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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Save the nozzle description file from a previous session. Thruster internal circular radius Ra. A straight sonic line is assumed to occur at the throat of the minimum length nozzle.
Click [X] to switch between the main data entry area Figure-2 and the secondary data entry area Figure Design Mach number Mdesign: Truncated aerospike nozzle base thrust is determined using two curve-fit relationships for computing base thrust.
Inclination angle from sonic line: Added the ability to include base thrust for truncated aerospike nozzles.
Webarchive template wayback links Articles needing expert attention with no reason or talk parameter Articles needing unspecified aeorspike 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 desibn 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 Likewise, for the 3-D Minimum Length Nozzle selection the “X” and “Y” coordinates of the contour represent the horizontal and radial dimensions that define the 3-D axisymmetric mesh.
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Please help improve it or discuss these issues on the talk page. Learn how and when to remove these template messages. This causes the thrust-generating exhaust to begin to expand outside the edge of the bell. For a minimum length nozzle the maximum expansion angle is equal to one-half the Prandtl-Meyer function for the design exit Aerospiks number. The recirculation zone at the base of the spike maintains the pressure in that zone to a fraction of 1 barhigher than the near-vacuum in front of the vehicle, thus giving extra thrust as altitude increases.
The resulting exit area ratio of the nozzle determined by the method of characteristics. The Mach number at the exit of the nozzle where the flow is uniform. Width of ramp for linear aerospike nozzles Lramp. Ratio of thruster internal exit area Aei to thruster throat area At.
Aerospike engine – Wikipedia
However, the user can over-ride the inserted ratio of specific heats by simply inserting his own ratio of specific heats in the data entry box. The X design was based on a lifting body shape with two revolutionary linear aerospike rocket engines and a rugged metallic thermal protection system. These values are automatically passed to the Aerospike Nozzle analysis when the command button is clicked. References Publications referenced by this paper.
Alexandrov Published A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. But this rocket design was never launched. The purpose of any engine bell is to direct the exhaust of a rocket engine in one direction, generating thrust in the opposite direction. As a by product of the oblique shock 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.
In this case the slightly upgraded J-2S engine machinery was used with a linear spike, creating the XRS Aerospike Input Data, 1st column.
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.
Input data for the results in Figure based on data from Figure-9 using AeroSpike version 2. Ratio of specific heats g: They announced a flight for August Please add a reason or a talk parameter to this template to explain the issue with the article. The X was to have been an unpiloted vehicle that took off vertically like a rocket and landed horizontally like an airplane. 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 deeign boundary from the lip of the cowl.
In the Aerospike Nozzle Data section added a display of Truncation as percent of total aerospike length. Define gas properties for inert gases, liquid propellant gases and solid fuel propellant gases or insert your own values. The two rockets were solid-fuel powered and fitted with non-truncated toroidal aerospike nozzles.
The development on the RS was formally halted in early when the X program did noozzle receive Space Launch Initiative funding. However, sometimes a sharp corner at the throat may be impractical.
The engine has a bell-shaped nozzle that has been cut in half, then stretched to form a ring with the half-nozzle now forming the bozzle of a plug. Contour plots used with permission from reference.
However, no such engine is in commercial production, although some large-scale aerospikes are in testing aeroxpike. Retrieved 30 May The exhaust, a high-temperature mix of gases, has an effectively random momentum distribution i. Since this exhaust begins traveling in the “wrong” direction i.
Determine shapes and flow properties of 3-D Minimum Length Nozzles using an approximation procedure based on 2-D results.
Several versions of the design exist, differentiated by their shapes. Return aerospioe the main start-up screen.