Tianjian TY-INS10A

The Tianjian TY-INS10A is a compact inertial navigation device for attitude measurement in low-cost aircraft. It combines MEMS inertial sensors, power conversion circuitry and a navigation computer, supporting initial alignment, real-time position, velocity and attitude output, and integrated navigation using external satellite navigation data.

Tianjian InertialDrone flight controller

Application: Attitude measurement for various low-cost aircraft
Weight: ≤140g
Dimensions: 50 mm×60 mm×26 mm

Product overview

The Tianjian TY-INS10A from Chongqing Tianjian Inertial Technology Co., Ltd. is an inertial navigation device for attitude measurement in low-cost aircraft. Its construction combines MEMS gyroscopes and accelerometers with power conversion circuitry and a high-performance navigation computer. Attitude calculation algorithms support initial alignment and measurement on moving platforms. The device incorporates self-test, static initial alignment and communication with a user terminal, with real-time output of position, velocity and attitude.

The TY-INS10A measures 50mm×60mm×26mm and weighs ≤140g. Its measurement ranges cover heading from 0° to 360°, pitch to ±90°, roll to ±180° and angular rate to ±500°/s. Acceleration measurement extends to ±50g on the X axis and ±10g on the Y and Z axes. Self-alignment takes ≤3s, while transfer alignment takes ≤30s. External satellite navigation data can be received for integrated navigation. In pure inertial navigation over 45s, heading accuracy is ≤0.6° and attitude accuracy is ≤0.45°, both at 3σ.

Flight control & navigation

Specifications

Tianjian TY-INS10A specifications
Specification	Value & conditions
Product	Chongqing Tianjian Inertial Technology Co., Ltd. TY-INS10A inertial navigation device
Application	Attitude measurement for various low-cost aircraft
Construction	MEMS gyroscopes, MEMS accelerometers, power conversion circuitry and a high-performance navigation computer
Attitude processing	Attitude calculation algorithms support initial attitude alignment and high-precision attitude measurement on moving platforms
Self-test	Self-test function
Integrated navigation	Receives external satellite navigation data for integrated navigationWith external satellite navigation data.
Initial alignment	Static initial alignmentStatic initialization.
Communication and output	Communicates with a user terminal and outputs position, velocity and attitude in real time
Weight	≤140g
Dimensions	50mm×60mm×26mm
Heading angle range	0°–360°
Pitch angle range	±90°
Roll angle range	±180°
Angular rate measurement range	±500°/s
Acceleration measurement range	±50gX axis.
Acceleration measurement range	±10gY and Z axes.
Alignment time	≤3sSelf-alignment.
Alignment time	≤30sTransfer alignment.
Attitude angle alignment accuracy	≤0.15°3σ.
Position accuracy	≤60mPure inertial navigation; 3σ, 45s.
Velocity accuracy	≤2.5m/sPure inertial navigation; 3σ, 45s.
Heading angle accuracy	≤0.6°Pure inertial navigation; 3σ, 45s.
Attitude angle accuracy	≤0.45°Pure inertial navigation; 3σ, 45s.
Bias stability	≤5°/hGyroscope; 1σ, 10s smoothing.
Bias repeatability	≤3°/hGyroscope; 1σ.
Bias stability	≤0.2mgAccelerometer; 1σ, 10s smoothing.
Bias repeatability	≤0.3mgAccelerometer; 1σ.