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 methodInfo
- 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
Links
Landscapes
- Feedback Control In General (AREA)
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
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 |
Family
ID=60541518
Family Applications (1)
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 |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU1830843A1 (en) |
Cited By (4)
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 |
-
1984
- 1984-07-09 SU SU3093763/23A patent/SU1830843A1/en active
Cited By (6)
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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