Mechanical deflection of the nozzle or thrust chamber. The development and testing of liquid injection thrust vector. Schematic of the shockvector fluidic thrust vectoring. Pdf thrust vectoring effects of a transverse gas injection. Todays most maneuverable fighters use thrust vectoring, which can make a jet turn faster and more tightly. 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. 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. Us3259320a secondary injection thrust vector control system. Fluidic thrust vectoring concept is better in terms of the weight, mechanical. Choosing a reactive liquid, n 2o 4, had the benefit that the injectant added to. Mk iib liquid injection thrust vector control youtube. For varying the mass flow rate, the net thrust is decreased for increasing the mass flow rate. Nov 03, 2011 i dont know if it comes for the eurofighter, but its available. 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.
Fluidic thrust vectoring using transverse jet injection in a. Thrust vector control is effective only while the propulsion system is oper ating and creating an exhaust jet. The 5th hot fire of the mk iib test platform, this was the first to. The method of injection, as well as the fluid that is injected, are both topics of much. Here all the high pressure pumps and pipes move together, and the flexible joints are in the low pressure feed pipes. The role of this divergent is to decrease the energy needed to make the boundary. Thrust vectoring nozzle for military aircraft engines example, there are 2d and 3d thrust vectoring. A nitrous oxidefed liquid thrust vector control system is proposed as an efficient method for vehicle attitude control during powered flight.
Fluidic thrust vectoring involves injecting fluid into or removing it from the boundary layer of a primary jet to enable vectoring. A computational study of thrust vectoring control using dual throat nozzle. For example, there are 2d and 3d thrust vectoring nozzles. Nitrous oxide liquid injection thrust vector pulsed. Dual throat nozzle dtn is fast becoming a popular technique for thrust vectoring. Some applications of it are fuel injection in supersonic combustion ramjet scramjet engines and thrust vectoring of high speed vehicles. Ryan, aerodynamic thrust vectoring for attitude control of a vertically thrusting jet engine 2011. The 5th hot fire of the mk iib test platform, this was the first to run nitrous injection thrust vector control. Indias pslv calls its design secondary injection thrust vector control system. Apart from vectoring, another aspect of thrust control is the modulation of thrust.
Here all the high pressure pumps and pipes move together, and the flexible. Nov 19, 2014 boston university rocket propulsion groups 200 lb thrust mk iib in hot fire testing. A fluidic thrust vectoring system has the advantage of being. If the liquid is injected on only one side of the missile, it modifies that side of the exhaust plume. Effects of secondary injection in rocket nozzle at various. Experimental research and numerical simulations of thrust. Using curved nozzle with rectangular or elliptic exit and aftdeck shown in fig. Liquid injection liquid injection encompasses any addition of a fluid that changes the characteristics of the combustion.
Mass estimates thrust vectoring liquid bipropellant rockets are usually gimballed to change the thrust vector. Isros polar satellite launch vehicle pslv uses strontium perchlorate from n2 pressurefed tanks attached on side of core introduced into the srb exhaust. An early minuteman first stage used a single motor with four gimballed nozzles to. Numerical investigation of optimization of injection angle. Introduction lift engines can be designed to operate in the vertical or. For varying secondary injection port position the minimum thrust is obtained at 30mm position. Liquid injection thrust vector control how is liquid injection thrust vector control abbreviated.
Secondary jet injection in the main flow primary acts as an obstacle and source of the main flow momentum change zmijanovic et al. As the secondary injection thrust vectoring technique, the one used in this study utilizes a secondary jet in the nozzle. Injection of fluid into the side of the diverging nozzle section, causing an. 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. An early minuteman first stage used a single motor with four gimballed nozzles to provide pitch, yaw, and roll control. In the present study, a computational work has been carried out to analyze the performance of a dual throat nozzle at. Liquid injection thrust vector control aiaa journal. Studies on thrust vector control using secondary injection.
May 17, 2012 analysis of dual secondary injection for thrust vectoring aircraft engineering and aerospace technology, vol. 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. Thrust vectoring enhances aircraft and spacecraft maneuverability. D2, professor3 1, 2,3department of aeronautical engineering, nehru institute of engineering and technology abstract interest in fluidic thrust vectoring has promoted. In the present study, a computational work has been carried out to analyze a fundamental performance of a dual. Pdf demonstration of thrust vector control by hydrogen peroxide. The annular secondary gas injection in the axisymmetrical nozzle causes complex effects boundary layer separation, shock wave interaction. The nozzle was designed with a recessed cavity to enhance the throat shifting method of fluidic thrust vectoring.
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. Experimental research and numerical simulations of thrust vector control nozzle flow volume 120 issue 1229 s. An important factor which affects fluidic thrust vectoring is the coanda effect 9. Numerical simulation of fluidic modulation of nozzle thrust. May 17, 2012 supersonic combustion of storable liquid fuels in mach 3. Simulation of liquid injection thrust vector control for. Rocketdyne concluded that aerospike nozzles had less or equal thrust vectoring capability than bell nozzle counterparts. Liquid injection thrust vectoring nozzles are another advanced design that allow pitch and yaw control from ungimbaled nozzles. Liquid injection pump fertilizer systems 8006216365. The main difference is that the injection occures at the exhaust section of the nozzle on an additional small divergent fig. Liquid injection thrust vector control litvc system is advantageous in the following ways. 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. 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. 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.
For liquid propellant motors, tvc is achieved by gimballing the motor and nozzle. Although a mechanical thrust vectoring system is effective, it can be heavy, complex, difficult to integrate and aerodynamically inefficient 3. A continuing series of 1,000 lb thrust hybrid rocket motor tests are proposed to characterize n2os side specific impulse as a function of thrust vectoring angle, as well as a series of 4,000 lb thrust motor firings culminating in a closedloop guidance navigation and control hardwareintheloop test in a vertical stand. 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 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.
Us3259320a secondary injection thrust vector control. Eurofighter typhoon thrust vectoring nozzle youtube. 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. Liquid injection thrust vector control listed as litvc.
Pdf a study on the supersonic flow characteristics through. Fluidic thrust vectoring using transverse jet injection in. Liquid side injection hotgasside injection sl sl proven technology. 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. Evaluation of fluidic thrust vectoring nozzle via thrust. By changing the combustion on one side of the nozzle the thrust vector can be changed. Insertion of heatresistant movable bodies into the exhaust jet. There are two ways to accomplish thrust vectoring, fluidic and mechanical. Choosing a reactive liquid, n 2o 4, had the benefit that the injectant added to the overall isp of the srm.
Thrust vectoring wikimili, the best wikipedia reader. Pdf a study on the supersonic flow characteristics. The figure below illustrates a basic concept for the litvc system. 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. 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. Also, there are different ways to achieve the deflection of. Analysis of dual secondary injection for thrust vectoring aircraft engineering and aerospace technology, vol. American institute of aeronautics and astronautics 12700 sunrise valley drive, suite 200 reston, va 201915807 703. Fluidic thrust vectoring for low observable aircraft. Liquid jet injection into supersonichypersonic cross flow topology has been widely investigated in recent years. In the present study, a computational work has been carried out to analyze a fundamental. Film cooling for reentry vehicles falls into this flow topology as well.
A computational study of a new dual throat fluidic thrust. Numerical simulation of a hot gas injection thrust vector control. This patent describes opening ports to release gases from aircraft and spacecraft in a direction other than. Within each category several variations of propellant and pres surization systems were considered. Pdf a liquid injection thrust vector control litvc system was designed for a hybrid rocket that uses 95 wt % hydrogen peroxide, and the. 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. A computational study of thrust vectoring control using. Moment characteristics of liquid injection thrust vector control. 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. Other area of interest for military applications, is the stealth technology that requires reduction in infrared signature and jet noise. A computational study of thrust vectoring control using dual.
Ozawa precision pumps this commercial pump is an extremely reliable pump and is extremely accurate. Both inert water and reactive fluids such as hydrazine or nitrogen tetroxide have been used. Computational study of fluidic thrust vectoring using. Effects of secondary injection in rocket nozzle at various conditions m.
Investigation and comparison effects of fluid injection type in. However, their tests were limited to liquid injection. Fluidic injection for thrust vectoring was investigated in the 1990s 5, 6. 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. Boston university rocket propulsion groups 200 lb thrust mk iib in hot fire testing. 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. Thrust engine control and augmentation systems thrust engine concepts thrust management and control thrust augmentation 43. At the conclusion of phase 2, the technology will be ready. The technique of obtaining thrust vector control by the t ctio. Liquid injection thrust vector control description the injection of a liquid in the supersonic section of the rocket nozzle creates a large oblique shock that produces a side force on the side of the nozzle. Thrust vectoring is an extremely powerful and valuable control effector at low dynamic pressures, where traditional aerodynamic control technologies loose control power.
Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergentdivergent nozzle january 20 doi. Liquid injection thrust vector control how is liquid. In litvc, a rocket jet is deflected for steering purposes by injecting liquid into the. Thrust vectoring system jet engine aerospace engineering. Effect of injection angle on liquid injection in supersonic flow. There are several types of thrust vectoring nozzles. The development and testing of liquid injection thrust. Pulled from a n2o main propulsion system oxidizer tank, it features system simplicity, no toxicity, room temperature storability, high system mass fraction. I dont know if it comes for the eurofighter, but its available. Experimental study of an axisymmetric dual throat fluidic. Abstract dual throat nozzledtn is recently attracting much attention as a new concept of the thrust vectoring technique. If the liquid is injected on only one side of the missile, it modifies that side. 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.