UA107270C2 - A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINET - Google Patents
A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINETInfo
- Publication number
- UA107270C2 UA107270C2 UAA201306211A UAA201306211A UA107270C2 UA 107270 C2 UA107270 C2 UA 107270C2 UA A201306211 A UAA201306211 A UA A201306211A UA A201306211 A UAA201306211 A UA A201306211A UA 107270 C2 UA107270 C2 UA 107270C2
- Authority
- UA
- Ukraine
- Prior art keywords
- rocket engine
- liquid rocket
- turbo
- fuel components
- actuators
- Prior art date
Links
Landscapes
- Testing Of Engines (AREA)
Abstract
Запропоновано спосіб керування вектором тяги рідинного ракетного двигуна з турбонасосним агрегатом подачі компонентів палива в камеру згоряння та рідинний ракетний двигун з його застосуванням. Спосіб базується на сукупному застосуванні газодинамічного регулювання вектора тяги камери рідинного ракетного двигуна плавно регульованим впорскуванням рідинного компонента палива в надзвуковий потік сопла і механічного регулювання вектора тяги газорозподілюванням відпрацьованого на турбіні генераторного газу між двома парами діаметрально протилежних нерухомих вихлопних сопел. Пристрій являє собою рідинний ракетний двигун, що містить нерухому камеру згоряння з надзвуковим соплом, турбонасосний агрегат подачі в камеру компонентів палива з турбіною, вихлопний колектор якої з'єднано з вихлопними соплами газоводами, що містять газорозподільники з приводами, з'єднаними з системою програмного керування польотом; в надзвуковій частині сопла в кожній чверті виготовлено вузли впорскування компонента палива з приводами, з'єднаними з системою керування польоту літального апарата по заданій траєкторії.A method of controlling the thrust vector of a liquid rocket engine with a turbo pump unit for supplying fuel components to the combustion chamber and a liquid rocket engine with its application is proposed. The method is based on the combined application of gas-dynamic regulation of the thrust vector of the liquid rocket engine chamber smoothly controlled injection of the liquid component of the fuel into the supersonic nozzle flow and mechanical regulation of the thrust vector by gas distribution of the turbine exhaust gas between two pairs of diametrically opposite diameters. The device is a liquid rocket engine containing a fixed combustion chamber with a supersonic nozzle, turbo-pump unit feed into the chamber of fuel components with a turbine, the exhaust manifold of which is connected to the exhaust nozzles with gas pipelines with actuators, actuators flight; in the supersonic part of the nozzle in each quarter nodes are injected fuel component with actuators connected to the flight control system of the aircraft along a given trajectory.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAA201306211A UA107270C2 (en) | 2013-05-20 | 2013-05-20 | A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINET |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAA201306211A UA107270C2 (en) | 2013-05-20 | 2013-05-20 | A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINET |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| UA107270C2 true UA107270C2 (en) | 2014-12-10 |
Family
ID=52680949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| UAA201306211A UA107270C2 (en) | 2013-05-20 | 2013-05-20 | A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINET |
Country Status (1)
| Country | Link |
|---|---|
| UA (1) | UA107270C2 (en) |
-
2013
- 2013-05-20 UA UAA201306211A patent/UA107270C2/en unknown
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20120145808A1 (en) | Method and apparatus for variable exhaust nozzle exit area | |
| US10927793B2 (en) | Engine for hypersonic aircrafts with supersonic combustor | |
| FR2967725B1 (en) | COMBINED TURBOREACTOR AND STATOREACTOR COMBINATION PROPELLER | |
| JP6323877B2 (en) | Propulsion assembly for rocket | |
| ATE547609T1 (en) | ROCKET ENGINE FOR LIQUID FUEL WITH CLOSING BLADE TO THE COMBUSTION CHAMBER | |
| CN108035824A (en) | A kind of pulsed secondary jet thrust vector control system | |
| WO2015019011A3 (en) | Device for supplying rocket engine propellant | |
| WO2020186065A3 (en) | Spacecraft propulsion devices and systems with microwave excitation | |
| JP2015190741A5 (en) | ||
| JP2015081600A5 (en) | ||
| UA107270C2 (en) | A METHOD OF CONTROL OF A VECTOR OF A TRUCK OF A LIQUID ROCKET ENGINE WITH A TURBO-PUMPING UNIT FOR THE SUBMITTING OF FUEL COMPONENTS TO A COMBINATION AND RIGINET | |
| JP2015507719A5 (en) | ||
| UA103528C2 (en) | Method for control of traction vector of liquid-propellant rocket engine and liquid-propellant rocket engine for its realization | |
| Chun et al. | Computational investigation of nozzle flowfields at various flight conditions for aircraft infrared signature analysis | |
| RU2380651C1 (en) | Multistaged air-defense missile | |
| UA108677C2 (en) | METHOD OF CONTROLLING A TRACTOR VECTOR OF A LIQUID ROCKET ENGINE AND A LIQUID ROCKET ENGINE WITH ITS APPLICATION | |
| CN105298683A (en) | Throat deviating type pneumatic thrust vectoring nozzle with fuel supplementing and thrust augmenting functions and control method | |
| UA111995C2 (en) | LIQUID ROCKET ENGINE WITH TURBO PUMP SYSTEM IN THE COMBUSTION AND GASODYNAMIC TRACTION CONTROL SYSTEM | |
| RU2681733C1 (en) | Camera lpr | |
| RU2380647C1 (en) | Multistaged cruise missile | |
| Wei et al. | Experimental study on combustion mode transition in an aero-ramp based scramjet | |
| RU2621771C2 (en) | Method of lowering the spent part of space-mission vehicle submissile and the device for its implementation | |
| Isaac et al. | Fluidic thrust vectoring nozzles | |
| UA112118C2 (en) | LIQUID ROCKET ENGINE WITH ADDITION OF DISPOSED GENERATOR GAS TURBINE TURBINE PUMP | |
| RU2380650C1 (en) | Air-defense missile |