RU2012126217A - METHOD FOR CONTROLLING Aircraft Thrust Vector of an Aircraft - Google Patents
METHOD FOR CONTROLLING Aircraft Thrust Vector of an Aircraft Download PDFInfo
- Publication number
- RU2012126217A RU2012126217A RU2012126217/06A RU2012126217A RU2012126217A RU 2012126217 A RU2012126217 A RU 2012126217A RU 2012126217/06 A RU2012126217/06 A RU 2012126217/06A RU 2012126217 A RU2012126217 A RU 2012126217A RU 2012126217 A RU2012126217 A RU 2012126217A
- Authority
- RU
- Russia
- Prior art keywords
- thrust vector
- aircraft
- nozzle
- symmetry
- electromagnets
- Prior art date
Links
Landscapes
- Plasma Technology (AREA)
Abstract
1. Способ управления вектором тяги сопла реактивного двигателя летательного аппарата, отличающийся тем, что для изменения направления вектора тяги отклоняется относительно оси симметрии поток истекающих из сопла газов, состоящих из плазмы (ионов и электронов) посредством воздействия на него парными электромагнитами управления, в виде, например, полос, установленных вдоль образующей закритической части на внешней поверхности раструба в плоскостях симметрии I-III и II-IV, при этом на парные электромагниты управления подается электрический ток противоположных знаков по командному сигналу системы управления летательным аппаратом.2. Способ управления вектором тяги по п.1, отличающийся тем, что для получения электрического тока, необходимого для подачи на электромагниты управления вектором тяги, на сопло установлен МГД-генератор индукционного типа.1. The method of controlling the thrust vector of the nozzle of a jet engine of an aircraft, characterized in that for changing the direction of the thrust vector, the flow of gases flowing out of the nozzle consisting of plasma (ions and electrons) is deflected relative to the axis of symmetry by exposure to it by paired control electromagnets, in the form, for example, strips installed along the generatrix of the supercritical part on the outer surface of the socket in the planes of symmetry I-III and II-IV, while electric t is supplied to the paired control electromagnets to the opposite sign of the instruction signal apparatom.2 aircraft control system. The thrust vector control method according to claim 1, characterized in that in order to obtain the electric current necessary for supplying thrust vector control electromagnets, an induction type MHD generator is installed on the nozzle.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012126217/06A RU2504683C1 (en) | 2012-06-22 | 2012-06-22 | Method of control over aircraft jet thrust vector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012126217/06A RU2504683C1 (en) | 2012-06-22 | 2012-06-22 | Method of control over aircraft jet thrust vector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2012126217A true RU2012126217A (en) | 2013-12-27 |
| RU2504683C1 RU2504683C1 (en) | 2014-01-20 |
Family
ID=49785976
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2012126217/06A RU2504683C1 (en) | 2012-06-22 | 2012-06-22 | Method of control over aircraft jet thrust vector |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2504683C1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2527798C2 (en) * | 2012-11-28 | 2014-09-10 | Михаил Никитович Алексенко | Jet engine thrust vector control device |
| RU2558961C1 (en) * | 2014-04-08 | 2015-08-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Балтийский государственный технический университет "ВОЕНМЕХ" им. Д.Ф. Устинова (БГТУ "ВОЕНМЕХ") | Method of control of aerodynamic characteristics of hypersonic aircraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2782884B1 (en) * | 1998-08-25 | 2000-11-24 | Snecma | CLOSED ELECTRON DERIVATIVE PLASMA PROPELLER SUITABLE FOR HIGH THERMAL LOADS |
| US6334302B1 (en) * | 1999-06-28 | 2002-01-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable specific impulse magnetoplasma rocket engine |
| RU2196396C2 (en) * | 2000-10-23 | 2003-01-10 | Петросов Валерий Александрович | Method and device for regulating thrust vector of electric rocket engine |
| RU2300007C1 (en) * | 2006-01-25 | 2007-05-27 | Игорь Константинович Тимошенко | Vortex rocket motor |
-
2012
- 2012-06-22 RU RU2012126217/06A patent/RU2504683C1/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2504683C1 (en) | 2014-01-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103953517B (en) | Hall thruster improves device | |
| US9028687B2 (en) | Separating device for separating magnetic or magnetizable particles present in suspension | |
| EP2613050B1 (en) | Plasma actuating propulsion system for aerial vehicles and propulsion method thereof | |
| RU2018111981A (en) | MAGNETO-HYDRODYNAMIC GENERATOR | |
| US8500404B2 (en) | Plasma actuator controlled film cooling | |
| JP2017025407A5 (en) | ||
| JP2015222705A5 (en) | ||
| JP2013149722A5 (en) | ||
| PH12018501136A1 (en) | System, method and device to optimize the efficiency of the combustion of gases for the production of clean energy | |
| US10033236B2 (en) | Vacuum gap generators and motors | |
| RU2012151111A (en) | REACTIVE ENGINE DRIVE VECTOR CONTROL DEVICE | |
| JP2015222069A5 (en) | ||
| RU2012126217A (en) | METHOD FOR CONTROLLING Aircraft Thrust Vector of an Aircraft | |
| ES2540167A1 (en) | System without mobile parts nor electrodes and procedure to vectorize the push in plasma space engines (Machine-translation by Google Translate, not legally binding) | |
| RU2012110455A (en) | MHD GENERATOR | |
| JP2011231928A (en) | Diffuser | |
| JP4772759B2 (en) | Diffuser | |
| JP2019057375A5 (en) | ||
| RU2017130327A (en) | HALL EFFECT ENGINE AND SPACE VEHICLE INCLUDING SUCH ENGINE | |
| CN105056667A (en) | Pressure-stabilizing aerial fog distributor | |
| RU2010146227A (en) | AIRCRAFT ICE CRYSTAL GENERATOR | |
| Fomichev et al. | Experimental study of the MHD-parachute phenomena in a hypersonic air flow | |
| JP5766739B2 (en) | Diffuser | |
| JP2010126151A (en) | Electromagnetic propulsion device | |
| RU2013119145A (en) | TURBINE OF A GAS-TURBINE ENGINE AND METHOD FOR ADJUSTING A RADIAL GAP IN A TURBINE |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20150623 |