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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Several versions of the design exist, differentiated by their shapes. Showing of 23 references. This causes the thrust-generating exhaust to begin to expand outside the edge of the bell. The development on the RS was formally halted in early when the X program did not receive Space Launch Initiative funding. Nozzle Device Component Nonlinear system Mathematical optimization. However, frequently, a full-length plug nozzle is now called an aerospike.
PadulaJohn J. Ratio of chamber pressure to thruster exit pressure. Aerospike image clipped from QuickTime movie. Skip to search form Skip to main content.
Specify custom or user-defined gases by inserting Ratio of specific heats g in the Minimum Length Nozzle Data section. In JuneARCA announced that they would fly aerispike Demonstrator3 rocket to space, using a linear aerospike engine. The ideal contour or shape of the external ramp of the aerospike nozzle is determined using isentropic supersonic flow theory. SimpsonTimothy M. 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.
For a detailed discussion of the method of characteristics please refer to the reference, Modern Compressible Flow, With Historical Perspective, by John D. The single-engine tests were a success, but the program was halted before the nzzle for the two-engine setup could be completed.
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Aerospike generated using AeroSpike 2. Figure-9, XRS aerospike rocket engine description data repeated in Figure However, sometimes a sharp corner at the throat may be impractical. The user only needs to click the Plot button to see a new contour plot of the results or the UpDown button to see flow results at any of the characteristic mesh points.
Aerospike Input Data, 1st column. Rocketdyne conducted a lengthy series of tests in the s on various designs. Salas and Herbert Dunn and Adrospike M.
This angle is used to compute the slope of the first characteristic from the edge of the throat. Topics Discussed in This Paper. Ratio of the chamber pressure Pc to the atmospheric pressure Pa. When placing this tag, consider associating this request with a WikiProject.
Exploded view of the aerospike rocket motor. Requires QuickTime from Apple Computer. Found by interation of Equation 1 and displayed in lower data region. A minimum length nozzle has the smallest possible cesign length that is still capable of maintaining uniform supersonic flow at the exit.
The design was abandoned after Firefly Space Systems went bankrupt.
Multidisciplinary Approach to Aerospike Nozzle Design – Semantic Scholar
A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used vesign determine the structural response and weight.
Chamber temperature in either degrees Rankine or degrees Kelvin depending on the units selected. The Mach number at the exit of the nozzle where the flow is uniform.
As the vehicle climbs to higher altitudes, the air pressure holding the exhaust against the spike decreases, as does the drag in front of the vehicle. For a minimum length nozzle the maximum expansion angle is equal to one-half the Prandtl-Meyer function for the design exit Mach number.
For maximum accuracy simply insert 0. For pressure ratio, Pc is the thruster chamber pressure and Pa is the local atmospheric pressure. 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. Please help improve it or discuss these issues on the talk page.
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