Multidisciplinary Approach to Linear Aerospike Nozzle Design

Korte, John J.; Salas, A. O.; Dunn, H. J.; Alexandrov, Natalia; Follett, W. W.; Orient, George Edgar; Hadid, A. H.

doi:10.2514/2.5712

Cited by 31 publications

(20 citation statements)

References 9 publications

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“…It should be noted that more realistic configurations for the airbreathing primary thruster cases should be explored by accounting for the inlet design [30,33] simultaneously for optimizing the advanced propulsion system. Additionally, structural installations [1] and weight impacts resulting from flow path modifications should be taken into account.…”

Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 99%

“…The linear aerospike nozzle is one of the most promising nozzle configurations for this kind of hypersonic vehicle because of its altitude compensating feature [1][2][3]. An engine employing an aerospike nozzle is capable of maintaining nearly optimal thrust performance from sea level to orbit, unlike that using a conventional bell-shaped nozzle, which reaches maximum performance only at one specific altitude (design altitude).…”

Section: Introductionmentioning

confidence: 99%

“…To date, numerous studies have been conducted to establish a performance prediction model, including a multidisciplinary optimization and feasibility study accounting for both aerodynamic and structural designs [1], and thrust performance and flowfield modelings based on experimental [5][6][7] and numerical simulation results [8][9][10][11]. Here, the overall thrust performance of a clustered linear aerospike nozzle composed with a rocket primary thruster in the still-air condition (i.e., at sea level or in near-vacuum) can be expressed in terms of the aerodynamics with possible drags as follows [12]: The fourth term is the thrust generated by the spike surface pressure, and the fifth term represents the spike base wake characteristics.…”

Section: Introductionmentioning

confidence: 99%

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Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Takahashi

Tomita

Tomioka

2015

53rd AIAA Aerospace Sciences Meeting

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The thrust performance of airframe-integrated linear aerospike propulsion systems for high-speed aircraft operated under off-design in-flight conditions was evaluated, based on performance prediction models established for linear aerospike nozzles by accounting for the freestream effect.The airframe configuration, equipped with a boattail appearing to the right upstream of the primary cell nozzle exit, enabled the freestream effect to be utilized for increasing the spike surface pressure.Performances of each thrust component were predicted by using the physics-based models established in separately performed studies. First, a parametric study was conducted on a rocket primary thruster with various design parameters. Then, an advanced concept with an airbreathing primary propulsion system was evaluated for its feasibility by comparing its thrust performance with that of a conventional rocket primary thruster. The benefit of the aerospike nozzle integrated into the airframe was also evaluated by comparing its thrust to a configuration without the aerospike nozzle.Results showed that the employment of the aerospike nozzle offered improved performance from takeoff to cruise phases. The advanced concept using the bypass airbreathing system for the primary thruster followed by the aerospike configuration exhibited further improvement in thrust by compensating for the boattail drag.

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Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Takahashi

Tomita

Tomioka

2015

53rd AIAA Aerospace Sciences Meeting

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“…Сопла с центральным телом (или «тарельчатые» сопла, сопла с прямолинейной верхней стенкой) находят, в основном, применение в авиапромышленности при изготовлении реактив-ных двигателей [1][2][3][4][5]. Автором предложена еще одна область практического применения со-пел с центральным телом в качестве одного из элементов конструкции горелочных устройств в нагревательных и термических печах различного назначения [6][7][8][9].…”

unclassified

Методика Расчета Горелочных Устройств На Базе Сопла С Центральным Телом

Копцев¹

2007

Вестн. Сам. гос. техн. ун-та. Сер. Физ.-мат. науки

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“…The truncation is also to attain the altitude compensating effects. [5][6][7] Allowing the engine exhaust to interfere with the ambient flow, the truncated nozzle is called an external nozzle (Fig. 2).…”

Section: Introductionmentioning

confidence: 99%

An Experimental Study on Aerodynamic Characteristics of the External Nozzle in Clustered Airframe-Integrated Propulsion System Equipped with the RLV

Isono

Tomioka

Sakuranaka

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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To elucidate the effects of non-uniformity (due to engine clustering) at the entrance of the external nozzle on wall pressure distribution and thrust performances of the external nozzle, wind tunnel tests had been conducted using room-temperature inert test gases. A clustered three cell test nozzle was used to simulate clustered engines and a non-clustered one cell test nozzle was also used as a reference. A straight expansion test ramp was used to simulate the external nozzle. Wall pressure on the test ramp and cell base pressure were measured. Test results showed that the effects of clustering on the aerodynamic characteristics of the external nozzle became remarkable with the flight altitude. This was because the magnitude of the spanwise expansion caused by cell bases became larger with the simulated altitude. Pressure thrusts generated by the external nozzle with clustered entrance were much the same as those with non-clustered entrance, when Nozzle Pressure Ratios (NPRs) were matched with each case. Therefore, we can neglect the presence of cell bases in prediction of the nozzle pressure thrusts. However, the cell base pressure always acts as the sizable drag at the external nozzle entrance, so that its value should be predictable. The present results showed that the cell base pressure could be estimated from the experimental expression.

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Multidisciplinary Approach to Linear Aerospike Nozzle Design

Cited by 31 publications

References 9 publications

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Методика Расчета Горелочных Устройств На Базе Сопла С Центральным Телом

An Experimental Study on Aerodynamic Characteristics of the External Nozzle in Clustered Airframe-Integrated Propulsion System Equipped with the RLV

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