope Performance

Angular velocity range: -200°/s to +200°/s
Low zero-point deviation, high stability
Low proportional factor nonlinearity, low crosstalk

Accelerometer Performance

Measurement Range: -10g to +10g (maximum ±15g axial)
Low zero-point deviation, high stability
High bandwidth response in dynamic environments

Navigation Accuracy

Initial alignment attitude error ≤1.0°
Position accuracy within 120 meters (short-term solution)
Attitude accuracy within 1.6°

Designed for Demanding Environments

This controller maintains stable operation under various dynamic conditions. The bandwidth of both the gyroscope and accelerometer is ≥70 Hz, ensuring fast system response and reliable control performance.

Its robust design minimizes the effects of vibration, noise, and environmental interference, making it suitable for demanding applications.

Specifications
Product Name Integrated flight controller

Accelerometer measurement range

-10g~10g, (axial -15g~15g).

Accelerometer zero bias

≤ 15mg (3σ)

Accelerometer zero bias stability

≤ 15mg (3σ)

Accelerometer scale factor non-linearity

≤ 500ppm

Accelerometer cross-coupling coefficient

≤ 500ppm

Accelerometer bandwidth:

≥ 70Hz (phase lag 90°

Navigation initial alignment attitude error

≤1.0° (3σ)

Initial alignment time

≤ 40s

Navigation solution position error within 18s

≤120m (3σ)

Navigation solution attitude error (including initial alignment error) within 18s

≤ 1.6° (3σ)

Application Scenarios

The integrated flight controller is suitable for systems requiring precise navigation and stable control performance

Unmanned aerial platforms Autonomous navigation systems Stabilized control systems High-dynamic motion platforms

FAQ

1.What is the main function of this controller?

It provides real-time navigation, motion sensing, and flight control in a single integrated unit.

2. How fast is the system initialization?

The initial alignment time is ≤40 seconds.

3. Is it suitable for high dynamic environments?

Yes, with high bandwidth sensors and stable performance, it is designed for dynamic conditions.