What are Space Qualified Accelerometers?

Space Qualified Accelerometers are precision inertial sensors designed to measure linear acceleration in spacecraft operating under vacuum, radiation, and extreme thermal conditions. These devices typically employ microelectromechanical systems (MEMS), piezoelectric, capacitive, or force-rebalance sensing architectures to detect inertial forces acting on a proof mass. The resulting displacement or force is converted into an electrical signal proportional to the applied acceleration, enabling accurate monitoring of spacecraft dynamics, structural loads, and attitude control maneuvers.

Engineered for long-duration missions, space accelerometers incorporate radiation-tolerant electronics, mechanically stable housings, and low-noise signal conditioning circuits to maintain measurement integrity over time. Their performance directly impacts navigation accuracy, vibration analysis, structural health monitoring, and propulsion system characterization. Careful selection of mechanical, electrical, and environmental parameters ensures compatibility with mission profiles and spacecraft integration constraints.

Key specifications of space qualified accelerometer:

• Orbit: Defines the operational environment such as LEO, MEO, GEO, or deep space. Orbit determines radiation exposure, thermal cycling, and microgravity conditions, which influence component screening, shielding requirements, and long-term calibration stability.
• Mass: Indicates the total mass of the accelerometer including sensing element, electronics, and housing. Mass affects spacecraft payload allocation and dynamic response characteristics, particularly in precision attitude and vibration measurement applications.
• Acceleration Range: Specifies the minimum and maximum measurable acceleration levels. The selected range determines suitability for low-level microgravity detection or high-dynamic launch and maneuver monitoring, influencing sensor design and signal conditioning architecture.
• Sensitivity: Represents the output signal change per unit of applied acceleration. Sensitivity affects measurement resolution and compatibility with downstream analog-to-digital conversion systems, directly influencing detection capability for small dynamic events.
• Base Strain Sensitivity: Describes the sensor’s susceptibility to mechanical strain transmitted through the mounting structure. Low base strain sensitivity minimizes measurement errors caused by structural deformation and enhances accuracy in high-load environments.
• Magnetic Sensitivity: Indicates the degree to which external magnetic fields influence the accelerometer output. Magnetic sensitivity must be controlled to prevent interference from spacecraft magnetic torquers, power systems, or environmental fields.
• Transverse Sensitivity: Refers to the response of the sensor to acceleration perpendicular to its primary measurement axis. Minimizing transverse sensitivity ensures axis decoupling and improves multi-axis measurement accuracy.
• Spectral Noise: Defines the noise density across frequency, typically expressed as acceleration per square root of bandwidth. Spectral noise determines the sensor’s capability to resolve low-level vibrations and contributes directly to system-level measurement uncertainty.
• Discharge Time: Specifies the time required for the sensor output to return to baseline after a transient event. Discharge time affects recovery behavior and suitability for repetitive dynamic measurements.
• Frequency Response: Describes the operational bandwidth over which the accelerometer maintains accurate amplitude and phase characteristics. Frequency response determines applicability for structural vibration analysis, propulsion diagnostics, and attitude control feedback.
• Resonance Frequency: Indicates the natural frequency of the sensing element. Operation well below resonance frequency ensures stable and linear measurement performance while preventing amplification artifacts.
• Linearity: Represents the degree to which output remains proportional to applied acceleration across the specified range. High linearity is essential for maintaining predictable calibration and minimizing systematic measurement errors.
• Noise Floor: Defines the minimum detectable acceleration level limited by intrinsic sensor noise. A lower noise floor enhances capability for micro-vibration detection and precision navigation applications.
• Connector: Specifies the electrical interface used for signal and power connectivity. Connector selection influences integration reliability, electromagnetic compatibility, and mechanical robustness in launch and orbital environments.
• Housing Material: Refers to the structural material enclosing the accelerometer assembly. Housing material affects mechanical stability, thermal expansion characteristics, radiation shielding, and overall durability in space conditions.

The Largest Database of Space Qualified Accelerometers

SatNow has listed Space Qualified Accelerometers from the leading manufacturers and made them searchable by specification. You can enter the key parameters and the search tool will scan catalogs from the leading manufacturers to identify products that meet your spec. Once you find Space Qualified Accelerometers that meet your requirement, you can view product information, download datasheets or request quotations. Quotation requests will be routed to the manufacturer of the product who will get back to you directly. The quotation will also be routed to distributors of the product in your region.