Our ultra-low bias IMUs and gyroscopes can help move your mission forward.
Over contested airspace, jamming is a planning assumption, and a UAS that navigates only by GNSS is a UAS with a short mission. OSCP builds low-SWaP photonic and MEMS IMUs, ITAR-free and made in Canada, that hold heading and slow position drift through the denial window.
The challenge
When GNSS drops, the flight controller falls back on its inertial sensors, and position error grows with every second of denial because gyro and accelerometer errors integrate over time. IMU quality sets how long the aircraft holds a useful navigation estimate.
The airframe works against the sensor too. Motor and propeller vibration couples directly into vibrating-mass MEMS gyros, which are g-sensitive, so sustained vibration shows up as rate error before the jammer ever switches on. All of it inside a SWaP budget measured in grams and single watts.
How OSCP helps
Optical sensing where vibration is worst. The MK2E2 measures rotation with light via the Sagnac effect, with no moving parts in the sensing path, so it is highly resistant to the vibration that degrades vibrating-mass MEMS gyros.
Sized for small airframes. The MK2M2 is 40 x 40 x 25 mm, 75 g and 1.2 W. The MK2E2 is 78 x 63 x 36 mm, 230 g and 2 W. RS-422 and CAN-FD straight to your flight controller at up to 500 Hz.
Tested to the environment. Vibration passed at 2, 4 and 8 g, shock passed at 20 g and 40 g, both to DO-160 style profiles. Built to withstand harsh environments.
An export path that scales. ITAR-free and made in Canada, so allied exports run under Canadian controls with no US approval in the loop. Tell us your destination countries and we will confirm the export path before you commit.
Recommended configuration
| Product | Grade | Choose it when |
|---|---|---|
| MK2M2 | Tactical Grade MEMS IMU, 0.5 °/hr min in-run bias, typically under 1.0 °/hr | Volume, weight-driven airframes with short denial windows and good aiding: airspeed, magnetometer, vision. 75 g, 1.2 W. |
| MK2E2 | Tactical Grade Photonic IMU, 0.5 °/hr min in-run bias, typically under 1.0 °/hr | The jamming window is long or vibration is severe, and the navigation estimate has to hold on inertial quality alone. 230 g, 2 W. |
Both share < 15 µg accelerometer bias stability and the same RS-422 or CAN-FD interface. The MK2M2 is IP67. The MK2E2 is IP57, with IP67 certification in progress. The MK2E2 is the larger unit, so it is not a mechanical drop-in for the MK2M2.
Proof
In our published case study, a 21 minute drive through Montreal with GNSS positioning denied, heading came from the gyro alone with a 1 Hz speed input for distance and no EKF. The MK2E2 finished 5.7 m from ground truth against 20.5 m for the MK2M2. Both units ran identical aiding, so the 3.6x gap is set almost entirely by heading drift. It is ground data, but the drift mechanism it exposes is exactly what a UAS fights in flight.
FAQ
Will motor and propeller vibration degrade the gyro in flight?
It affects every gyro, but differently. MEMS gyros sense rotation with a vibrating proof mass and are g-sensitive, so airframe vibration couples into rate error. The MK2E2’s optical gyro has no moving parts in the sensing path and is highly resistant. Our units passed vibration at 2, 4 and 8 g to DO-160 style profiles.
Do you offer a version with GNSS built in?
Ask us. Where a GNSS receiver is fitted alongside the IMU it adds a receiver only, with no onboard fusion, so your flight controller keeps ownership of the navigation solution. An INS with GNSS receivers is also scheduled for release Q4 2026.