Rocket test stand

BAM testing methods 144 165 187 banc d essai = rocket test stand... 

Entzundungstemperatur = deflagration point 75 environmental seal 120 environmental testing > rocket test stand 275... 

R-Salz = cyclotrimethylenetrinitrosa-mine (german) 71 radicals, free radicals 324 Rakete = rocket 275 Raketenflugkorper = missile 218 Raketenmotor = rocket motor 275 Raketenpriifstand = rocket test stand 275... 

In the case of solid fuel rockets, the delay in inflammation, which is determined on a test stand, is understood to mean the time which elapsed between the moment of application of the initiation voltage to the electric inflammation element and the moment when about 10% of the maximum pressure has been attained. Clearly, the magnitude of this parameter depends both on the nature of the firing charge employed and on the ease with which the solid propellant can be initiated. The permitted initiation delay will depend on the objective of the firing. 

Multiple cancers were reported among workers with exposures to rocket engine test stands. I16l Workers in the area were exposed to... 

Our discussion has concerned only rockets fixed to a test stand we consider moving rockets in Sec. 7.5. 

A rocket has the throat area and exit area shown in Fig. 8,15. It is being fired while held down by the test stand. In the combustion chamber the velocity is negligible, the pressure is 200 psia, the temperature is 2000°R, the molecular weight is 201bm/(lbmol), and k is 1.4. The flow through the nozzle is steady and isentropic. What is the thrust of this rocket ... 

Other cryogenic liquid losses in transfer operations result from liquid trapped in the system after loading and unloading. At the Edwards Air Force Rocket Engine Test Laboratory this liquid loss originally amounted to approximately 20 of the test-stand losses [10]. Trapped liquid left in the system may be reduced by the use of auxiliary line and pump sections in the transfer system, permitting return of unused liquid to the storage tank. This may precipitate additional cool-down losses if liquid remains in the test tanks after a run. Accurate control of test liquid requirements will help to minimize these losses. 

F igure 2 shows a t5q>ical rocket engine fuel pump test rig mounted on one of the test stands. The liquid hydrogen is supplied from the storage tanks through the vacuum-insulated line In the foreground. The recirculation system is at the... 

It is evident that the standing pressure wave in a rocket motor is suppressed by solid particles in the free volume of the combushon chamber. The effect of the pressure wave damping is dependent on the concentrahon of the solid parhcles, and the size of the parhcles is determined by the nature of the pressure wave, such as the frequency of the oscillation and the pressure level, as well as the properties of the combustion gases. Fig. 13.25 shows the results of combustion tests to determine the effechve mass fraction of A1 parhcles. When the propellant grain without A1 particles is burned, there is breakdown due to the combushon instability. When... 

The FJ test is similar to an aerodynamic wind-turmel test used for supersonic aircraft, except for the airflow condition. A ducted rocket projectile is mounted on a thrust stand and the projectile and thmst stand are placed in a test chamber. A supersonic airflow simulating the flight conditions is suppHed to the projectile through a supersonic nozzle attached to the front-end of the test chamber. The pressure and temperature in the test chamber are kept equivalent to the flight alHtude conditions. The aerodynamic drag on the projectile and the thmst generated by the ducted rocket are measured directly by the FJ test. The airflow surrounding the projectile and the combustion gas expelled from the ramburner flow out from the exhaust pipe attached to the rear-end of the test chamber. 

FASp. In Rocket Technology it stands for Final Average Sustained Pressure , and refers to die average pressure near the end of a test run before the pressure has begnn to foil off markedly... 

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