System architecture

Two vehicles.
One clean handoff.

A reusable aircraft owns atmospheric ascent. A dedicated rocket owns vacuum acceleration. Neither carries the other's compromises to orbit.

FA / ARCH / 001
Concept baseline
Revision 01
01 / VEHICLES

Specialize the hardware.
Simplify the mission.

The baseline is not a single-stage spaceplane. It is a reusable first stage and a separate orbital vehicle, joined only for the first part of flight.

FA-C1 / CARRIER

Astra Carrier

An uncrewed, runway-recoverable aircraft that accelerates the orbital vehicle through the atmosphere and releases it during a low-dynamic-pressure coast.

Propulsion
Air-breathing combined cycle
Design point
Mach 5 / 25–30 km
Release
40–60 km ballistic coast
Recovery
Downrange runway
Status
Architecture study
FA-O1 / ORBITAL VEHICLE

Astra Orbital

A compact rocket-powered vehicle sized around the velocity that remains after carrier release—not around the demands of sea-level launch.

Propulsion
High-efficiency vacuum rocket
Ignition
After positive clearance
Mission
300–550 km LEO
Configuration
One or two stages, trade open
Status
Mass model pending
02 / FIRST PRINCIPLES

Altitude is access.
Velocity is orbit.

At 300 km, circular orbit requires about 7.73 km/s sideways. The carrier is valuable because it supplies useful downrange velocity and eliminates first-stage onboard oxidizer—not because it simply climbs high.

v = √(μ / r)
≈ 7.73 km/s

The orbital requirement

Mach 5 contributes roughly 20% of orbital speed and 4% of orbital kinetic energy. Rocket mass changes exponentially with required velocity, so that contribution can still materially improve the orbital stage's propellant fraction.

1.5 km/sMach 5 near 30 km
3.8%Orbital kinetic energy
~8.6Illustrative rocket mass ratio
Low-qRelease objective
03 / CARRIAGE

Protected in flight.
Positive at release.

The hypersonic vehicle requires an integrated cradle, not a conventional bomb bay. Separation is commanded, measured and complete before the orbital engine is allowed to start.

01

Semi-recessed centerline

The orbital vehicle sits in a ventral cradle that limits wave drag while preserving a direct, downward escape path.

02

Mechanical clearance

Pneumatic or cold-gas ejectors create relative velocity. Weightlessness alone does not separate two coasting vehicles.

03

Delayed ignition

Independent sensing confirms distance, attitude and divergent trajectories before the orbital stage commits to powered flight.

04 / DESIGN RULES

What the system
will not pretend.

Credibility is a design constraint. These boundaries keep the program tied to physics and test evidence.

01
Air is not fuel
Energy source

The carrier still needs onboard fuel. Atmospheric air supplies oxidizer and reaction mass.

02
Mach 5 is not orbit
Velocity gap

The orbital stage still provides the majority of velocity and all sustained vacuum propulsion.

03
Runway does not mean airline
Operations

Hypersonic structures, inlets and separation remain experimental until proven through repeated flight.

04
Targets are not test results
Evidence

Performance numbers remain design objectives until closed by mass models and validated in hardware.

See how the handoff
becomes an orbit.

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