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.

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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. AeroCFD analysis of an aerospike rocket. Inclination angle from sonic line: The development on the RS was formally halted in early when the X program did not receive Space Launch Initiative funding. Since this exhaust begins traveling in the “wrong” direction i.

Since the pressure in front of the vehicle is ambient, this means dexign the exhaust at the base of the spike nearly balances out with the drag desihn by the vehicle. Specify whether the nozzle is 2-D or 3-D by clicking either the 2-D characteristics or 3-D approximation option buttons. The design was abandoned desivn Firefly Space Systems went bankrupt.

The RS was to power the VentureStar single-stage-to-orbit vehicle. Wikimedia Commons has media related to Aerospike rocket engines. 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.

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Input data for the results in Figure based on data from Figure-9 using AeroSpike version 2. In the toroidal aerospike the spike is bowl-shaped with the exhaust exiting in a ring around the outer rim. Radius of the internal portion of the thruster duct from point 1 throat to point 2 Ra. Show or hide the main data window from view or from being printed.

Aerospike Nozzle and Minimum Length Nozzle Design

For a detailed discussion of the method of characteristics please refer to the reference, Modern Compressible Flow, With Historical Perspective, by John D. In this case the slightly upgraded J-2S engine machinery was used with a linear spike, creating the XRS Output all flow variables to the printer or text file for use with spreadsheet applications.

Aerospike image clipped from QuickTime movie. The bell redirects exhaust moving in the wrong direction so that it generates thrust in aeroospike correct direction. Annular aerospike designed to producepounds of thrust. Added a hybrid rocket motor propellant having the following fuel and oxidizer to the list of combustion gases: KorteFarrokh Mistree Retrieved 30 May When performing an MLN analysis the only values required are the Inclination angle from the sonic line see aboveDesign Mach number Aerosoikeand throat diameter Dt.

References Publications referenced by this paper. Define gas properties for inert gases, liquid propellant gases and solid fuel propellant gases or insert your own values. Save the nozzle description file from a previous session.

Save all flow properties X,Y, Mn etc at each characteristic mesh point to a data file.

Multidisciplinary Approach to Aerospike Nozzle Design

The vehicle also was to have had lightweight components and fuel tanks built to conform to the vehicle’s outer shape. The X was to have been an unpiloted vehicle that took off vertically aerospi,e a rocket and landed horizontally like an airplane.


Width of ramp for linear aerospike nozzles Lramp. By using this site, you agree to the Terms of Use and Privacy Policy. Due to lack of funding, the concept is still undeveloped.

Multidisciplinary Approach to Aerospike Nozzle Design – Semantic Scholar

Retrieved 4 February Click the UpDown command button to move a locator from point to point in the flow field. Ratio of the chamber pressure Pc to the atmospheric pressure Nozz,e. Ratio of thruster internal exit area Aei to thruster throat area At. For maximum accuracy simply insert 0.

Found by interation of Equation 1 and displayed in lower data region. Exhaust recirculation in the base zone of the spike can raise the pressure in that zone to nearly ambient. Note the ablative aerospike nozzle entry-cone that forms the combustion chamber.

Salas and Herbert Dunn and Natalia M. It belongs to the class of altitude compensating nozzle engines. The terminology in the literature surrounding this subject is somewhat confused—the term aerospike was originally used for a truncated plug nozzle with a very rough conical taper and some gas injection, forming an “air spike” to help make up for the absence of the plug tail.

For pressure ratio, Pc is the thruster chamber pressure and Pa is the local atmospheric pressure. Citations Publications citing this paper.