The Engines of Progress
GUIDANCE, NAVIGATION
& CONTROL (GNC)
Precise, Scalable Control for Every Orbit
At Space Inventor, we know that absolute precision is the foundation of mission success. Leveraging our deep vertical integration, our Guidance, Navigation, and Control (GNC) platform is a fully integrated, flight-proven system built exclusively from our own hardware and software.
By applying our philosophy of Flexible Modularity, we offer a complete in-house solution that scales effortlessly. Whether you are flying an agile 10 kg CubeSat or a high-precision 200+ kg MicroSat in LEO, MEO, or GEO, our modular GNC suite can be rapidly tailored to meet your exact mission requirements, delivering arcsecond attitude determination and robust performance without the delays of custom engineering.
THE CORE FUNCTIONALITY:
INTELLIGENT, AUTONOMOUS PRECISION
At the heart of the GNC solution is our advanced algorithms for sensor fusion, guidance, and closed-loop control. The system is designed for maximum autonomy and reliability in orbit, featuring:
ADVANCED ATTITUDE DETERMINATION
Achieves pinpoint accuracy by fusing data from star trackers, IMUs, magnetometers, and fine sun sensors using advanced Extended Kalman Filtering.
VERSATILE CONTROL MODES
Provides precision control for a vast array of mission profiles, including Nadir, Velocity, ECI, Safe Sun pointing, target tracking, ground station tracking, and push-broom imaging modes.
ORBIT DETERMINATION
Utilizes GNSS-based positioning and velocity tracking integrated directly with our guidance algorithms.
AUTOMATED MOMENTUM MANAGEMENT
Autonomously unloads wheel momentum utilizing our in-house magnetorquer rods or optional propulsion interfaces
ROBUST FAULT TOLERANCE
A Hierarchical State Machine and FDIR (Fault Detection, Isolation, and Recovery) framework guarantees autonomous fault detection and recovery.
THE GNC SUITE
Every sensor, actuator, and processor is meticulously designed in-house to guarantee seamless integration and deterministic operation.
GNC platform is a fully integrated, flight-proven system combining all sensors, actuators, and control software required for precise spacecraft attitude and orbit control.
Built exclusively from Space Inventor hardware and software, this modular suite offers a complete in-house solution that can be tailored to meet diverse mission requirements — from agile CubeSats to high-precision MicroSats operating in LEO, MEO, or GEO.
1. THE BRAIN: AOCS COMPUTER
Achieves pinpoint accuracy by fusing data from star trackers, IMUs, magnetometers, and fine sun sensors using advanced Extended Kalman Filtering.
OBC-P4:
REDUNDANCY FOR MISSION-CRITICAL OPERATIONS
The OBC-P4 is an advanced onboard computing platform designed for maximum reliability. It consists of four independent ARM Cortex-M7 modules, each equipped with its own separate power supply, interfacing, and storage.
The Advantage:
This dual architecture makes the OBC-P4 the premier choice for hot/cold redundancy solutions. It is specifically designed to safeguard mission-critical subsystems, such as Telemetry & Command (T&C), Guidance, Navigation & Control (GNC), or the management of high-value payloads. This ensures your mission survives even the most unpredictable single-event upsets
2. THE MUSCLE: PRECISION ACTUATORS
Our actuators provide stable attitude control and momentum management across all spacecraft axes, designed for mission lifetimes of up to 5 years.
REACTION WHEELS (WHL-P4 SERIES)
Ranging from the WHL-100 to the WHL-1000, these high-performance units feature an integrated 3-phase outrunner permanent magnet synchronous motor (PMSM) for fine 3-axis control and agile slews.
MAGNETORQUERS (MT-P4 SERIES):
With the capacity of providing up to 4 Am2 of dipole moment, these integrated rods are optimized for low-power momentum dumping in LEO. Built with an annealed Alloy 79 core, they feature built-in control electronics, redundant input supplies, and redundant driver electronics for enhanced reliability.
3. THE SENSES: HIGH-FIDELITY SENSORS
Our sensor modules provide accurate, continuous data across multiple operating modes and environmental conditions.
STAR TRACKERS (STR-P3)
Utilizes advanced algorithms and compact, rad-hard optics to track across the entire celestial vault with full performance up to 0.3º/s.
INERTIAL MEASUREMENT UNIT (IMU-P4)
The IMU-P4 is a compact and rugged inertial measurement unit comprising two redundant Murata SCH16T-K01 6-DOF XYZ-axis Gyroscope and XYZ-axis Accelerometer and two RM3100 magnetometers as well as temperature sensors.
The two redundant sets of sensors are interfaced via two redundant microcontrollers and redundant CAN bus interfaces with CSP (Cubesat Space Protocol) making them accessible from the satellite communication bus.
FINE SUN SENSORS (FSS-P3)
A highly integrated module using four photodiodes to estimate the sun direction vector with exceptional precision (<1º).
