AEROSPIKE NOZZLE DESIGN PDF

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

Aerospike Nozzle and Minimum Length Nozzle Design

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. A new company, Firefly Aerospacehas replaced the aerospike engine with a conventional engine in the Alpha 2. Selected from a pull-down menu hozzle user-defined.

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. When performing an MLN analysis the only values required are the Inclination angle from the sonic line see aboveDesign Mach number Mdesignand throat diameter Dt. Please help to improve this article by introducing more precise citations. The ideal contour or shape of the external ramp of the aerospike nozzle is determined using isentropic supersonic flow theory.

This design concept was developed using AeroSpike 2. Through demonstration flight and ground research, NASA’s X program was to have provide the information needed for industry representatives such as Lockheed Martin to decide whether to proceed with the development of a full-scale, commercial RLV program.

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The cancellation of the Lockheed Martin X nozlze the federal government in decreased funding availability, but aerospike engines remain an area of active research.

The ratio of specific heats, gas constant Rgaschamber pressure Pcand pressure ratio PR are required for the Aerospike Nozzle analysis. 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.

This rocket was designed to test several components of their Haas 2CA at a lower cost.

The disadvantages of aerospikes seem to be extra weight for the spike, and increased cooling requirements to the extra heated area, the spike. Define the angle the sonic section of the thruster makes with the axis of the aerospike nozzle.

Exhaust recirculation in the base zone of the spike areospike raise the pressure in that zone to nearly ambient. Small-scale aerospike engine development using a aeroapike rocket propellant configuration has been ongoing by members of the Reaction Research Society. AeroCFD analysis of an aerospike desivn. Propellant Gases Available Inert Gases. The nozzle data entry area is displayed by default. The purpose of any engine bell is to direct the exhaust of a rocket engine in one direction, generating thrust in the opposite direction.

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. Several versions of the design exist, differentiated by their shapes. Chamber pressure whose units depend on the units selected.

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Specify whether the nozzle is 2-D or 3-D by clicking either the 2-D characteristics or 3-D approximation option buttons. Aerospikes work relatively poorly between Mach 1—3, where the airflow around the vehicle has reduced the pressure, thus reducing the thrust. A straight sonic line is assumed to occur at the throat of the minimum length nozzle.

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Aerospike Input Data, 1st column. Show or hide the main data window from view or from being printed. The bell redirects exhaust moving in the wrong direction so that it generates thrust in the correct direction.

Note the ablative aerospike nozzle entry-cone that forms the combustion chamber. Liquid Fuel Propellant Gases.

Design Mach number Mdesign: Found by interation of Equation 1 and displayed in lower data region. Click the UpDown command button to move a locator to one of seven points in the flow field.

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 wedge-shaped protrusion, the “spike”, which serves the same function as a traditional engine bell. Ratio of the chamber pressure Pc to the atmospheric pressure Pa.

Aerospike engine

It uses carbon composite materials and uses the same basic design for both stages. Save the nozzle description file from a previous session.

See Figure 1 below.