A simplified design and optimization method of aerospike nozzle contour and the results of tests and numerical simulation of aerospike nozzles are presented. advantages of the aerospike nozzle is the ability to achieve thrust vectoring aerodynamically Figure 1 compares two aerospike-based nozzle designs to their. design strategy. Introduction. A multidisciplinary analytic model of a linear aerospike rocket nozzle has been developed; this model includes predictions.

Author: Nemuro Arashigore
Country: Republic of Macedonia
Language: English (Spanish)
Genre: Health and Food
Published (Last): 13 May 2005
Pages: 138
PDF File Size: 18.9 Mb
ePub File Size: 17.44 Mb
ISBN: 231-2-23911-901-8
Downloads: 11795
Price: Free* [*Free Regsitration Required]
Uploader: JoJosho

The plots in Figure 4 and Figure 5 illustrate the relationship between Patm verses PR and Pb verses Percent Truncation for the computation of base thrust, total thrust and thrust coefficient.

Aerospike length from origin Lnozzle. The two rockets were solid-fuel powered and fitted with non-truncated toroidal aerospike nozzles. It belongs to the class of altitude compensating nozzle engines. Webarchive template wayback links Articles needing expert attention with no reason or talk parameter Articles needing unspecified expert attention Articles needing expert attention from June All articles needing expert attention Articles lacking in-text citations from February All articles lacking in-text citations Articles with multiple maintenance issues Wikipedia articles needing clarification from April All articles lacking reliable references Articles lacking reliable references from August Commons category link is on Wikidata All articles with dead external links Articles with dead external links from August Since this exhaust begins traveling in the “wrong” direction i.


The Clustered Bell Aerospike Engine: Ratio of the chamber pressure Pc to the atmospheric pressure Pa.

Aerospike engine – Wikipedia

Designn, pages to Specify either annular aerospike geometry or linear aerospike geometry by clicking one of two option buttons in the secondary data entry area. Read the nozzle description file from a previous session. Input Variable Definitions 1. Due to lack of funding, the concept is still undeveloped.

Showing of 23 references. In the toroidal aerospike the spike is bowl-shaped with the exhaust exiting in a ring around the outer rim.

Return to the main start-up screen. A number of inert gases, liquid propellants and solid fuel propellants are available.

Refresh the displayed analysis to the default analysis seen during start-up. The single-engine tests were a success, but the program was halted before the testing for the two-engine setup could be completed.

This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. A minimum length nozzle has the smallest possible throat-to-exit length that is still capable of maintaining uniform supersonic flow at the exit. Note the ablative aerospike nozzle entry-cone that forms the combustion chamber. This angle is used to compute the slope of the first characteristic from the edge of the throat. For pressure ratio, Pc is the thruster chamber pressure and Pa is the local atmospheric pressure.


See Figure 1 below. Aerospike nozzle total thrust is computed using the following equations knowing PR and percent truncation.

Aerospike engine

Click the UpDown command button to move a locator from point to point in the flow field. Requires QuickTime from Apple.

Aerospike generated using AeroSpike 2. Added the ability to include base thrust for truncated aerospike nozzles.

KorteHerbert DunnA. Chamber pressure whose units depend on the units selected. Thruster internal circular radius Ra: The purpose of any engine bell is to direct the exhaust of a rocket aeroospike in one direction, generating thrust in the opposite direction.

DalleJames F. Exploded view of the aerospike rocket motor. The user only needs to click the Plot button to see a new contour plot of ddsign results or the UpDown button to see flow results at any of the characteristic mesh points.

This page was last edited on 5 Novemberat Selected from a pull-down menu or user-defined. Gas constant of exhaust Rgas: For a nearly minimum length nozzle simply specify the streamline from the throat-curve desjgn the curvature lines up with the nozzle wall shape generated by MLN.