Numerical investigation of pitch motion induced unsteady effects on transverse jet interaction

Lai, Jiang; Zhongliang, Zhao; Wang, Xiaobing; Li, Hao; Li, Qian

doi:10.1016/j.ast.2020.106005

Cited by 10 publications

(3 citation statements)

References 19 publications

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“…During high maneuvers of flight vehicles, the attitude angles change drastically with large rotational angular rates. At the same time, there are serious nonlinear coupling problems between rapid changes in aerodynamic and flight dynamic characteristics [1][2][3][4][5], which could induce strongly nonlinear, unsteady aerodynamic characteristics and uncommanded multi-degrees-of-freedom coupled motions, endanger flight safety, and even result in the loss of control [6][7][8][9][10]. The aerodynamic database for flight control law design is mainly derived from wind tunnel tests.…”

Section: Introductionmentioning

confidence: 99%

High-Speed Virtual Flight Testing Platform for Performance Evaluation of Pitch Maneuvers

Li,

Zhao

et al. 2023

Aerospace

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To research serious nonlinear coupling problems among aerodynamics, flight mechanics, and flight control during high maneuvers, a virtual flight testing platform has been developed for a large-scale, high-speed wind tunnel, based on the real physical environment, and it can significantly mitigate risks and reduce the costs of subsequent flight tests. The platform of virtual flight testing is composed of three-degrees-of-freedom model support, measuring devices for aerodynamic and motion parameters, a virtual flight control system, and a test model. It provides the ability to realistically simulate real maneuvers, investigate the coupling characteristics of unsteady aerodynamics and nonlinear flight dynamics, evaluate flight performance, and verify the flight control law. The typical test results of a pitch maneuver with open-loop and closed-loop control are presented, including a one-degree-of-freedom pitch motion and a two-degrees-of-freedom pitch and roll motion. The serious pitch and roll-coupled motion during a pitch maneuver at a high angle of attack is revealed, and the flight control law for decoupled control is successfully verified. The comparison of the test results and the flight data of a real pitch maneuver proves the reliability and capability of virtual flight testing.

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Section: Introductionmentioning

confidence: 99%

High-Speed Virtual Flight Testing Platform for Performance Evaluation of Pitch Maneuvers

Li,

Zhao

et al. 2023

Aerospace

Self Cite

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“…In a particularly relevant study, Lai et al [17] numerically studied motion-induced unsteady effects on transverse jet interaction. The potential effects were evaluated by choosing forced oscillation and free-response motion.…”

Section: Introductionmentioning

confidence: 99%

“…For example, in Refs. [9,10,17], the air vehicle's tail is equipped with support rods during the wind tunnel test, preventing the motion of the air vehicle model by the jet force. Each test can only calculate the jet force in a single state or obtain the jet flow field diagram of a single test and is inadequate to produce coupling results and the data shown in Figure 1.…”

Section: Introductionmentioning

confidence: 99%

Solving the Moment Amplification Factor of a Lateral Jet by the Unsteady Motion Experimental Method

Xue

Zhang²,

Cao

et al. 2022

Applied Sciences

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In this paper, unsteady motion tests of a lateral jet adjusting an air vehicle’s attitude are carried out. Curves of pitch moment amplification factors (KM) for a lateral jet versus angle of attack (α) are obtained using a wind tunnel free-flight test technique with a jet and data processing method. This new method overcomes the disadvantage of previous experiments that can study only one unsteady characteristic. The free-flight test technique in the proposed method ensures that the test model can be coupled in real-time with multiple parameters (unsteady flow caused by the jet, unsteady air vehicle aerodynamic force, and unsteady air vehicle motion). This approach simulates an actual air vehicle’s complete jet test process and ensures more authentic and reliable test results. In the new data processing method, continuous data curves are fitted to discrete data points, making it easier to convert the angular displacement versus time curve into the pitch moment versus α curve to obtain KM. The results show that when the pressure of the micro high-pressure gas cylinder is 2.0 MPa, KM is below 1, indicating that the lateral jet does not significantly promote the pitching moment. When the gas cylinder pressure is 4.0 MPa and the angle of attack is 5° < |α| < 16°, KM is greater than 1, and the lateral jet promotes the pitching moment. When 16° < |α| < 20°, KM is less than 1, and the lateral jet does not significantly contribute to the pitching moment. It was further found that KM decreases slowly with increasing α. When |α| > 30°, the influence of the jet on the pitching moment nearly disappears.

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Experimental study of Stagnation Pressure Reaction Control for mid-calibre non-spinning projectiles

Bouquet

Wildschut

Hakkesteegt

2021

Aerospace Science and Technology

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Numerical investigation of pitch motion induced unsteady effects on transverse jet interaction

Cited by 10 publications

References 19 publications

High-Speed Virtual Flight Testing Platform for Performance Evaluation of Pitch Maneuvers

High-Speed Virtual Flight Testing Platform for Performance Evaluation of Pitch Maneuvers

Solving the Moment Amplification Factor of a Lateral Jet by the Unsteady Motion Experimental Method

Experimental study of Stagnation Pressure Reaction Control for mid-calibre non-spinning projectiles

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