Mk.IIb
The Mk.IIb engine was a small scale test bench hybrid rocket motor that rapidly and effectively conducted static tests for newly developed technologies that would appear on future Mk engines
Mk.IIb
The Mk.IIb engine was designed to be a rapid test platform and allow for rapid turnaround times for multiple tests per day. It’s construction allowed it to be easily taken apart and put back together and required significantly less nitrous oxide than full scale flight engines. These came together to allow for Mk.IIb to be a cheap and effective test for future propulsion technologies.
By its retirement, the Mk.IIb engine had one of the most successful and expansive test campaigns that BURPG had ever conducted. Completing three cold flow tests and seven hot fire tests. The Mk.IIb tested several nozzle designs and materials, fuel grain regression characteristics, throttling performance, long duration nozzle models, and electronic ground systems. Most impressively, the Mk.IIb had the first successful implementation of liquid injection thrust vector control (LITVC) on a hybrid rocket motor.
Without the creation of the Mk.IIb engine, BURPG can firmly say it would not have been able to accomplish all it has.
Engine Overview
Streamlined Manufacturing
Mk.IIb fuel grain is cast as one continuous piece. Once it solidifies, the fuel grain is cut into four equally sized segments and then glued together with HTPB in order to resemble the Mk.V fuel grain. The fuel grain uses a single port geometry commonly found on amateur and high powered solid rocket motors.
System Validation
The Mk.IIb ground system has been used to test Hyperion, an electronics board that controls the ground infrastructure for Starscraper. The Ground Operations Device (GOD) Box is a housing structure that protects Hyperion and the flight computer during operation. The GOD Box routes all cables and allows for simple electronics setup at each test.
Facts & Figures:
| 200 lbf | LITVC |
|---|---|
| Mk.IIb's small size allowed for rapid testing and development | Liquid injection thrust vector control was tested on a hybrid for the first time with Mk.IIb |
| 20 sec | 7 Hotfires |
| Mk.IIb burned for over 20 seconds continuously, with thrust vector control running throughout the burn. | Mk.IIb completed seven back-to-back hotfires without a failure. |
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