BLOCK 00
Architecture closure
Close the mass, propulsion, trajectory, thermal and economic models. Select the subsonic carrier, orbital stack and safe maritime operating range.
Development program
Earn each
flight regime.
Start with the separation problem we can fly now. Advance only when hardware closes the next risk.
FA / PROGRAM / 001
Evidence-led gates
No calendar fiction
Evidence-led gates
No calendar fiction
01 / ROADMAP
A program of
measured escalation.
The roadmap is gated by technical evidence, not promotional dates. Each block produces an operational capability and data for the next decision.
Current focus
BLOCK 01
Subsonic separation demonstrator
Use a modified widebody carrier and instrumented test article to validate carriage loads, release dynamics, delayed ignition and autonomous range safety.
BLOCK 02
Small orbital service
Operate a subsonic air-launch service with a compact multistage rocket. Learn the real economics of aircraft integration, launch cadence and mobile range operations.
BLOCK 03
Mach 2–3 reusable carrier
Introduce a purpose-built high-speed carrier without requiring a scramjet. Validate thermal cycles, inlet behavior, downrange recovery and supersonic separation.
BLOCK 04
Mach 5 flight demonstrator
Demonstrate the full carrier flow path, shallow zoom, low-q separation and reusable descent before integrating a live orbital stage.
BLOCK 05
Hypersonic orbital service
Pair the operational carrier with the lightest credible orbital vehicle. Scale cadence only after turnaround inspection and mission reliability are measured.
02 / RISK
The hard parts,
named early.
A reusable hypersonic first stage is not made safe by calling it an aircraft. The program is organized around the risks that can end it.
| Risk | Why it matters | Closure method | Priority |
|---|---|---|---|
| Installed propulsion | Net thrust must remain positive after inlet, cooling and nozzle losses across the flight envelope. | Full-flow-path ground rig, then progressive flight envelope expansion. | Critical |
| Stage separation | Shock interaction or recontact can destroy both vehicles before orbital ignition. | CFD, wind tunnel, captive carry, inert drop and powered separation sequence. | Critical |
| Thermal cycling | Reusable economics fail if every Mach 5 sortie demands extensive structure and inlet replacement. | Representative hot-structure coupon tests and inspection-hour tracking. | Critical |
| Orbital mass margin | The carrier only creates value if the remaining orbital stage closes with useful payload. | Independent mass model with reserves and trajectory-coupled sizing. | High |
| Recovery operations | A downrange landing may require multiple bases, crews and fuel systems. | Lifecycle model based on real block-flight operations. | High |
| Range integration | Runway departure does not remove launch corridors, hazard areas or licensing. | Early regulator and maritime-range partnership. | High |
03 / DECISION
Optimize lifecycle cost.
Not fuel headlines.
Mach 5 is worth pursuing only if higher payload fraction outweighs development, inspection and downrange recovery cost.
Payload per sortie
Useful mass delivered to the exact target orbit after reserves—not gross mass attached to the carrier.
Inspection burden
Maintenance hours and replaced hardware after every thermal and propulsion cycle.
Mission reliability
Probability of successful deployment, carrier recovery and readiness for the next sortie.