The Test Stand for ORVEAL Series of Combined Rocket Engines

Abstract

As a part of the ORVEAL project, the brand new series of compound rocket engines MEC-80 is subjected to a line of restrictions imposed by the experiment plan, which add an extra weight to the definitely expensive phase of the experimental development of the new types of rocket engine. The direct way to reduce the development time and cost of the new powering systems was found in tediously defining the experimental plan, the variables involved, the nature of the pay-off polynomials and the technological solutions. For the specific case the technological and reliability related constraints are explored, that led to the definition of a reversed-vertical configuration of the thrust frame of the test stand and of the scale and support system of the thrust frame, with position-defined sensors for acquiring the thrust tensor value. Simplicity and reliability were the main requirements in designing and manufacturing the components of the test stand in the new environment of the recently enhanced CEZAR proving grounds of ADDA Ltd. in Fagaras, Transylvania. The ORVEAL research is granted by Romanian UEFISCDI financing authority.

Intricacy of the Transit Manifold Concept Paid-off by Computational Accuracy

“…The evolution of the pressure on the SRE head during the static pressure built-up is definitely linear, confirming the analytical prediction (Rugescu 2001). The static phase is followed by the multiple transits of the expansion waves and further dynamic transients produced by combustion.…”

“…Special attention must be devoted to the intimacy of the mixing process near the burning surface A a and in the chamber channel to enhance the power of the one-dimensional model. Some geometric relations are valid [3] and as a result the following basic equations of motion (mass, impulse H and total energy conservation respectively), in an integral perspective, are valid. To be more specific, let first refer to the thermodynamic behavior of the solid propellant RE, presenting the geometry of the chamber area and the propellant grain depicted in Fig.…”

“…Successful in describing continuous, isentropic flows in aerodynamics, the wave front method [1] proved unsecure for extended gas-dynamical applications in rocket engines (RE) [2], [3]. A new computational front method was thus developed for unsteady flows in WINNDER solar mirror gravity-assisted wind tower (ST) for aeroacoustics [4], [5], [6], [7] is here demonstrated.…”

Conflicting Design Issues Hallmark the Compound Rocket Motors

“…Different liquid oxidizers where investigated through TERMADDA simulations to compare the possible increase in the specific impulse of the CRE versus the equivalent SRM and the increase in the thrust level by the simultaneous increase of the propellant mass through the addition of oxidizer in a maximal amount possible [14]. The A-100 homogeneous solid propellant [15] was investigated due to its availability to ADDA Ltd in large amounts for research and development (Fig.…”

Reentry Design Solution for a Hypersonic Small Capsule

“…The equations of motion in the most general manner, when the flying body executes a general motion, involve the relative fluid mechanics of the internal flow in the engines, relative to a mobile point M, bound to the capsule casing, and consequently are based [32] on the general reaction force equation ( 5) and on the reaction torque equation ( 6)…”