Propulsion

Thruster-based control typically requires a substantial engineering effort in order to mitigate an important issue: the control system tends to use many thruster pulses to accomplish what a single thruster pulse could do instead. This fundamental problem...

Innovators at the NASA Armstrong Flight Research Center have developed a compressor-generator-motor turbojet design concept that integrates the generator with the aerodynamic blade structures of the compression section of turbomachinery. This reduces weight and volume...

Anon-catalytic pyrotechnic ignition system was developed for advanced green monopropellant systems operating with hydroxylammonium nitrate (HAN)-based monopropellant AF-M315E. This technology will provide increased performance and new operating regimes for future...

During inspection of pressure vessels and other large structures, an industry-accepted fixture is used to hold the search unit a predetermined distance from the area of interest under inspection. This fixture is then moved manually around the area of interest so that data can be collected and stored...

The purpose of this work was to create a safe, green, controllable solid rocket motor that can be pulsed a number of times with electricity to control the ignition and extinguishment times to produce a required thrust or impulse bit. The innovation features an Electric Solid...

There are many applications where a high power-to-weight engine is either necessary or helpful. Uses for this type of engine range from handheld power equipment, to motorcycles and aircraft — uses multiply when fuel efficiency, compactness, and versatility are added. Currently, there are few viable options available to...

Hydrazine has been the standard baseline liquid monopropellant for space propulsion over many decades since replacing hydrogen peroxide. Hydrazine was preferred over peroxide due to its easier storability and higher performance. Like peroxide, hydrazine can be readily decomposed by...

NASA's Jet Propulsion Laboratory has developed a Hall thruster with a variable-area discharge chamber that improves the performance and lifetime of the thruster. Conventional Hall thrusters have poor ionization efficiency, which limits the thrust-to-power ratio...

Small satellites, launched as secondary payloads, are increasingly being fielded. Advances in liquid rocket propulsion that enhance the on-orbit maneuverability, increase the on-orbit life, and decrease the time between identified need for and deployment of such spacecraft are of great value....

Two different types of electrostatic thrusters are used to propel spacecraft: ion thrusters and Hall-effect thrusters. Ion thrusters have the benefit of relatively high exhaust velocities with higher overall thrust efficiencies. Hall-effect thrusters typically offer higher thrust-to-power ratios, but they operate...

Innovators at NASA's Glenn Research Center have developed several new technological innovations to improve the capability of Hall-effect thrusters, which are used primarily on Earth-orbiting satellites and can also be used for deep-space robotic vehicles. Hall thrusters are susceptible to discharge channel...

Innovators at NASA's Glenn Research Center have developed an engine control mode that improves an engine's responsiveness to throttle commands during emergency landing conditions. The high speed idle (HSI) control mode increases the speed of the engine's fan and core shafts, allowing faster response and increased...

The problem to be resolved in this work was the use of radial control drums as the sole active reactivity control system for nuclear thermal propulsion, which results in significant rocket performance changes during full-power operation. This can result in large inefficiencies in...