AYAP Lunar Propulsion System
DELTAV Space Technologies
DeltaV Space Technologies' hybrid propulsion system under development for Turkey's Lunar Hard Landing Mission (AYAP), designed for lunar descent braking.
Typed specifications1 values
Discloses 1 of 11 fields engineers filter by in this category (category median 3).
- Propulsion family
- hybrid description
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier6 lines, in the manufacturer's own wording
- Mission
- Turkey Lunar Hard Landing Mission (AYAP)
- Propulsion type
- Hybrid (solid fuel + liquid oxidizer)
- Function
- Lunar descent braking burn
- Program owner
- Turkish Space Agency (TUA)
- Status
- Development
- Key capability
- Deep space operation, vacuum restart (demonstrated on SORS)
About
DeltaV Space Technologies is developing a hybrid rocket propulsion system specifically for Turkey’s Lunar Hard Landing Mission (AYAP — Aya Postası, ‘Lunar Mail’), a flagship mission of Turkey’s National Space Program targeting the Moon as part of Turkey’s stated goal of landing a satellite on the Moon by the Republic’s centennial celebrations and beyond.
The AYAP propulsion system is designed to provide the deceleration burn required for a hard landing (impact at controlled velocity) on the lunar surface, requiring operation in the deep space environment far from Earth. DeltaV’s hybrid propulsion technology — combining solid fuel with a liquid oxidizer — offers advantages for this mission: storability (no cryogenic oxidizer), reliability (no turbopump or propellant pump for the liquid oxidizer), and the ability to restart in vacuum (as demonstrated on the SORS sounding rocket).
This is DeltaV’s most ambitious mission to date and is developed in cooperation with the Turkish Space Agency (TUA). Technical specifications for thrust, Isp, and propellant mass are not publicly disclosed.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.