Aerospike nozzles are rather unique, in that they are somewhat of a reverse version of the standard bell nozzle. Instead of using a shroud to contain the exit flow. Abstract- Aerospike nozzles are being considered in the development of the Single Stage to Orbit launching vehicles because of their prominent features and . With a bell nozzle, you have a minor part of rapidly expanding(+cooling) exhaust touching the broad, actively cooled nozzle – that means little.

Author: Zulumi Kajigul
Country: Nigeria
Language: English (Spanish)
Genre: Health and Food
Published (Last): 26 November 2018
Pages: 180
PDF File Size: 16.94 Mb
ePub File Size: 11.50 Mb
ISBN: 171-8-92540-718-6
Downloads: 40721
Price: Free* [*Free Regsitration Required]
Uploader: Vira

So it must be cooled which is difficult. Liquid Fuel Propellant Gases. Instead of using a physical shroud to contain the exhaust flow, the outer boundary is defined naturally by the local back-pressure. This effectively behaves like an “altitude compensator” in that the size of the bell automatically compensates as air pressure falls.

All important flow properties are displayed in real time as the locator moves from point to point in the flow field described by the characteristic mesh of the aerospike.

Aerospike engine

Show or hide the main data window from view or from being printed. I would add aefospike engine topology can improve atmospheric specific impulse, which is expressly what aerospikes are supposed to do. Powered by Create your own unique website with customizable templates. It gives no overall thrust, but this part of the nozzle also doesn’t lose thrust by forming a partial vacuum.

The annular aerospike rocket motor pictured above left is a design developed and rendered by Richard Caldwell Rocket Nut intended to producepounds of thrust at sea level.

Then, depending on whether the flow is underexpanded or if the flow is overexpanded AeroSpike performs either a Prandtl-Meyer expansion analysis or an oblique shock wave analysis to determine the angle of the outer flow boundary from the lip of the cowl. Click the UpDown command button to move a locator to one of seven points in the flow field.

Aerospike Nozzle and Minimum Length Nozzle Design

The purpose of any engine bell is to direct the exhaust of a rocket engine in one direction, generating thrust in the opposite direction. However, sometimes a sharp corner at the throat may be impractical. Linear aerospikes provide an advantage over toroidal aerospikes, in that the turbomachinery and combustion chamber actually fit within the inner section of the nozzle, allowing for the entire assembly to be tilted from side to side for thrust vectoring purposes, which are discussed on the next page.


It was planned to reach altitudes of up to 50 miles and nozlze hypersonic speeds. Truncated aerospike zerospike base thrust is determined using two curve-fit relationships for computing base thrust. Nozzls this case the slightly upgraded J-2S engine machinery was used with a linear spike, creating the XRS A number of inert gases, liquid propellants and solid fuel propellants are available.

As a by product of the oblique nozzel wave analysis AeroSpike determines the shock wave angle for overexpanded flow and plots both the outer boundary contour and the initial shock wave from the lip of the cowl. But in the meantime, they also want to gather data on how it performs in flight.

The aerospike engine is a time-honored concept. You have a lot of extra-hot, very dense gas in contact with the narrow spike that must pass all the coolant and dissipate the heat somehow, not to nozzke.

Aerospike Input Data, 1st column. They just onzzle run continuously for as long as a typical rocket needs to lift payload to orbit. Post as a guest Name. The remaining expansion fan is divided into six increments. Learn how and when to remove these template messages. Dimensional data for this analysis are based on Boeing’s results for the XRS linear aerospike rocket engine where vacuum thrust and Isp arelbf and The cancellation of the Lockheed Martin X by the federal government in decreased funding availability, but aerospike engines remain an area of active research.

Radius that defines the projected area of the aerospike nozzle Re. This design has the advantage of being stackable, allowing several smaller engines to be placed in a row to make one larger engine while augmenting steering performance with the use of individual engine throttle control. This results in a smoothly varying exit flow area which is always optimized as back-pressure changes.

The Mach number at the exit of the nozzle where the flow is uniform. In the Aerospike Nozzle Data section added areospike display of Distance from end of thruster to end of ramp. Send all flow propeties X, Y, Mn etc at each characteristic mesh point to the printer. In the Aerospike Nozzle Data section added a display of Distance from throat origin to end of thruster.


If the exhaust is allowed to escape in this form, only a small part of the flow will be moving in the correct direction and thus contribute to forward thrust. Ratio of thruster internal exit area Aei to thruster throat area At.

Finally, check the Check to Include base thrust check box to include base thrust for the determination of total thrust and thrust coefficient CF for truncated aerospike nozzles. These measures are not only allowing for the commercialization of Low-Earth Orbit LEObut are opening up possibilities that were previously thought to be impossible for the time being — like space-based solar power and space habitats!

Instead of using a shroud to contain the exit flow, aerospikes direct the flow along the exterior of the nozzle. Aerospikr Results, 2nd column. The RS was to power the VentureStar single-stage-to-orbit vehicle. Added a hybrid rocket motor propellant having areospike following fuel and oxidizer to the list of combustion gases: Figure-9, XRS aerospike rocket engine description data repeated in Figure Ambient air pressure also imparts a small pressure against the exhaust, helping to keep it moving in the “right” direction as it exits the engine.

In the toroidal aerospike the spike is bowl-shaped with the exhaust exiting in a ring around the outer rim.

Due to unavailable thruster dimensions and conflicting dimensional and performance information provided by NASA and relevant technical papers this aerospike rocket engine analysis is an approximation. This article needs attention from an expert on the subject. I know this is an old post but check this: The disadvantages of aerospikes seem to be extra weight for the spike, and increased cooling requirements to the extra heated area, the spike.

Inclination angle from sonic line: