RU2010106287A - ADAPTIVE CONTROL SYSTEM OF THE PLANE AT THE PITCH ANGLE - Google Patents
ADAPTIVE CONTROL SYSTEM OF THE PLANE AT THE PITCH ANGLE Download PDFInfo
- Publication number
- RU2010106287A RU2010106287A RU2010106287/08A RU2010106287A RU2010106287A RU 2010106287 A RU2010106287 A RU 2010106287A RU 2010106287/08 A RU2010106287/08 A RU 2010106287/08A RU 2010106287 A RU2010106287 A RU 2010106287A RU 2010106287 A RU2010106287 A RU 2010106287A
- Authority
- RU
- Russia
- Prior art keywords
- adder
- input
- output
- amplifier
- integrator
- Prior art date
Links
- 230000003044 adaptive effect Effects 0.000 title claims abstract 3
Landscapes
- Feedback Control In General (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Система адаптивного управления самолетом по углу тангажа, содержащая последовательно соединенные задатчик угла тангажа, первый сумматор, первый усилитель, второй сумматор, первый интегратор, объект управления (самолет) и датчик угла, выход которого соединен со вторым входом первого сумматора, выход объекта управления через последовательно соединенные датчик угловой скорости, первый дифференциатор, второй усилитель и третий сумматор соединен со вторым входом второго сумматора, а выход датчика угловой скорости через третий усилитель подключен ко второму входу третьего сумматора, отличающаяся тем, что она содержит датчик параметра, задатчик параметра, два блока умножения, четвертый, пятый и шестой сумматоры, вторые интегратор и дифференциатор, эталонную модель, четвертый и пятый усилители, выход первого интегратора через первый блок умножения соединен с третьим входом второго сумматора, выход датчика параметра через четвертый сумматор подключен ко второму входу первого блока умножения, а выход задатчика параметра соединен со вторым входом четвертого сумматора, выход первого усилителя через последовательно соединенные эталонную модель, пятый сумматор, четвертый усилитель, второй интегратор, шестой сумматор, второй блок умножения и пятый усилитель соединен с третьим входом четвертого сумматора, вход второго дифференциатора соединен со вторым входом пятого сумматора, вход объекта управления соединен со вторым входом второго блока умножения, а выход через последовательно соединенные шестой сумматор и второй дифференциатор - с третьим входом пятого сумматора. The adaptive control system of the aircraft by the pitch angle, containing the pitch angle adjuster, the first adder, the first amplifier, the second adder, the first integrator, the control object (airplane) and the angle sensor, the output of which is connected to the second input of the first adder, the control object output in series the connected angular velocity sensor, the first differentiator, the second amplifier and the third adder are connected to the second input of the second adder, and the output of the angular velocity sensor through the third amplifier is is connected to the second input of the third adder, characterized in that it contains a parameter sensor, a parameter adjuster, two multiplication units, a fourth, fifth and sixth adders, a second integrator and differentiator, a reference model, fourth and fifth amplifiers, the output of the first integrator through the first multiplication unit connected to the third input of the second adder, the output of the parameter sensor through the fourth adder is connected to the second input of the first multiplication unit, and the output of the parameter setter is connected to the second input of the fourth adder, the output the first amplifier through a series-connected reference model, the fifth adder, the fourth amplifier, the second integrator, the sixth adder, the second multiplication unit and the fifth amplifier are connected to the third input of the fourth adder, the input of the second differentiator is connected to the second input of the fifth adder, the input of the control object is connected to the second input the second block of multiplication, and the output through the sixth adder and the second differentiator connected in series with the third input of the fifth adder.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010106287/08A RU2445671C2 (en) | 2010-02-25 | 2010-02-25 | System for adaptive control of aeroplane on pitch angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010106287/08A RU2445671C2 (en) | 2010-02-25 | 2010-02-25 | System for adaptive control of aeroplane on pitch angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2010106287A true RU2010106287A (en) | 2011-08-27 |
| RU2445671C2 RU2445671C2 (en) | 2012-03-20 |
Family
ID=44756310
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2010106287/08A RU2445671C2 (en) | 2010-02-25 | 2010-02-25 | System for adaptive control of aeroplane on pitch angle |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2445671C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2647405C1 (en) * | 2016-09-19 | 2018-03-15 | Государственное бюджетное образовательное учреждение высшего образования Московской области "Университет "Дубна" (Государственный университет "Дубна") | Adaptive system with reference model for control of aircraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2661149B1 (en) * | 1990-04-24 | 1992-08-14 | Aerospatiale | SYSTEM FOR THE PILOTAGE OF AN AIRPLANE IN TANGAGE. |
| US5722620A (en) * | 1995-05-15 | 1998-03-03 | The Boeing Company | Aircraft pitch-axis stability and command augmentation |
| FR2881849B1 (en) * | 2005-02-04 | 2007-04-06 | Airbus France Sas | METHOD AND DEVICE FOR CONTROLLING A PLANE IN BLANK |
| RU2303805C1 (en) * | 2005-12-21 | 2007-07-27 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Control unit of flight vehicle pitch channel |
-
2010
- 2010-02-25 RU RU2010106287/08A patent/RU2445671C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2445671C2 (en) | 2012-03-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PD4A | Correction of name of patent owner | ||
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20150226 |