PSGI-1A rocket engine hardware
PSGI-1A Engine System

Engineered for Mission Assurance.

A pressure-fed LOX/RP-1 engine designed from the ground up with COTS-qualified components, regenerative cooling, and a modular architecture that eliminates single-source risk.

Design Philosophy

Heritage Performance. Commercial Agility.

The PSGI-1A draws on decades of liquid propulsion heritage while rejecting the cost and schedule penalties of traditional aerospace procurement. Every subsystem was evaluated against a COTS-first criterion: if a commercial component could meet the performance envelope, it was qualified and integrated. The result is an engine with heritage-class Isp and thrust margins, delivered on a commercial timeline.

COTS-First Sourcing

All components evaluated against commercial availability before custom fabrication is considered. 94% of components are COTS-qualified.

Modular Architecture

Subsystems are designed for independent replacement and upgrade. Thrust chamber, injector, and feed system are all field-swappable.

Regenerative Cooling

Propellant-cooled nozzle and chamber wall design eliminates ablative liner replacement between test campaigns.

Restart Capability

Demonstrated multi-start ignition sequence. Engine supports up to 5 restarts per mission profile without hardware replacement.

Performance Specifications

PSGI-1A // Full Technical Data

Thrust & Performance

Thrust (Vacuum)25,000 lbf111.2 kN
Thrust (Sea Level)21,800 lbf97.0 kN
Specific Impulse (Vac)311 secMeasured
Specific Impulse (SL)271 secMeasured
Thrust-to-Weight36.5:1Engine only

Propulsion System

PropellantsLOX / RP-1Bipropellant
Mixture Ratio (O/F)2.56Nominal
Chamber Pressure850 psiaNominal
Feed SystemPressure-FedCOTS regulators
Nozzle Expansion Ratio40:1Bell nozzle

Physical & Operational

Engine Mass (Dry)312 kg688 lbs
Overall Length2.14 m84.3 in
Nozzle Exit Diameter0.91 m35.8 in
Restart Capability5 startsPer mission
Min Burn Duration0.5 secDemonstrated

Maturity & Qualification

Technology Readiness LevelTRL-6Validated
Hot-Fire Tests Completed143 campaigns
Total Accumulated Burn Time312 secAcross all tests
Max Single Burn Duration45 secCampaign 3
Anomalies (Major)0All campaigns
Innovation Differentiators

What Sets PSGI-1A Apart.

47%Cost Reduction

Versus heritage component procurement. COTS sourcing strategy drives down recurring unit cost without sacrificing performance margins.

18 moDevelopment Timeline

From PDR to first hot-fire. Compressed schedule enabled by COTS availability and modular design that allows parallel subsystem development.

0Single-Source Parts

Every component has at least two qualified vendor sources. Supply chain resilience is a design requirement, not an afterthought.

TRL-6Validated Maturity

System-level demonstration in a relevant environment. Ready for program integration and qualification testing under government oversight.

Request the Full Technical Data Package.

Detailed design documentation, test data reports, and cost models are available to qualified program offices under NDA.

Request Technical Package
PSGI Space

Advancing propulsion through COTS-derived engineering. Mission-ready solutions for government and commercial launch programs.

psgi.space
Program Status
Engine DesignationPSGI-1A
Current TRLTRL-6
Test CampaignActive
PropellantLOX / RP-1
© 2026 PSGI Space. All rights reserved.