National Technical Reports Library

The National Technical Information Service acquires, indexes, abstracts, and archives the largest collection of U.S. government-sponsored technical reports in existence. The NTRL offers online, free and open access to these authenticated government technical reports. Technical reports and documents in its repository may be available online for free either from the issuing federal agency, the U.S. Government Publishing Office’s Federal Digital System website, or through search engines.

Details

Helicopter Trim Analysis.

ADA310293

Publication Date	1996
Personal Author	Fries, J.
Page Count	52
Abstract	This report presents a generic first-principles helicopter trim analysis for use on a personal work station. Working from the helicopter's physical properties, it calculates the main rotor blade's collective, longitudinal cyclic, body pitch, and stabilator pitch angles to maintain a trimmed flight condition over a complete forward-speed range. The computer program automatically sweeps through a forward-speed range, varying the collective, longitudinal cyclic, and stabilator pitch angles to satisfy the trimmed condition. It is an improvement over earlier work where the analyst had to vary these parameters at the keyboard. It presents an example of the usage with an AH-64A helicopter, and the program's source code is included.
Keywords	Helicopters Trim(Aerodynamics) Computer programs Angles Steady state Sources Pitch(Inclination) Pitch(Motion) Physical properties Aerodynamic stability Coding Human body Cutting Rotor blades
Source Agency	Non Paid ADAS
NTIS Subject Category	51A - Aerodynamics 51C - Aircraft
Corporate Authors	Army Research Lab., Aberdeen Proving Ground, MD.
Document Type	Technical Report
Title Note	Final rept. 10-15 Sep 92.
NTIS Issue Number	199621

Helicopter Trim Analysis.

Helicopter Trim Analysis.
ADA310293

Publication Date	1996
Personal Author	Fries, J.
Page Count	52
Abstract	This report presents a generic first-principles helicopter trim analysis for use on a personal work station. Working from the helicopter's physical properties, it calculates the main rotor blade's collective, longitudinal cyclic, body pitch, and stabilator pitch angles to maintain a trimmed flight condition over a complete forward-speed range. The computer program automatically sweeps through a forward-speed range, varying the collective, longitudinal cyclic, and stabilator pitch angles to satisfy the trimmed condition. It is an improvement over earlier work where the analyst had to vary these parameters at the keyboard. It presents an example of the usage with an AH-64A helicopter, and the program's source code is included.
Keywords	Helicopters Trim(Aerodynamics) Computer programs Angles Steady state Sources Pitch(Inclination) Pitch(Motion) Physical properties Aerodynamic stability Coding Human body Cutting Rotor blades
Source Agency	Non Paid ADAS
NTIS Subject Category	51A - Aerodynamics 51C - Aircraft
Corporate Authors	Army Research Lab., Aberdeen Proving Ground, MD.
Document Type	Technical Report
Title Note	Final rept. 10-15 Sep 92.
NTIS Issue Number	199621