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Our Launch Vehicle Programme

Speck

Semi-Reusable Launch Vehicle Demonstrator

Speck is a small-scale reusable launch vehicle demonstrator developed to validate core technologies required for propulsive vertical landing and rapid vehicle reuse. The programme focuses on iterative flight testing of guidance, navigation, and control systems; propulsion performance; and structural reusability under repeated flight loads.

Height
m
Diameter
m
Gross Mass
kg
Propellant
— / —
Max Thrust
kN
Flight Profile
VTVL
QUNIX Speck reusable launch vehicle demonstrator

Development Roadmap

Phase 01 · 2024
Concept Design & Feasibility
Initial vehicle sizing, propulsion trade studies, and mission architecture definition.
Completed
Phase 02 · 2025
Engine Development & Bench Testing
Design and fabrication of the primary propulsion unit. Cold-flow testing, ignition trials, and thrust characterisation.
Completed
Phase 03 · 2026 — Current
Full Prototype Manufacturing & Ground Test
Assembly of complete flight vehicle. Static fire testing of integrated propulsion system. Avionics integration and GNC software validation.
In Progress
Phase 04 · 2026 – 2027
Hop Testing & Low-Altitude VTVL Flights
Tethered hover tests followed by free-flight low-altitude hop campaigns.
Planned
Phase 05 · 2027
High-Altitude Flight & Recovery Demonstration
Full mission profile flight to target apogee followed by propulsive return-to-launch-site manoeuvre and precision vertical landing.
Planned
Phase 06 · 2027 – 2028
Speck 2 — Full Scale Design Lock
Translation of Speck lessons into full-scale orbital vehicle design. Engine upscaling programme begins.
Planned

Siragu

Siragu is QUNIX's medium-lift reusable launch vehicle, designed to deliver payloads to low Earth orbit and sun-synchronous orbit with a fully reusable first stage. Named after the Tamil word for eagle, Siragu represents the next step after Speck — scaling proven reusability into an operational orbital system at competitive cost-per-kg.

Payload to LEO
1,000
kg
500 km circular orbit · expendable
Payload to SSO
700
kg
500 km sun-synchronous orbit
Lift-off Thrust
350
kN
Multi-engine first stage · sea level
Vehicle Height
22
m
Diameter: 1.8 m
Gross Lift-off Mass
35,000
kg
LOX / RP-1 propellant
Target Orbit
250–550
km LEO / SSO
Inclinations 28° – 98°

First Stage · Propulsion

Engine designationIn development
Propellant combinationLOX / RP-1
Cycle typeGas generator
Sea-level thrust350 kN
Specific impulse (SL)~295 s
Recovery methodPropulsive VTVL

Second Stage · Performance

EngineVacuum optimised
Vacuum thrust~45 kN
Specific impulse (vac)~340 s
Fairing diameter1.8 m
Payload volume~3.5 m³
Separation altitude~90 km
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Email

contact@qunixspace.com

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Address

Komarayanur, Anthiyur
Erode 638504
Tamil Nadu, India

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