Static performance of a multiaxis thrust vectoring cruciform nozzle

Wing, David J.; Asbury, Scott C.

doi:10.2514/6.1991-2137

Cited by 4 publications

(5 citation statements)

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“…Several performance parameters for the multi-axis nozzle concept were tested for a range of NPR = 2-11.5. A pitch and yaw vectoring angle of 35 • and 31 • were obtained [99].…”

Section: Slot Configurationmentioning

confidence: 99%

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Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Afridi,

Khan,

Shah

et al. 2023

Energies

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Thrust vectoring innovations are demonstrated ideas that improve the projection of aerospace power with enhanced maneuverability, control effectiveness, survivability, performance, and stealth. Thrust vector control systems following a variety of concepts have been considered for modern aircraft and missiles to enhance their military performance. Short Take-off and Landing (STOL) and control effectiveness at lower aircraft speeds can be achieved by employing Fluidic Thrust Vectoring Control (FTVC). This paper summarizes a range of ideas for FTVC that have been designed and tested both computationally and experimentally to determine the thrust vectoring performance of supersonic propulsion system nozzles. The conventional method of thrust vectoring involves mechanical means to deflect the direction of flow of the exhaust gases, whereas the most recent method involves fluidic-based thrust vectoring techniques. Fluid-based thrust vectoring has the advantages of simplicity and low weight over mechanical-based thrust vectoring, which has complex geometry and adds extra weight to the aircraft. The fluidic vectoring control nozzles are divided into seven categories: shock vector, bypass shock vector, counterflow, co-flow, throat skewing, dual throat, and bypass dual throat nozzle control. This paper provides a summary of each fluidic thrust vectoring technique with its characteristics, design, classification, and different operational criteria developed to date and compares the intrinsic characteristics of each technique. Based on the present literature, it is concluded that among all the fluidic control techniques, the bypass dual-throat nozzle control can achieve better thrust vectoring performance with large vector angles and low thrust loss.

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“…Several performance parameters for the multi-axis nozzle concept were tested for a range of NPR = 2-11.5. A pitch and yaw vectoring angle of 35 • and 31 • were obtained [99].…”

Section: Slot Configurationmentioning

confidence: 99%

“…Fluidic injection for throttling and vectoring was explored in the 1950s for application to rocket nozzle systems. It actively controlled the primary flow deflection by penetrating the secondary fluid into the divergent section of the rocket nozzle [5][6][7]. However, its interest was lost.…”

Section: Introductionmentioning

confidence: 99%

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Afridi,

Khan,

Shah

et al. 2023

Energies

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show abstract

“…According to TSC, at NPR = 5.5, the vectoring angle was reported to be 8.5 • , whereas NPR less than 5.5 was reported to achieve 13.66 • [26]. According to [27], a multi-axis nozzle could deliver a 35 • pitch vectoring angle and a 31 • yaw vectoring angle at NPR = 2-11.5. Moreover, the injection angle greatly influences thrust modulation [28].…”

Section: Introductionmentioning

confidence: 99%

“…In the TSC technique, shock formation is avoided in the supersonic area of the nozzle. Due to turning the flow subsonically, the thrust losses are often low with high thrust vectoring efficiency [27,29,30].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

et al. 2023

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Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) control is a new fluidic thrust vectoring technique capable of achieving superior performance with large vector angles and low thrust loss. In this study, we analyzed the flow characteristics and performance parameters of BDTN by varying the bypass angle, nozzle convergence angle, and bypass width. The flow governing equations are solved according to a finite volume discretization technique of the compressible RANS equations coupled with the Renormalization Group (RNG) k-ϵ turbulence model for Nozzle Pressure Ratio (NPR = 2~10) to capture the significance of under-expanded and over-expanded jets. Results show that by decreasing the bypass angle from 90° to 35°, there is a 6% increase in vectoring angle while the vectoring efficiency is enhanced by 18%. However, a decrease of 3% in the thrust and discharge coefficients is also observed. When the convergence angle was increased from 22° to 37°, vectoring angle, discharge coefficient, and thrust coefficient increased by 2%, 1%, and 0.26%, respectively. Moreover, vectoring efficiency is also enhanced by 8% by reducing the convergence angle from 37° to 22°. Based on the investigated parameters, it is determined that nozzle convergence angle does not significantly influence thrust vectoring performance, however, bypass width and bypass angle have a significant effect on thrust vectoring performance.

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“…The resulting total thrust vector is therefore redirected. Related literature includes Wing et al [23,24]. The throat shifting method distinguishes itself from shockvector control by the injection of jet flow precisely at the nozzle throat, i.e., the original sonic plane.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Aerodynamic Characteristics of an Active Jets-Matrix Serving as Pitch Control Surface

2022

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To facilitate future Hypersonic Flight Vehicle (HFV) implementation with high maneuverability throughout its reentry trajectory, an Active Jets-Matrix (AJM) is designed to serve as the flapless pitch control surface. The AJM consists of four control groups composed in total of 48 supersonic nozzles. The AJM aims to utilize the jet flow-interaction-induced additional control moment to improve the control efficiency during atmospheric entry. A comparative research method is employed to study the eight simulation cases for three different HFV configurations (baseline, mechanical control surface with 30° deflection, and the AJM configuration) and two AJM control moment adjustment strategies (nozzle chamber pressure regulation and discretized nozzle group on–off control). A conventional in-house computational fluid dynamics (CFD) solver with the two-equation SST turbulence model is employed to undertake the simulation tasks. Simulation results indicate that: (a) only the AJM configuration is capable of trimming the HFV in pitch channel; (b) nonlinearity exists between the augmentation moment and the specific control variable from respective adjustment strategies; (c) the chamber pressure regulation strategy bears higher overall efficiency, while the discretized control strategy induces more intense local jet-flow interaction. With a maximum control moment augmentation of 1.58, the AJM presents itself as a competitive candidate for future HFV flapless control methods.

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Static performance of a multiaxis thrust vectoring cruciform nozzle

Cited by 4 publications

References 0 publications

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

Numerical Investigation on Aerodynamic Characteristics of an Active Jets-Matrix Serving as Pitch Control Surface

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