Reusable launch vehicle propulsion based on the RD-0120 engine

Goncharov, N. V.; Орлов, В. В.; Rachuk, V. S.; Shostak, Arthur B.; Starke, R. G.

doi:10.2514/6.1995-3003

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…These inserts can be either ablative or ejectible. The inserts may have the form of a complete secondary nozzle 23 (Fig. 12), or of small steps attached inside the nozzle wall.…”

Section: Nozzles With Temporary Insertsmentioning

confidence: 99%

“…Recent hot-ring tests performed in Russia with a modi ed RD-0120 engine, equipped with a secondary nozzle insert, revealed a signi cant performance gain of 12% during the sealevel operation at 100% chamber pressure, compared with the original RD-0120 performance. 23 Nominal chamber pressure of this engine is p c = 206 bar, with an area ratio of « = 85.7. These full-scale, hot-ring tests demonstrated the durability of materials, sealings, and the release mechanism and, thus, the feasibility of this concept.…”

Section: Nozzles With Temporary Insertsmentioning

confidence: 99%

“…Figure 12 shows the nozzle hardware and a sketch of the secondary nozzle mounted inside the RD-0120 nozzle. 23 The principle performance characteristics of this RD-0120 nozzle with ejectible insert are included in Fig. 13.…”

Section: Nozzles With Temporary Insertsmentioning

confidence: 99%

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Several nozzle concepts that promise a gain in performance over existing conventional nozzles are discussed in this paper. It is shown that signi cant performance gains result from the adaptation of the exhaust ow to the ambient pressure. Special attention is then given to altitude-adaptive nozzle concepts, which have recently received new interest in the space industry. Current research results are presented for dual-bell nozzles and other nozzles with devices for forced ow separation and for plug nozzles with external freestream expansion. In addition, results of former research on nozzles of dual-mode engines such as dual-throat and dual-expander engines and on expansionde ection nozzles are shown. In general, ow adaptation induces shocks and expansion waves, which result in exit pro les that are quite different from idealized one-dimensional assumptions. Flow phenomena observed in experiments and numerical simulations during different nozzle operations are highlighted, critical design aspects and operation conditions are discussed, and performance characteristics of selected nozzles are presented. The consideration of derived performance characteristics in launcher and trajectory optimization calculations reveal signi cant payload gains at least for some of these advanced nozzle concepts.

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“…These inserts can be either ablative or ejectible. The inserts may have the form of a complete secondary nozzle 23 (Fig. 12), or of small steps attached inside the nozzle wall.…”

Section: Nozzles With Temporary Insertsmentioning

confidence: 99%

Section: Nozzles With Temporary Insertsmentioning

confidence: 99%