FLIP

Overview

A commercial rover that flies before its buyer has committed to it has to solve a problem peer-reviewed programs rarely face: proving the subsystems work at flight scale without a customer’s requirements document or a customer’s launch vehicle. FLIP, the FLEX Lunar Innovation Platform, is Astrolab’s answer. It is manifested as the primary payload on Astrobotic’s Griffin Mission One to the Nobile region of the lunar south pole, a slot that opened when NASA discontinued VIPER and converted the CLPS delivery into a large-lander demonstration carrying a comparable mass [12], [5]. FLIP is not a scaled model of anything. It carries full-sized batteries, tires, avionics, sensors and software drawn from FLEX, Astrolab’s much larger commercial rover, so that each is exercised at flight scale in the environment FLEX is meant to work in before FLEX itself exists as flight hardware [11].

The design logic follows from the mismatch between the two vehicles. FLEX is Astrolab’s large modular rover, built around a standardized payload interface with an underslung bay of up to 3 cubic meters and a removable standing crew interface so the same chassis serves suited astronauts or pure teleoperation [2]. Astrobotic’s own release once projected FLEX for a Starship landing by late 2026, a date that has since slipped [12]. NASA has separately adapted a smaller derivative, CLV-1, to its Lunar Terrain Vehicle Services program, awarding Astrolab a task order of about 219 million dollars against an IDIQ ceiling of up to 4.6 billion dollars over 13 years, with delivery anticipated by 2028 and a design mass near 950 kg [1]. FLIP sidesteps both timelines: at roughly half a tonne with a 30 kg payload allocation, it is sized to ride a medium-class commercial lander that already exists, converting a component qualification problem into a manifest problem instead of a launch vehicle problem [11], [12], [4]. NASA’s own 2025 survey of in-space servicing, assembly and manufacturing capability lists Astrolab and FLEX among the vehicles being developed for exactly this class of commercial lunar logistics [4].

Specifications

Parameter	Value	Source
Mass	nearly half a metric ton	[12]
Payload capacity	30 kg
Wheels	hyper-deformable airless tires from Venturi Space	[11], [12], [3]
Battery enclosure	custom design by Venturi Space	[11]
Lander compatibility	medium-class commercial lunar landers	[12]

Dimensions, drive speed, slope limit, obstacle capability, generation capacity, battery capacity, night survival, processor and communications parameters are not published. Astrolab publishes no technical documentation for this vehicle beyond its press material, and no peer-reviewed or conference publication about it has appeared.

Mission profile

Parameter	Value	Source
Lander	Astrobotic Griffin	[12]
Landing site	Nobile region, lunar south pole
Delivery	announced for end of 2025, subsequently stated as summer 2026	[11], [12]

FLIP took the primary payload position on Griffin Mission One after the flight’s original assignment changed, when NASA canceled VIPER before delivery and Astrobotic retained the Griffin lander for a different payload manifest [12]. Astrobotic’s own record of its first lunar landing, Peregrine Mission 1, is the relevant precedent for what a Griffin-class flight actually has to survive. A single failed helium valve doomed that lander’s soft-landing attempt 92 minutes after separation, but the team still recovered 10 days 14 hours of cislunar operation and returned data from all nine payloads before a controlled re-entry, and most subsystems reached flight maturity even though the landing itself was lost [5]. Griffin Mission One is Astrobotic’s next attempt at the landing Peregrine did not complete, and it carries the consequences of that first mission’s post-flight review in its design.

Mobility

Four wheels carry hyper-deformable airless tires supplied by Venturi Space, the same wheel design intended for FLEX [11]. Venturi states a duty cycle for the wheel rather than a figure specific to FLIP: four wheels carrying a two-tonne vehicle including payload, deforming to absorb ground irregularities at 15 km/h, across south-pole temperatures spanning -240 to +130 C, required to last at least 1,000 km and to resist south-pole radiation, with NASA testing and analysis of the wheel at Glenn Research Center and Johnson Space Center [3]. That duty cycle is stated for the larger FLEX vehicle; no wheel test data specific to FLIP’s roughly 500 kg mass has been released, and no speed, gradeability, obstacle height or ground-pressure result appears anywhere in Astrolab’s material [11].

The gap between a stated duty cycle and a demonstrated one is the ordinary condition of lunar wheel-soil work, not a defect specific to Astrolab. The only published reduced-gravity wheel-soil dataset in this class comes from parabolic-flight tests of a different wheel, an ExoMars-style prototype driven through Martian simulant under 20 to 30 seconds of lunar and Martian gravity at a time, with wheel load held constant against the ground-test baseline so gravity’s effect on the soil could be isolated: drawbar pull fell 20 percent on average in lunar gravity and maximum sinkage rose 38 percent, both statistically significant [6]. No test of this kind has been run against a hyper-deformable airless tire of the type Venturi has built, so the wheel’s on-Moon performance is, at present, an engineering claim rather than a measured or simulated one.

Dust sealing of the wheel actuators is named as one of the things the mission is there to test, which places it among the open questions rather than among the solved ones [11].

Power and energy

Solar generation with batteries supplied by Venturi Space in a custom enclosure of Venturi’s design, at the same physical size as those intended for FLEX [11]. Generation capacity, battery capacity, night survival and duty cycle are not published for FLIP itself. Astrolab’s press material claims lunar-night survival for the battery enclosure with no energy, insulation or temperature figures attached [11].

Thermal

Protective coatings for the solar array and the radiator are among the technologies the mission is to test, and performance in south-polar temperatures is named as an objective [11]. No temperature limits, heater strategy or radiator area is published.

The stakes of that test are set by a mechanism the Apollo program already documented [7] across all six landings: dust degradation of thermal control is nonlinear, eleven percent areal dust coverage is enough to double solar absorptance, the Lunar Roving Vehicle’s own batteries exceeded their operating temperature limits on Apollo 16 and 17 from exactly this mechanism, and ground testing consistently underestimated the problem, since brushing that cleared dust reliably in a chamber did not clear it on the Moon. FLIP’s coating and dust-sealing tests address the same failure mode on hardware that has not yet flown.

Compute and avionics

Described only as critical avionics systems carried at full size [12]. No processor, memory or radiation tolerance approach is published.

Autonomy

Not published.

Communications

Not published.

Payload and instruments

The rover carries a 30 kg payload allocation, part of which Astrolab states will go toward investigations into mitigating the risk lunar dust poses to vehicles, structures and spacecraft systems: protective-coating tests on the solar array and radiator, measurement of dust accumulation rate on surfaces, and new dust-sealing strategies for the wheel actuators [12]. No instrument has been named. No measurement technique, coating identification or success criterion has been published for any of the three, a gap consistent with the layered, largely untested state of lunar dust mitigation technology generally [8].

A published taxonomy of lunar dust mitigation technologies groups countermeasures into four layers, avoiding dust generation, preventing it sticking or entering, removing it, and tolerating it, and argues that layering several 90-percent-effective measures beats relying on one 99-percent one [8]. FLIP’s planned tests span at least two of those layers, prevention by coating and toleration by sealing, but nothing about which specific mitigation approach within either layer was chosen has been disclosed.

Modes of operation

Not published.

Ground operations

Not published.

Technologies developed

The program’s contribution is the pathfinder itself: a deliberately intermediate vehicle whose purpose is to fly the flight-sized subsystems of a larger rover on a lander that already exists, rather than waiting for the launch vehicle the larger rover needs [11]. The subsystems being proven that way are the batteries and their enclosure, the hyper-deformable airless tires, the avionics, the sensors and the software, the protective coatings on the solar array and radiator, and the dust sealing of the wheel actuators.

VIPER is the closest available comparison for what that qualification work actually involves on a lunar rover of similar class, even though VIPER never flew. Its systems integration record documents a 40 km wheel endurance test to failure over lunar simulant and rocks, slip characterization at a dedicated terrain facility, sink-tank testing in glass beads to develop entrapment-escape gaits for soft polar shadowed-region soil, and two rover-egress campaigns with Astrobotic that changed the Griffin rampway design after finding rover-lander interferences no CAD model had caught [9]. None of that class of ground test result has been published for FLIP. Software cost alone was a material factor in VIPER’s schedule, estimated with a dedicated life-cycle cost model built from historical module-sizing analogies and parametric cross-checks, an effort scale VIPER’s cancellation did not remove from the class of vehicle FLIP belongs to [10].

Nothing about FLIP’s own vehicle has been demonstrated yet, and nothing about it has been published in a form that carries a measurement.

What is not established

Every quantitative figure specific to FLIP comes from the manufacturer or its landing services partner, not from a reviewed publication, and no peer-reviewed or conference paper about the vehicle has appeared [11], [12]. Dimensions, drive speed, slope and obstacle limits, generation and battery capacity, night survival, and communications parameters are absent entirely. The wheel duty cycle cited above describes the larger FLEX vehicle, not the roughly 500 kg FLIP, and no source states whether the same tire design meets the same duty cycle at FLIP’s lower mass [3]. Delivery date has already slipped once, from an announced end of 2025 to a subsequently stated summer 2026, and no source reconciles that slip with Griffin Mission One’s own schedule [11], [12]. Nothing in the corpus describes a ground test campaign for FLIP comparable to VIPER’s wheel endurance, slip characterization or egress testing, so whether FLIP has undergone equivalent verification, or is flying without it, cannot currently be established [9].