Liquid Injection Thrust Vector Control Research Articles

Demonstration of Thrust Vector Control by Hydrogen Peroxide Injection in Hybrid Rockets

A liquid injection thrust vector control (LITVC) system was designed for a hybrid rocket that uses 95 wt % hydrogen peroxide, and the system was demonstrated by using the hydrogen peroxide as the injectant. The influence of the chamber pressure, injectant flow rate, and injection location on the LITVC performance was parametrically investigated. The investigations revealed that the chamber pressure had a significant influence on the LITVC performance. As the chamber pressure increased from 20 to 40 bar, the side specific impulse improved from 71.7 to 157.3 s under injectant flow rates equal to 9% of the primary gas flow rates and at the injection location of (where is the distance from the throat to the injection location and is the length of the nozzle diverging section). To examine the effects of injection location on the LITVC performance, side specific impulses were measured at , 0.47, and 0.72 under the chamber pressure condition of 40 bar. Among all injection locations, provided the highest side specific impulses under all injectant flow rate conditions. Furthermore, the radial spreading caused by increasing the injectant flow rates degraded the LITVC efficiency.

Liquid-Injection Thrust Vector Control.

Theme A PROCEDURE is presented for preliminary design of a liquid-injection thrust-vector-control (LITVC) system for solid-propellant rockets. In LITVC, a rocket jet is deflected for steering purposes by injecting liquid into the side of the nozzle exit flow (see Fig. 1). The liquid is preferably both dense and exothermally reactive. The injection produces side thrust and added axial thrust mainly by pressures on the nozzle wall caused by shock waves and addition of mass and energy to the flow.

Moment characteristics of liquid injection thrust vector control

Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.

The Attitude Control System for MU Rockets Used to Launch Japanese Scientific Satellites

Summary The attitude control system whose attitude reference is established by a 2-degree-of-freedom gyroscope (2-DFG) mounted on a single axis stabilized table has been developed to launch Japanese scientific satellites by Mu rockets. Firstly the final attitude was only specified by the rotor of 2-DFG, while now the function is augmented to include the pitch programmer and the radio guidance receiver. Then this system was applied to Mu-3C rockets whose 2nd stage motor is stabilized by liquid injection thrust vector control (LITVC) unit, and realized successfully two satellites. For the past successful 7 flight experiments, the trajectory estimation based on the iterative least square (differential correction) method gave very satisfactory results. From these analysis, it is concluded that the injection errors of total system were within the 2° in pitch, 5° in yaw and 1% in velocity.

ＬＩＴＶＣ特性についての一考察

A simple relation is derived concerning to LITVC (Liquid Injection Thrust Vector Control) characteristics based on a model taken into consideration of the momentum exchange between the injectant and the main nozzle flow. In this model, it is assumed that the injectant forms an equivalent slender body being swept away by main nozzle flow after injection and the side force is generated with the disturbed wall pressur around the equivalent slender body. General conclusions from numerical calculations using the slender body theory for typical bodies of revolution are effectively used to derive a simple relation. This relation expressing the dependency of Isps (specific impulse of secondary injection) on the injectant flow rate and the chamber pressure has been examined by correlating experimental values obtained in the series of experiments conducted by the Institute of Space and Aeronautical Science of University of Tokyo.

Application of jet pumping to liquid injection thrust vector control

Application of jet pumping to liquid injection thrust vector control

Measurement Systems for Dual Range Rocket Motor Performance and LITVC Evaluation

Analysis results and relative merits of five measurement system techniques and transducer designs are discussed for providing accurate pressure and force definitions during static solid rocket motor firings with dual level ballistic performance or dual gain liquid injection thrust vector control (LITVC). The accuracy and reliability of each system depends upon the inherent capability and procedures maintained in each approach, the operational levels, and the specific applications; therefore, these factors are necessarily discussed in the text. An analysis of the described force and pressure measurement systems show how an instrumentation measurement system total error may vary from ±0.5% to ±10% depending on the emphasis placed upon the overall measurement system design, and the control exercised during use.

Noise-and-Vibration Characteristics of Large, Solid Rocket Motors with Thrust-Vector Control

Noise-and-vibration measurements have been made during static firing of three solid rocket motors. The thrust level of the largest motor was approximately 106 lb. Far- and near-field acoustic data show fair agreement with data scaled from smaller motors, but raise some questions concerning assumed acoustic equivalences between solid- and liquid-fuel systems. The effects of liquid-injection thrust-vector control are visible in acoustic and vibration data. These effects are in line with the hypothesis that thrust-vector control tends to relocate the sources of nearfield noise closer to the exhaust nozzle. [This work was supported in part by subcontract with Aerospace Corporation.]