Propulsion system integration and thrust vectoring aspects for scaled jet UAVs

Bougas, Lykourgos; Hornung, Mirko

doi:10.1007/s13272-013-0076-x

Cited by 11 publications

(7 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The DTN designs that were used in this work were scaled versions of the design provided in a study by Bougas and Hornung (2013), as shown in Fig. 2 with the letter codes (A, B, C etc.…”

Section: Experimental Modelsmentioning

confidence: 99%

“…The direction of this motion is strictly related to the angle that the jet is issued at. Altering this angle by means of jet vectoring methods particularly for thrust vectoring purposes has been subject to many studies and mainly classified as mechanical and fluidic vectoring concepts (Bougas and Hornung 2013).…”

Section: Introductionmentioning

confidence: 99%

“…DTN design is basically a nozzle consisting of two identical throats in which the control fluid is injected from the first throat to make the jet attach to the opposite inner wall of the nozzle's recessed cavity due to separation and the vectored jet leaves the nozzle from the second throat. Figure 1 shows the Mach contours obtained through the preliminary numerical analyses which were done in the early phase of this study for no control and 2% fluidic injection cases on a DTN design based on the dimensions given in a study by Bougas and Hornung (2013). In this figure, injection location and the separated region can clearly be seen while the primary jet is vectored 8° relative to the x-axis.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Effect of Geometry Modifications on the Vectoring Performance of a Controlled Jet

Tomac¹

2017

JAFM

View full text Add to dashboard Cite

Jet vectoring performances of ten different designs with various depths and geometrical outlines were quantified through constant temperature anemometry measurements for a Reynolds number range from 10,000 to 30,000 by using passive and active flow control methods at cold flow. The reference design was based on NASA's double throat nozzle concept and a self-injection double throat nozzle design that uses similar flow control concept as the reference design, were also tested for performance comparison. Furthermore, jet vectoring performance of a single throat design, utilizing Coanda effect for jet vectoring, was also quantified. Results indicated jet vectoring angles starting from 2° up to 47° for a control jet flow rate range from 1% up to 10% with respect to the primary jet flow rate in the investigated Re range. Maximum jet vectoring angle was achieved with a single throat design which incorporates small step geometry before the Coanda surface for more effective flow attachment and these results were compared with the vectoring performance of the double throat nozzle designs.

show abstract

“…The DTN designs that were used in this work were scaled versions of the design provided in a study by Bougas and Hornung (2013), as shown in Fig. 2 with the letter codes (A, B, C etc.…”

Section: Experimental Modelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effect of Geometry Modifications on the Vectoring Performance of a Controlled Jet

Tomac¹

2017

JAFM

View full text Add to dashboard Cite

show abstract

“…In today's aviation world, the most commonly used thrust vectoring types are given in Figure 1. Among them Coanda methods [2,3] are most suitable for new generation Vertical Take-Off and Landing/ Short Takeoff and Landing (VTOL/STOL) air vehicles, with their quick responses they can have a huge impact even on futuristic city transportation systems in the following decades.…”

Section: Introductionmentioning

confidence: 99%

“…Figure 1. Thrust vectoring concepts [3] Although general purpose fluidic thrust vectoring is utilized for enhancing thrust maneuverability since late 1960s [10], the HOMER design is highly immature and open to improvement with its only 10 years of background. In this paragraph, the most recent article/project of the study groups working on HOMER design is taken into account.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation and numerical verification of Coanda effect on curved surfaces using co-flow thrust vectoring

Kara

Erpulat

2021

International Advanced Researches and Engineering Journal

View full text Add to dashboard Cite

In this study, a popular co-flow thrust vectoring system, which is superior to typical Coanda nozzles with one main jet, is examined experimentally and compared with 2D and 3D computational fluid dynamics results. High Speed Orienting Momentum with Enhanced Reversibility nozzle concept is the base design to proposed configuration which uses a control jet additional to the main jet for better and active enhancement on the flow vectoring and streamlined side-walls resulted in less flow blockage. This comparatively novel concept is utilized in an experimental setup to direct the thrust of aerial vehicles. The system includes two inlets (inlet1, inlet2) with different jet velocities and one pintle to separate and smoothly direct these jets and a converging-diverging nozzle to enclose these components. Experimental study is accomplished with four different configurations of inlet1 and inlet2 as 15 m/s and 10 m/s; 20 m/s and 10 m/s; 30 m/s and 10 m/s, and 45 m/s and 10 m/s, respectively. The tangential velocities on the curved surfaces are successfully measured utilizing a micro-manometer (Pitot tube) so that attachments/detachments of jets on the exit walls and deflection angles are calculated for each inlet velocities. The current experimental study also revealed that 3D assumption of computational fluid dynamics of Coanda effect is highly accurate and deflection angle results are not far from experimental results with the average deficit of only 5.44 %. As the result, 3D verification study resembles to experimental study in terms of deflection angles for all configurations.

show abstract

Numerical investigation of a Coandă-based fluidic thrust vectoring system for subsonic nozzles

Schwagerus,

Stößel,

Krummenauer

et al. 2023

CEAS Aeronaut J

View full text Add to dashboard Cite

The numerical investigation of a novel subsonic thrust concept for fluidic thrust vectoring (FTV) of jet engines is the subject of this publication. FTV possibly offers advantages over conventional mechanical thrust vector control such as decreased complexity, mass and maintenance costs. The operating principle of the FTV nozzles under investigation at the Institute of Jet Propulsion is based on the Coandă effect. The applied concept of thrust vectoring uses dedicated secondary flow channels which are mounted in parallel around the nozzle inner cone or the nozzle wall. If required, bleed air, provided by extraction from the engine compressor or from an external source, is injected at a specific nozzle pressure ratio at the nozzle throat $$A_8$$ A 8 through these secondary ducts, resulting in the redirection of the secondary jet towards the convex Coandă surface. The interaction between the primary mass flow and the secondary jet leads to a redirection of the primary exhaust mass flow of the engine and thus to a vectoring of the exhaust flow. In this paper, the influence of different nozzle geometric parameters and different operating points are investigated within an extensive parametric study applied to a convergent two-dimensional thrust vectoring nozzle using computational fluid dynamics tools. Thrust vector deflection of up to $${20}^{\circ }$$ 20 ∘ at a maximum secondary to primary mass flow ratio of $$10 \%$$ 10 % is achieved. Reducing this mass flow rate to $$5 \%$$ 5 % still yields vectoring angles of up to $${15}^{\circ }$$ 15 ∘ whereby similar deflection angles compared to conventional mechanical thrust vectoring systems are achievable.

show abstract

Propulsion system integration and thrust vectoring aspects for scaled jet UAVs

Cited by 11 publications

References 11 publications

Effect of Geometry Modifications on the Vectoring Performance of a Controlled Jet

Effect of Geometry Modifications on the Vectoring Performance of a Controlled Jet

Experimental investigation and numerical verification of Coanda effect on curved surfaces using co-flow thrust vectoring

Numerical investigation of a Coandă-based fluidic thrust vectoring system for subsonic nozzles

Contact Info

Product

Resources

About