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Rocket

About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.


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Journal ArticleDOI
TL;DR: In this paper, side forces generated by secondary gas injection in a 15° conical rocket exhaust nozzle were measured directly with a force transducer and the data examined in terms of an amplification factor I8/I8*9 where Is is the measured effective specific impulse of injectant, and Is* is the specific impulse for sonic flow into a vacuum.
Abstract: Data are presented on side forces generated by secondary gas injection in a 15° conical rocket exhaust nozzle. The side force was measured directly with a force transducer and the data examined in terms of an amplification factor I8/I8*9 where Is is the measured effective specific impulse of injectant, and Is* is the specific impulse of injectant for sonic flow into a vacuum. Injection was normal to the axis of the nozzle through a single circular orifice at a fixed point in the diverging portion of the nozzle. A variety of ambient temperature gaseous injectants (H2, He, He + Ar, N2, CO2, and Ar) and orifice diameters were carefully studied. Injectant flow rate was varied for each configuration. The main propellant was hot gas (catalytically decomposed 90% H2O2), and motor conditions were held essentially constant. Aj = A\ = CD = FN = F =

61 citations

Proceedings ArticleDOI
02 Aug 2009
TL;DR: A detailed survey of liquid-propellant rocket engine throttling can be found in this article, where several methods of LRE throttling are discussed, including high-pressure-drop systems, dual-injector manifolds, gas injection, multiple chambers, pulse modulation, throat throttling, movable injector components, and hydrodynamically dissipative injectors.
Abstract: Liquid-Propellant Rocket Engines (LREs) are capable of on-command variable thrust or thrust modulation, an operability advantage that has been studied intermittently since the late 1930s. Throttleable LREs can be used for planetary entry and descent, space rendezvous, orbital maneuvering including orientation and stabilization in space, and hovering and hazard avoidance during planetary landing. Other applications have included control of aircraft rocket engines, limiting of vehicle acceleration or velocity using retrograde rockets, and ballistic missile defense trajectory control. Throttleable LREs can also continuously follow the most economical thrust curve in a given situation, compared to discrete throttling changes over a few select operating points. The effects of variable thrust on the mechanics and dynamics of an LRE as well as difficulties and issues surrounding the throttling process are important aspects of throttling behavior. This review provides a detailed survey of LRE throttling centered around engines from the United States. Several LRE throttling methods are discussed, including high-pressure-drop systems, dual-injector manifolds, gas injection, multiple chambers, pulse modulation, throat throttling, movable injector components, and hydrodynamically dissipative injectors. Concerns and issues surrounding each method are examined, and the advantages and shortcomings compared.

61 citations

Journal ArticleDOI
TL;DR: In this paper, the authors describe an experimental investigation on the flutter of viscoelastic cantilevers subjected to a tangential follower force. But their results were compared with theoretical flutter predictions made by accounting for an internal damping of the test columns, as well as the mass and size of the installed rocket motor.
Abstract: This paper describes an experimental investigation on the flutter of viscoelastic cantilevers subjected to a tangential follower force. The force was produced by the direct installation of a real solid rocket motor to the tip end of the cantilevered columns. The columns lost their stability by flutter. The results were compared with theoretical flutter predictions made by accounting for an internal damping of the test columns, as well as the mass and size of the installed rocket motor. The introduction of the concept of instability in a finite time interval is of vital importance in predicting the experimental flutter force.

60 citations

Journal ArticleDOI
TL;DR: In this article, reactive B/Ti multilayer igniters were investigated for the noncontact ignition of a micro solid rocket array thruster in vacuum, and three sizes of three sizes were fabricated and tested in six configurations of solid propellant.
Abstract: In this study, reactive B/Ti multilayer igniters were investigated for the noncontact ignition of a micro solid rocket array thruster in vacuum. When current is supplied to the B/Ti multilayer igniter, the chemical reaction: 2B + Ti → TiB 2 + 1320 cal/g occurs, and sparkles are spread to a distance of several millimeters or more. The B/Ti multilayer igniters with three sizes were fabricated, and tested in six configurations of solid propellant. Although one rocket with ignition charge was ignited successfully, the noncontact ignition of the solid propellant was not achieved. However, the B/Ti multilayer igniters themselves generated small impulses of 10 −6 N s order, suggesting the possibility of self-propulsion.

60 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202211
2021373
2020480
2019624
2018537
2017493