Trim Calculation of the CH-53 Helicopter Using Numerical Continuation Method

Cao, Yihua; Cao, Lei; Wan, Shaofeng

doi:10.2514/1.g000180

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Figure 1 Coaxial Helicopter Prototype With a New Coaxial Ro1

Helicopter Flight Mechanics Model1

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2017

2024

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Cited by 5 publications

(2 citation statements)

References 17 publications

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“…After constructing the model, it needs a technical tool to evaluate the impact on dynamic characteristics under the proposed trim method. Frequency response analysis has widely been used to validate the dynamic response with flight data in different rotorcraft [14][15][16]. These applications confirm our confidence that frequency response analysis is indeed superior benefit to dynamic characteristics.…”

Section: Figure 1 Coaxial Helicopter Prototype With a New Coaxial Rosupporting

confidence: 59%

A Trimming Methodology for a New Coaxial Rotor Configuration of Robotic Helicopter Based on Rotor's Thrust Ratio

Dong¹,

Liu²,

Chen³

et al. 2017

IJCA

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Section: Figure 1 Coaxial Helicopter Prototype With a New Coaxial Rosupporting

confidence: 59%

A Trimming Methodology for a New Coaxial Rotor Configuration of Robotic Helicopter Based on Rotor's Thrust Ratio

Dong¹,

Liu²,

Chen³

et al. 2017

IJCA

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“…The detailed information on conducting trim calculations using the numerical continuation method can be found in Ref. [29].…”

Section: Helicopter Flight Mechanics Modelmentioning

confidence: 99%

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Cao

Qin

Tan

et al. 2022

JMSE

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Landing a helicopter to the ship flight deck is most demanding even for the most experienced pilots and modeling and simulation of the ship-helicopter dynamic interface is a substantially challenging technical problem. In this paper, a coupling numerical method was developed to simulate the fully coupled ship-helicopter flow-field under complete wind-over-deck conditions. The steady actuator disk model based on the momentum source approach and the resolved blade method based on the moving overset mesh method were employed to model the rotor. Two different ship-helicopter combinations were studied. The helicopter flight mechanics model was established and then the influences of coupled airwake on the helicopter were analyzed. Finally, based on the derived rejection criterion of safe landing and the developed numerical method, the flight envelopes for these two ship-helicopter combinations were predicted. The steady actuator disk model was found to be effective in the study of helicopter operations in the shipboard environment. The calculated flight envelopes indicate that an appropriate wind direction angle is beneficial to increasing the allowable maximum wind speed and the operating boundary is affected by the rotation direction of the main rotor.

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Modeling and Simulation of Ship–Helicopter Dynamic Interface: Method and Application

Cao

Qin

2022

Arch Computat Methods Eng

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Trim Calculation of the CH-53 Helicopter Using Numerical Continuation Method

Cited by 5 publications

References 17 publications

A Trimming Methodology for a New Coaxial Rotor Configuration of Robotic Helicopter Based on Rotor's Thrust Ratio

A Trimming Methodology for a New Coaxial Rotor Configuration of Robotic Helicopter Based on Rotor's Thrust Ratio

Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations

Modeling and Simulation of Ship–Helicopter Dynamic Interface: Method and Application

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