Overview

The Trident Engine represents a paradigm shift in propulsion technology. By unifying turbine, ramjet, scramjet, and rocket propulsion systems using our proprietary U-TRSR (Unified Turbine-Ramjet-Scramjet-Rocket) architecture, we have created the world's first true Single Stage To Orbit (SSTO) capable engine.

Key innovations include additively manufactured components for precise internal geometries, advanced regenerative cooling systems, and a single retractable nozzle that adapts to all four propulsion modes. This integration eliminates the complexity and weight penalties of traditional multi-stage rockets while providing unmatched operational flexibility.

The Trident Engine's turbine mode utilizes a proprietary wrap-around turbine design optimized for our integrated architecture. This mode provides reliable propulsion from takeoff through Mach 2, bridging the gap between conventional aircraft engines and high-speed propulsion systems.

Key Components:

• Multi-Stage Compressor: Seven-stage axial compressor with variable geometry inlet guide vanes
• Mid-Compressor Bypass: Controlled airflow diversion for ramjet mode preparation
• Annular Combustion Chamber: High-temperature resistant ceramic matrix composite liner
• Two-Stage Turbine: Single-crystal superalloy blades with thermal barrier coatings

The wrap-around configuration allows the turbine components to be positioned concentrically around the ramjet/scramjet flowpath, enabling seamless transition between modes without mechanical interference. During operation, the compressor provides pressurized air to the combustion chamber while the mid-compressor bypass system gradually redirects airflow as the engine approaches ramjet operating conditions.

The Trident Engine's high-speed capability. These modes utilize shock compression and controlled combustion to achieve efficient propulsion from Mach 2 through Mach 8+, covering the critical hypersonic flight regime.

Ramjet Operation (Mach 2-4):

• Shock Compression: Multiple oblique shocks decelerate and compress incoming air
• Isolator Geometry: Constant-area duct manages pressure fluctuations
• Subsonic Combustion: Fuel injection and mixing in subsonic airflow
• Boundary-Layer Fuel Injection: Enhanced mixing through wall-injection systems

Scramjet Operation (Mach 4-8+):

• Supersonic Combustion: Fuel burns in supersonic airflow without choking
• Arc-Igniter Rings: Plasma-assisted ignition ensures reliable combustion
• Variable Geometry: Adaptive inlet and combustor configuration
• Fuel Management: Precise injection timing and distribution control

The transition from ramjet to scramjet mode occurs automatically as flight speed increases, with no mechanical actuators required. Advanced computational fluid dynamics and real-time pressure monitoring ensure optimal performance across the entire operating envelope.

Rocket mode enables the Trident Engine to operate in the vacuum of space and provides the final thrust needed for orbital insertion. This mode features a completely closed-cycle design with independent liquid fuel and oxidizer systems.

Key Features:

• Mechanical Iris Transition: Sealed closure system isolates rocket mode from airbreathing modes
• Closed-Cycle Operation: Independent of atmospheric air supply
• Liquid Propellant System: High-performance fuel and oxidizer injection
• Pintle Injectors: Variable thrust and mixture ratio control
• Arc Igniters: Reliable ignition system for space operations
• Regenerative-Film Cooling: Advanced thermal management

The mechanical iris system provides a complete seal between the rocket combustion chamber and the airbreathing flowpath, allowing for optimal rocket performance while protecting sensitive turbine components from rocket exhaust temperatures. The pintle injector design enables throttling capability and restart capability essential for orbital maneuvering.

The Trident Engine's single-body variable nozzle represents a breakthrough in propulsion system integration. This innovative design replaces multiple fixed nozzles with a single, adaptable system that optimizes performance across all four propulsion modes.

Design Specifications:

• Single-Body Construction: Unified nozzle structure for all modes
• Eight Hydraulic Arms: Precise actuation system for geometry control
• Variable Position: Optimal expansion ratio for each flight regime
• Mode-Specific Configuration: Automatic adjustment based on engine mode
• Retractable Design: Compact stowed configuration for ground operations

The hydraulic actuation system provides rapid and precise nozzle positioning, with the ability to change configuration in under 3 seconds. This responsiveness is critical during mode transitions, ensuring continuous optimal performance throughout the flight envelope. The nozzle geometry is continuously optimized based on altitude, Mach number, and engine operating mode.

We are also exploring electric actuation systems as an alternative to hydraulic systems. This approach would offer enhanced precision, reduced weight, and improved reliability while maintaining the rapid response times required for seamless mode transitions.