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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For the 2-D Minimum Length Nozzle selection the “X” and “Y” coordinates of the nozzle contour represent the horizontal and vertical dimensions that define the 2-D characteristic mesh. The outer boundary angle from the edsign of the thruster cowl to the end of the external ramp increases as altitude increases.
A nearly minimum length nozzle may be generated by specifying a very small but finite radius of curvature at the throat with the inflection point of the throat-curve just downstream of the throat.
The disadvantages of aerospikes seem to be extra weight for the spike, and increased cooling requirements to the extra heated area, the spike. This design continues to evolve so updated information will appear as results are available. From This Paper Figures, tables, and topics from this paper. Define the angle the sonic section of the thruster makes with the axis of the aerospike nozzle.
Multidisciplinary Approach to Aerospike Nozzle Design
Technical problems with the composite liquid hydrogen tank resulted in the program being cancelled in February In this case the slightly upgraded J-2S engine machinery was used with a linear spike, creating the XRS See Figure 1 below. The two rockets were solid-fuel powered and fitted with non-truncated toroidal aerospike nozzles.
Salas and Herbert Dunn and Natalia M. Instead of firing the exhaust out of a small hole in the middle of a bell, an aerospike engine avoids this random distribution by firing along the outside edge of a dexign protrusion, the “spike”, which serves the same function as a traditional engine bell.
MunakataShigeru Sato Ratio of the chamber pressure Pc to the atmospheric pressure Pa. However, sometimes a sharp corner at the throat may be impractical. Radius that defines the projected area of the aerospike nozzle Re.
Aerospike engine – Wikipedia
A minimum length nozzle has the smallest possible throat-to-exit length that is still capable of maintaining uniform supersonic flow at the exit. Retrieved from ” https: Since the pressure in front of the vehicle is ambient, this means that the exhaust at the base of the spike nearly balances out with the drag experienced by the vehicle. Requires QuickTime from Apple. Citations Publications citing this paper.
The aerospike nozzles and solid rocket motors were developed and built by the rocket motor division of Cesaroni Technology Nnozzlenorth of Toronto, Ontario.
The thrust at the base part of the nozzle can be ignored at low altitude. The ideal contour or shape of the external ramp of the aerospike nozzle is determined using isentropic supersonic flow theory.
For maximum accuracy simply insert 0. Rocketdyne conducted a lengthy series of tests in the s on various designs. Radius to lip of cowl Re: However, no such engine is in commercial production, although some large-scale aerospikes are in testing phases.
The development on the RS was formally halted in early when the X program did not receive Space Launch Initiative funding. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. A new company, Firefly Aerospacehas replaced the aerospike engine with a conventional engine in the Alpha 2. The Mach number at the exit of the nozzle where the flow is uniform. For pressure ratio, Pc is the thruster chamber pressure and Pa is the local atmospheric pressure.
Aerospike rocket motor primed and ready for hot fire testing. DalleJames F. Selected from a pull-down menu or user-defined. Determine shapes and flow properties of 3-D Minimum Length Nozzles using an approximation procedure based on 2-D results. Read the nozzle description file from a previous session. The X was to have been an unpiloted vehicle that took off vertically like a rocket and landed horizontally like an airplane.
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The ratio of specific heats, gas constant Rgaschamber pressure Pcand pressure ratio PR are required for the Aerospike Nozzle analysis.
This effectively behaves like an “altitude compensator” in that the size of the bell automatically compensates as air pressure falls. 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. Total length of the aerospike nozzle from the origin throat of the thruster to the end of the ramp. 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.