Filament Winder with Upper Stage Tank; CPM 1.0 on Transfer Car; CPM 2.0 on Assembly Car; Close Up of Upper-Stage Tank
MOJAVE 04.03.2017---The Interorbital team has completed the CPM 2.0 tank assembly that will be used in an upcoming low-altitude guidance system test flight. CPM 2.0 is composed of four identical tanks containing the rocket's storable propellants and pressurant gas. This regulated pressure-fed configuration was chosen to increase engine performance while at the same time reducing cost and manufacturing time.
The IOS team has also completed construction and testing of a filament-winding machine, developed in-house. A tank for the liquid upper-stage option has been successfully wound and tested. As expected, the tank weight is well within the margin required for orbital applications.
In addition, the analysis and simulation for the three-stage NEPTUNE 1 (N1) has been completed. The N1 is composed of a single CPM 2.0 and two liquid upper-stages. It will be capable of placing a 10 pound (4.5 kg) payload into a 192 mi (310 km) polar orbit---perfect for the dedicated launch of the new 3U-CubeSat plus 1U-propulsion system assemblies now trending in the small satellite industry. Since the N1 launch vehicle is 36 ft (11 m) in length and weighs only 5,400 lbs (2,449 kg), it will be the smallest orbital launch vehicle in the world. The NEPTUNE 1 will also be the world's lowest-cost orbital launch vehicle, with a base price of $250,000 (academic only) per launch to a circular polar orbit at 310km.
CPM 2.0 Tank Assembly Completed; Filament Winder Tested; IOS N1 Analysis Complete!