|
| एमओक्यू: | 1 सेट |
| मूल्य: | $1000-$100000 |
| वितरण अवधि: | 30 कार्य दिवस |
| भुगतान विधि: | टी/टी |
| आपूर्ति क्षमता: | प्रति वर्ष 500 सेट |
The next-generation gyrocompassing-grade Inertial Measurement Unit (IMU) is engineered for demanding navigation and precision positioning applications. Designed for mission-critical platforms, it delivers high-accuracy heading, attitude, and inertial navigation performance for aerospace, defense, unmanned systems, industrial surveying, and maritime operations.
The unit integrates advanced inertial sensing architecture within a rugged, environmentally-sealed aluminum enclosure, providing exceptional resistance to vibration, shock, and harsh environmental conditions. It maintains long-term performance stability without the need for external cooling or auxiliary thermal management.
This IMU is deployed across a wide range of platforms and operational environments, including:
Multiple interface and output configurations are available to support flexible integration into flight control computers, navigation computers, GNSS/INS integrated solutions, and avionics architectures. Users can configure output data rates, filtering modes, and communication protocols to optimize performance for specific mission profiles.
As a gyrocompassing-class inertial sensor, the unit offers high stability, high reliability, and excellent SWaP (Size, Weight, and Power) characteristics — providing advanced inertial navigation capability with reduced system burden. It is well-suited for applications requiring high-precision heading, inertial positioning, and sustained autonomy in GPS-denied or contested environments.
| Parameter | Specification |
| Navigation System | Strapdown Inertial System (SINS) |
| Startup Time | ≤ 10 s (from power-on to self-test completion) |
| Core Sensor Accuracy – Gyroscope | Bias stability: ≤ 0.1°/h (1σ) |
| Bias repeatability: ≤ 0.05°/h (1σ) | |
| Scale factor error: ≤ 20 ppm (1σ) | |
| Random walk: ≤ 0.02°/√h (1σ) | |
| Range: ±1000°/s | |
| Core Sensor Accuracy – Accelerometer | Bias stability: ≤ 5×10⁻⁵ g (1σ) |
| Bias repeatability: ≤ 5×10⁻⁵ g (1σ) | |
| Scale factor error: ≤ 50 ppm (1σ) | |
| Range: -60 g ~ +60 g | |
| Navigation Data Update Rate | ≥ 200 Hz |
| Input Voltage | 18–32 V, typical 24 V |
| Power Consumption (Steady-State) | ≤ 15 W |
| Weight | ≤ 1.5 kg |
| Dimensions (D × H) | 110 mm × 115 mm |
| Interfaces | 1 × RS232, 1 × RS485, 1 × RS422 |
| Operating Temperature | -40 °C ~ +60 °C |
| Storage Temperature | -55 °C ~ +70 °C |
| Operating Humidity | ≤ 95% (25 °C) |
| Storage Humidity | ≤ 95% (30 °C) |
|
|
| एमओक्यू: | 1 सेट |
| मूल्य: | $1000-$100000 |
| वितरण अवधि: | 30 कार्य दिवस |
| भुगतान विधि: | टी/टी |
| आपूर्ति क्षमता: | प्रति वर्ष 500 सेट |
The next-generation gyrocompassing-grade Inertial Measurement Unit (IMU) is engineered for demanding navigation and precision positioning applications. Designed for mission-critical platforms, it delivers high-accuracy heading, attitude, and inertial navigation performance for aerospace, defense, unmanned systems, industrial surveying, and maritime operations.
The unit integrates advanced inertial sensing architecture within a rugged, environmentally-sealed aluminum enclosure, providing exceptional resistance to vibration, shock, and harsh environmental conditions. It maintains long-term performance stability without the need for external cooling or auxiliary thermal management.
This IMU is deployed across a wide range of platforms and operational environments, including:
Multiple interface and output configurations are available to support flexible integration into flight control computers, navigation computers, GNSS/INS integrated solutions, and avionics architectures. Users can configure output data rates, filtering modes, and communication protocols to optimize performance for specific mission profiles.
As a gyrocompassing-class inertial sensor, the unit offers high stability, high reliability, and excellent SWaP (Size, Weight, and Power) characteristics — providing advanced inertial navigation capability with reduced system burden. It is well-suited for applications requiring high-precision heading, inertial positioning, and sustained autonomy in GPS-denied or contested environments.
| Parameter | Specification |
| Navigation System | Strapdown Inertial System (SINS) |
| Startup Time | ≤ 10 s (from power-on to self-test completion) |
| Core Sensor Accuracy – Gyroscope | Bias stability: ≤ 0.1°/h (1σ) |
| Bias repeatability: ≤ 0.05°/h (1σ) | |
| Scale factor error: ≤ 20 ppm (1σ) | |
| Random walk: ≤ 0.02°/√h (1σ) | |
| Range: ±1000°/s | |
| Core Sensor Accuracy – Accelerometer | Bias stability: ≤ 5×10⁻⁵ g (1σ) |
| Bias repeatability: ≤ 5×10⁻⁵ g (1σ) | |
| Scale factor error: ≤ 50 ppm (1σ) | |
| Range: -60 g ~ +60 g | |
| Navigation Data Update Rate | ≥ 200 Hz |
| Input Voltage | 18–32 V, typical 24 V |
| Power Consumption (Steady-State) | ≤ 15 W |
| Weight | ≤ 1.5 kg |
| Dimensions (D × H) | 110 mm × 115 mm |
| Interfaces | 1 × RS232, 1 × RS485, 1 × RS422 |
| Operating Temperature | -40 °C ~ +60 °C |
| Storage Temperature | -55 °C ~ +70 °C |
| Operating Humidity | ≤ 95% (25 °C) |
| Storage Humidity | ≤ 95% (30 °C) |
