Kinematic Design and Control Analysis of A Subsonic Ejector Nozzle with Omni-Directional Thrust Vectoring for Afterburning Turbofan Engines

A/C name	Eurofighter Typhoon, EF2000	MiG-35	Su-30MKI	Su-35S	T-50 PAK FA	F-22 Raptor	ATD-X	F-35B
Airframe	Eurofighter GmbH	RSK MiG	JSC Sukhoi Company	JSC Sukhoi Company	JSC Sukhoi Company	Lockheed Martin	TRDI, Mitsubishi Heavy Industries	Lockheed Martin
Engine	2 × EJ200	2 × RD-33MKV	2 × AL-31FP	2 × AL-41F1S	2 × AL-41F1	2 × F119-PW-100	2 × IHI XF5-1	1 × F135
Nozzle type
TVC availability
TVC part (movable)	Supersonic part	Supersonic part	All nozzle	All nozzle	Supersonic part	Supersonic part	Supersonic part	All nozzle
Axisymmetric nozzle;			Flat nozzle;
Thrust vector control;			Thrust vector in the vertical plane.

Subsonic variable nozzle of the AI-222-25F engine.

Kinematic scheme of subsonic nozzle with TVC.

Deflection of nozzle elements in a plane parallel to the triangle profile.

Deflection of nozzle elements in a plane perpendicular to the triangle profile.

Subsonic nozzle with TVC, deflected by 18°.

Kinematic scheme of ejector nozzle with TVC.

Subsonic nozzle with TVC in different positions.

Ejector nozzle with TVC during expansion and contraction.

Positions of triangle 9 in the initial and current state.

Connection scheme of lever 11 with triangle 9.

Projection of the ring onto a plane perpendicular to the axis of its rotation.

Computational scheme for the nozzle control system.

Nozzle position when the ring is rotated 2° in the horizontal plane.

Table 2.

Displacement of hydraulic cylinder pistons at δ = 2°.

δ, deg.	Θ, deg.	x₁, mm	x₂, mm	x₃, mm
2	90	0	-13.7	13.7

Nozzle position when the ring is rotated 2° in two planes.

Table 3.

Movement of hydraulic cylinder pistons at δ = 2° and Θ = 2°.

δ, deg.	Θ, deg.	x₁, mm	x₂, mm	x₃, mm
2	88	-15.6	-5.7	21.7

References

Authors

Metrics

Articles in this issue

DOI: https://doi.org/10.2478/tar-2025-0018 | Journal eISSN: 2545-2835

Journal RSS Feed

Language: English

Page range: 45 - 68

Submitted on: Aug 18, 2025

Accepted on: Oct 23, 2025

Published on: Dec 24, 2025

Published by: ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION

In partnership with: Paradigm Publishing Services

Keywords:

integration of nozzle and airframe,

turbofan engine,

subsonic nozzle,

ejector nozzle,

thrust vector control,

kinematic scheme,

control system

Related subjects:

Engineering,

Introductions and overviews,

Materials sciences, other,

Physics,

Physics, other

© 2025 Igor Oganyan, Vasyl Loginov, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

Volume 2025 (2025): Issue 4 (December 2025)

Kinematic Design and Control Analysis of A Subsonic Ejector Nozzle with Omni-Directional Thrust Vectoring for Afterburning Turbofan Engines

Figures & Tables

Table 1.

Fig. 1.

Fig. 2.

Fig. 3.

Fig. 4.

Fig. 5.

Fig. 6.

Fig. 7.

Fig. 8.

Fig. 9.

Fig. 10.

Fig. 11.

Fig. 12.

Fig. 13.

Fig. 14.

Fig. 15.

Fig. 16.

Fig. 17.

Fig. 18.

Fig. 19.

Table 2.

Fig. 20.

Table 3.

Paradigm

My account