Investigation and comparison effects of fluid injection type in. Nitrous oxide liquid injection thrust vector pulsed. An early minuteman first stage used a single motor with four gimballed nozzles to provide pitch, yaw, and roll control. Rocketdyne concluded that aerospike nozzles had less or equal thrust vectoring capability than bell nozzle counterparts. Evaluation of fluidic thrust vectoring nozzle via thrust pitching angle and thrust pitching moment article in shock waves 271 march 2016 with 68 reads how we measure reads. Fluidic thrust vectoring involves injecting fluid into or removing it from the boundary layer of a primary jet to enable vectoring. Fluidic thrust vectoring for low observable aircraft.
Effect of injection angle on liquid injection in supersonic flow. The method of injection, as well as the fluid that is injected, are both topics of much. Introduction lift engines can be designed to operate in the vertical or. Insertion of heatresistant movable bodies into the exhaust jet. Liquid side injection hotgasside injection sl sl proven technology. Here all the high pressure pumps and pipes move together, and the flexible. There are two ways to accomplish thrust vectoring, fluidic and mechanical. Todays most maneuverable fighters use thrust vectoring, which can make a jet turn faster and more tightly. The dtn is designed with two throats, an upstream minimum and a downstream minimum at the nozzle exit, with a cavity in between the upstream throat and exit.
A computational study of a new dual throat fluidic thrust. Pdf thrust vectoring effects of a transverse gas injection. Dual throat nozzle dtn is fast becoming a popular technique for thrust vectoring. Liquid injection thrust vector control aiaa journal.
Ozawa precision pumps this commercial pump is an extremely reliable pump and is extremely accurate. Schematic of the shockvector fluidic thrust vectoring. Here all the high pressure pumps and pipes move together, and the flexible joints are in the low pressure feed pipes. Using curved nozzle with rectangular or elliptic exit and aftdeck shown in fig. Thrust vectoring, also thrust vector control or tvc, is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engines or motors to control the attitude or angular velocity of the vehicle in rocketry and ballistic missiles that fly outside the atmosphere, aerodynamic control surfaces are ineffective, so thrust vectoring is the primary. Fluidic thrust vectoring using transverse jet injection in a. Choosing a reactive liquid, n 2o 4, had the benefit that the injectant added to the overall isp of the srm.
Boston university rocket propulsion groups 200 lb thrust mk iib in hot fire testing. The 5th hot fire of the mk iib test platform, this was the first to. Nov 03, 2011 i dont know if it comes for the eurofighter, but its available. Ryan, aerodynamic thrust vectoring for attitude control of a vertically thrusting jet engine 2011. Within each category several variations of propellant and pres surization systems were considered. May 17, 2012 supersonic combustion of storable liquid fuels in mach 3. Liquid injection thrust vectoring nozzles are another advanced design that allow pitch and yaw control from ungimbaled nozzles. Pulled from a n2o main propulsion system oxidizer tank, it features system simplicity, no toxicity, room temperature storability, high system mass fraction. Experimental study of an axisymmetric dual throat fluidic. Us3259320a secondary injection thrust vector control system. I dont know if it comes for the eurofighter, but its available. Thrust vectoring nozzle for military aircraft engines example, there are 2d and 3d thrust vectoring. An early minuteman first stage used a single motor with four gimballed nozzles to.
Thrust vectoring wikimili, the best wikipedia reader. Numerical investigation of optimization of injection angle. There are several types of thrust vectoring nozzles. Analysis of dual secondary injection for thrust vectoring aircraft engineering and aerospace technology, vol. Mk iib liquid injection thrust vector control youtube. Apart from having an actuated nozzle, an inert gas or reactive liquid can be injected into the nozzle of an srb to dynamically deflect or shape the exhaust, thereby vectoring the thrust. Fluidic thrust vectoring using transverse jet injection in. Abstract dual throat nozzledtn is recently attracting much attention as a new concept of the thrust vectoring technique. Choosing a reactive liquid, n 2o 4, had the benefit that the injectant added to. Thrust vectoring can provide modern military aircraft with a number of advantages regarding performance and survivability, all of which has an influence upon life cycle cost. Although side injection of reactive liquids is still used on some of the older vehicles, it requires a pressurized propellant tank and a feed system. Us3259320a us27627463a us3259320a us 3259320 a us3259320 a us 3259320a us 27627463 a us27627463 a us 27627463a us 3259320 a us3259320 a us 3259320a authority us united states prior art keywords liquid vector control thrust vector control system injection prior art date 19601219 legal status the legal status is an assumption and is not a legal.
Pdf a study on the supersonic flow characteristics through. For example, there are 2d and 3d thrust vectoring nozzles. A computational investigation of a two dimensional nozzle was completed to assess the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. Liquid injection thrust vector control how is liquid injection thrust vector control abbreviated. Fluidic injection for thrust vectoring was investigated in the 1990s 5, 6.
Us3259320a secondary injection thrust vector control. In the present study, a computational work has been carried out to analyze the performance of a dual throat nozzle at various mass flow rates of secondary. Also, there are different ways to achieve the deflection of. The annular secondary gas injection in the axisymmetrical nozzle causes complex effects boundary layer separation, shock wave interaction. Liquid injection thrust vector control litvc system is advantageous in the following ways. Mechanical deflection of the nozzle or thrust chamber. The nozzle was designed with a recessed cavity to enhance the throat shifting method of fluidic thrust vectoring. Pdf demonstration of thrust vector control by hydrogen peroxide. Apart from vectoring, another aspect of thrust control is the modulation of thrust. Experimental research and numerical simulations of thrust vector control nozzle flow volume 120 issue 1229 s.
For liquid propellant motors, tvc is achieved by gimballing the motor and nozzle. A fluidic thrust vectoring system has the advantage of being. The propulsion systems of aircraft, using gas turbine engines, and spacecraft, using solid or liquid rockets, generate compressed gases that are directed through a nozzle to generate forward thrust. A computational study of thrust vectoring control using. In litvc, a rocket jet is deflected for steering purposes by injecting liquid into the. In the present study, a computational work has been carried out to analyze a fundamental performance of a dual. Studies on thrust vector control using secondary injection. For varying secondary injection port position the minimum thrust is obtained at 30mm position. Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergentdivergent nozzle january 20 doi.
Pdf a liquid injection thrust vector control litvc system was designed for a hybrid rocket that uses 95 wt % hydrogen peroxide, and the. Injection of fluid into the side of the diverging nozzle section, causing an. At the conclusion of phase 2, the technology will be ready. Thrust vectoring system jet engine aerospace engineering. A computational study of thrust vectoring control using dual. Evaluation of fluidic thrust vectoring nozzle via thrust. Eurofighter typhoon thrust vectoring nozzle youtube. Some applications of it are fuel injection in supersonic combustion ramjet scramjet engines and thrust vectoring of high speed vehicles. The main difference is that the injection occures at the exhaust section of the nozzle on an additional small divergent fig.
This dtn is designed with two throats, an upstream minimum and a downstream minimum at the nozzle exit, with a cavity in between the upstream throat and exit. If the liquid is injected on only one side of the missile, it modifies that side of the exhaust plume. Experimental research and numerical simulations of thrust. A numerical and modeling study has been accomplished to investigate the effects of a secondary injection in an axisymmetrical,convergentdivergent nozzle for fluidic thrust vectoring purpose. In the present study, a computational work has been carried out to analyze a fundamental. By changing the combustion on one side of the nozzle the thrust vector can be changed. Although a mechanical thrust vectoring system is effective, it can be heavy, complex, difficult to integrate and aerodynamically inefficient 3. Liquid fuelled aircraft engines modulate the thrust by varying the amount of fuel that enters the combustion chamber and by mechanically altering the throat and exit diameter of the nozzle. A rocket motor thrust vector control system comprising a combustion chamber for generating combustion gases, a nozzle in communication with the aft end of said combustion chamber, said nozzle having a convergent portion and a divergent portion downstream of said convergent portion, liquid injection ports in said nozzle downstream from said.
May 17, 2012 analysis of dual secondary injection for thrust vectoring aircraft engineering and aerospace technology, vol. D2, professor3 1, 2,3department of aeronautical engineering, nehru institute of engineering and technology abstract interest in fluidic thrust vectoring has promoted. The role of this divergent is to decrease the energy needed to make the boundary. Thrust engine control and augmentation systems thrust engine concepts thrust management and control thrust augmentation 43. For varying the mass flow rate, the net thrust is decreased for increasing the mass flow rate. Simulation of liquid injection thrust vector control for. A nitrous oxidefed liquid thrust vector control system is proposed as an efficient method for vehicle attitude control during powered flight. Liquid injection thrust vector control how is liquid. Other area of interest for military applications, is the stealth technology that requires reduction in infrared signature and jet noise.
Secondary jet injection in the main flow primary acts as an obstacle and source of the main flow momentum change zmijanovic et al. Numerical simulation of fluidic modulation of nozzle thrust. However, their tests were limited to liquid injection. Computational study of fluidic thrust vectoring using. Effects of secondary injection in rocket nozzle at various conditions m. Another method of thrust vectoring used on solid propellant ballistic missiles is liquid injection, in which the rocket nozzle is fixed, but a fluid is introduced into the exhaust flow from injectors mounted around the aft end of the missile. Liquid injection pump fertilizer systems 8006216365. Both inert water and reactive fluids such as hydrazine or nitrogen tetroxide have been used. If the liquid is injected on only one side of the missile, it modifies that side. A computational study of thrust vectoring control using dual throat nozzle. Moment characteristics of liquid injection thrust vector control.
Mass estimates thrust vectoring liquid bipropellant rockets are usually gimballed to change the thrust vector. Thrust vectoring enhances aircraft and spacecraft maneuverability. Thrust vectoring, also thrust vector control or tvc, is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engines or motor in order to control the attitude or angular velocity of the vehicle. This patent describes opening ports to release gases from aircraft and spacecraft in a direction other than. The fluidic thrust vectoring techniques which have been developed till date include throat skewing, shock vector, counterflow 7 and coflow 8. The technique of obtaining thrust vector control by the t ctio. Isros polar satellite launch vehicle pslv uses strontium perchlorate from n2 pressurefed tanks attached on side of core introduced into the srb exhaust. Numerical simulation of a hot gas injection thrust vector control.
Liquid injection thrust vector control listed as litvc. American institute of aeronautics and astronautics 12700 sunrise valley drive, suite 200 reston, va 201915807 703. This can be accomplished by gimballing the nozzle, as in the space shuttle srbs, by the use of jet vanes in the exhaust as in the v2 rocket, or by liquid injection thrust vectoring litv. Effects of secondary injection in rocket nozzle at various. Thrust vector control is effective only while the propulsion system is oper ating and creating an exhaust jet. Pdf a study on the supersonic flow characteristics. In the present study, a computational work has been carried out to analyze the performance of a dual throat nozzle at. An important factor which affects fluidic thrust vectoring is the coanda effect 9. Thrust vectoring, also thrust vector control or tvc, is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engines or motors in order to control the attitude or angular velocity of the vehicle in rocketry and ballistic missiles that fly outside the atmosphere, aerodynamic control surfaces are ineffective, so thrust vectoring is the. Liquid jet injection into supersonichypersonic cross flow topology has been widely investigated in recent years. The 5th hot fire of the mk iib test platform, this was the first to run nitrous injection thrust vector control.
Liquid injection thrust vector control litvc, in the exit cone of the nozzle, was selected to turn the direction of the boosters thrust vector, when steering was needed. Liquid injection liquid injection encompasses any addition of a fluid that changes the characteristics of the combustion. Film cooling for reentry vehicles falls into this flow topology as well. Liquid injection systems, auxiliary hot or cold gas systems and gimballed nozzle systems were analyzed to determine the size of each type of system required to overcome the maximum possible moment due to thrust mis alignment. The development and testing of liquid injection thrust vector.1074 110 270 466 1532 1118 1157 1502 1540 10 967 1397 1035 345 1021 97 415 767 539 1208 359 960 220 1459 1423 1405 1603 966 1614 1301 794 1143 924 1290 796 1593 1365 526 753 1432 1317 940 277 10 1199 135 80 182 53