Solid rocket thrust vector control.

Cover title.

Solid rocket motor nozzles /

"...written by Russell A. Ellis."

Captive-fired testing of solid rocket motors

Cover title.

20th meeting bulletin.

Mode of access: Internet.

Long liquid bridges aboard sounding rockets

Large free liquid volumes, 30 mm in diameter and 80 mm long, anchored to coaxial discs, have been achieved during a sounding-rocket flight. As these flights provide some six minutes of microgravity and the formation of the liquid column takes only a matter of seconds, ample time is left for experimentation. The results of these trials are presented, and the equipment used to obtain them is briefly described.

A review of hybrid rockets: present status and future potential

This paper discusses the potential of the hybrid rocket engine as a viable and attractive mode of propulsion for both space vehicles and missiles. Research and development work on this engine in other countries is presented and evaluated. The various advantages of a hybrid engine over solid and liquid engines and its problems are highlighted. It has been argued that because of the low technology needed in the development of the hybrid system, it constitutes a cost-and-time-effective propulsion system for several applications in space programmes as well as weapon systems. In support of this conclusion, experience on the developmental studies of a variable thrust 100 kg engine is presented. Some future possibilities for hybrid propulsion systems are cited.

Solid propellant binders

Solid, propellants are widely used in modern rockets and missiles. Although the history of solid rockets could be traced to the discovery of gunpowder over a thousand years ago, the technology could be perfected only by the later half of the 20(th) century. The failure of gunpowder rockets was largely due to the unknown consolidating technique of the powder composition. The emergence of large solid propellant motors had, to await the dawn of polymer. science and technology(S&T). Specific syntheses of functionally terminated polymers having cross-linking capability led to the emergence of casting technology of solid composite propellants. This review describes the various polymeric fuel/binder systems used or considered for use in solid,propellants. It includes a brief background, advantages, and shortcomings of the various systems, an account of the currently used binders and a critical survey of the advanced polymers envisaged for future usage. Special emphasis has been laid on recently synthesized polymers having N-N bonds in their structures, and-on the feasibility of developing smokeless propellants based on ammonium nitrate.

Performance calculations of new propellant systems

The purpose of this thesis is to investigate the effect on performance and chamber temperature of adding hydrogen to a propellant system. The systems investigated are:

(1) RFNA-Aniline

(2) Nitromethane

(3) Anhydrous hydrazene-liquid oxygen

Since a systematic investigation of the performance parameters of the RFNA-Aniline system over a wide range of mixture ratios has never been made, it was decided to make these calculations, in addition to the investigations stated above.

The results of the calculations can best be summarized by a study of the figures at the end of the thesis. A few generalizations can be made. The effect of adding hydrogen in small quantities to a high temperature system is to increase the performance considerably without too much change in the chamber temperature. As more hydrogen is added, the percentage increase in performance. If hydrogen is added in large quantities, both the performance curve (effective exhaust velocity) and the chamber temperature curve flatten out.

The behavior discussed above is characteristic of hot propellant systems such as RFNA-Aniline and anhydrous hydrazene. In a low temperature system, such as nitromethane, the effect is quite different. The addition of hydrogen in small quantities causes a rapid decrease in chamber temperature, but the increase in performance is considerably less on a percentage basis. As more hydrogen is added the changes in performance and chamber temperature are almost linear.

Electrodynamic tether applications and constraints

Propulsion and power generation by bare electrodynamic tethers are revisited in a unified way and issues and constraints are addressed. In comparing electrodynamic tethers, which do not use propellant, with other propellantconsuming systems, mission duration is a discriminator that defines crossover points for systems with equal initial masses. Bare tethers operating in low Earth orbit can be more competitive than optimum ion thrusters in missions exceeding two-three days for orbital deboost and three weeks for boosting operations. If the tether produces useful onboard power during deboost, the crossover point reaches to about 10 days. Power generation by means of a bare electrodynamic tether in combination with chemical propulsion to maintain orbital altitude of the system is more efficient than use of the same chemicals (liquid hydrogen and liquid oxygen) in a fuel cell to produce power for missions longer than one week. Issues associated with tether temperature, bowing, deployment, and arcing are also discussed. Heating/cooling rates reach about 4 K/s for a 0.05-mm-thick tape and a fraction of Kelvin/second for the ProSEDS (0.6-mm-radius) wire; under dominant ohmic effects, temperatures areover200K (night) and 380 K (day) for the tape and 320 and 415 K for that wire. Tether applications other than propulsion and power are briefly discussed.

Liquid rocket engine nozzles /

Cover title.

Titan II storable propellant handbook : final handbook /

"June 1961."