SU1830843A1 - Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method - Google Patents

Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method

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Publication number
SU1830843A1
SU1830843A1 SU3093763/23A SU3093763A SU1830843A1 SU 1830843 A1 SU1830843 A1 SU 1830843A1 SU 3093763/23 A SU3093763/23 A SU 3093763/23A SU 3093763 A SU3093763 A SU 3093763A SU 1830843 A1 SU1830843 A1 SU 1830843A1
Authority
SU
USSR - Soviet Union
Prior art keywords
attack
angle
elevens
aircraft
deflected
Prior art date
Application number
SU3093763/23A
Other languages
Russian (ru)
Inventor
Г.И. Загайнов
В.Л. Суханов
А.З. Тарасов
Н.И. Костенко
В.А. Наумов
Ю.И. Шенфинкель
В.П. Власов
Original Assignee
Центральный аэрогидродинамический институт им.Н.Е.Жуковского
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Центральный аэрогидродинамический институт им.Н.Е.Жуковского filed Critical Центральный аэрогидродинамический институт им.Н.Е.Жуковского
Priority to SU3093763/23A priority Critical patent/SU1830843A1/en
Application granted granted Critical
Publication of SU1830843A1 publication Critical patent/SU1830843A1/en

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Abstract

FIELD: aeronautical engineering. SUBSTANCE: method is based on joint deviation of control members - fore plane, elevens and tail panels at angle of attack up to that corresponding to maximum lift force α < αcy; elevens are deflected down- ward in function of angle of attack which is selected from condition of enhanced aerodynamic characteristics of aircraft; tail panels are deflected through angle determined by condition of longitudinal trim of aircraft at indicated position of elevens; at angles of attack of α > αcy, tail panels are deflected for aircraft trim and after they come to limit, elevens are deflected to the same side; at any angle of attack, stabilization of aircraft is effected through deflecting the tail panels and fore horizontal planes relative to their trim position. Device for realization of this method has computer, angle-of- attack sensor, pitch-rate pickup, normal g-load sensor and control stick position sensor; first, second and third adders, first and second aperiodic elements, servo units of fore horizontal planes, tail panels and elevens; first and second scaling units at adjustable gain and first, second and third nonlinear functional converters. EFFECT: enhanced stability and controllability of aircraft at static longitudinal instability at angles of attack of αcy- and enhanced longitudinal stability at α > αcyas well as enhanced efficiency of longitudinal control in entire range of angle of attack. 3 cl, 3 dwg
SU3093763/23A 1984-07-09 1984-07-09 Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method SU1830843A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU3093763/23A SU1830843A1 (en) 1984-07-09 1984-07-09 Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU3093763/23A SU1830843A1 (en) 1984-07-09 1984-07-09 Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method

Publications (1)

Publication Number Publication Date
SU1830843A1 true SU1830843A1 (en) 1996-01-27

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Application Number Title Priority Date Filing Date
SU3093763/23A SU1830843A1 (en) 1984-07-09 1984-07-09 Method of control of longitudinal motion of canard aeroplane with swept-forward wing and device for realization of this method

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SU (1) SU1830843A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2446429C1 (en) * 2010-10-06 2012-03-27 Открытое акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (ОАО МНПК "Авионика") High-maneuverability aircraft flight automatic control method
RU2459230C2 (en) * 2010-10-06 2012-08-20 Открытое акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (ОАО МНПК "Авионика") Automatic flight control system for highly-manoeuvrable aircraft
CN113479316A (en) * 2021-09-08 2021-10-08 中国商用飞机有限责任公司 Methods, systems, and media for controlling horizontal tail unloading of an aircraft
CN113703318A (en) * 2021-08-08 2021-11-26 中国航空工业集团公司沈阳飞机设计研究所 Longitudinal leveling control method based on meter speed resolving variable overload

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2446429C1 (en) * 2010-10-06 2012-03-27 Открытое акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (ОАО МНПК "Авионика") High-maneuverability aircraft flight automatic control method
RU2459230C2 (en) * 2010-10-06 2012-08-20 Открытое акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (ОАО МНПК "Авионика") Automatic flight control system for highly-manoeuvrable aircraft
CN113703318A (en) * 2021-08-08 2021-11-26 中国航空工业集团公司沈阳飞机设计研究所 Longitudinal leveling control method based on meter speed resolving variable overload
CN113703318B (en) * 2021-08-08 2023-12-15 中国航空工业集团公司沈阳飞机设计研究所 Longitudinal leveling control method based on table speed calculation overload change
CN113479316A (en) * 2021-09-08 2021-10-08 中国商用飞机有限责任公司 Methods, systems, and media for controlling horizontal tail unloading of an aircraft
CN113479316B (en) * 2021-09-08 2021-11-30 中国商用飞机有限责任公司 Methods, systems, and media for controlling horizontal tail unloading of an aircraft

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