First Operational Experience with DORIS II
DORIS II is a completely new designed e+-e- storage ring with a mini-beta scheme. After first runs with a 8 cm optic, the vertical amplitude functions in the interaction points were reduced to 4 cm. This yielded luminosities of L = 1.5 . l031 cm-2sec-1 with 2 × 27 mA at E = 5 GeV. Because of the short injection time, an integrated luminosity of more than 600 nb-1 per day has been obtained.
Doris II, an e+-e− Storage Ring with Mini Beta Sections
A significant increase in luminosity can be achieved at DORIS by installing additional quadrupoles in the two experimental regions 1.2 m away from the interaction points. At one interaction point these quadrupoles will be mounted in the yoke of the magnetic detector ARGUS. In order to shield the quads from the detector field of.8 Tesla two types of compensating coils will be installed inside the detector. With these “mini-beta-quads” it is possible to reduce the beta functions at the interaction points toβ =.4 m and β*z =.03 m. The expected luminosity at 5 ǦeV with maximum currents of 2 × 35 mA is L = 1.0 × 1031 cm−2 sec−1.
THE PERFORMANCE OF STEADY DETONATION ENGINES
Propulsion systems driven by steady normal detonations are studied. The practical di‐culties associated with stabilizing a detonation wave are highlighted. The requirement on the freestream total enthalpy is considered in parallel with efiects such as condensation or auto-ignition of the fuel-air mixture and limitations associated with fuel sensitivity to detonation. A criterion for detonation stabilization is formulated and applied to an analytical treatment of a detonation ramjet and a detonation turbojet, which are the respective analogs of the ramjet and the turbojet using detonative combustion. The performance of these engines is evaluated and compared to the ideal ramjet and turbojet models for hydrogen and JP10. A limitation is placed on the maximum total temperature allowed in the combustor, based on material considerations. The results show that steady detonation engines have a small thrust-producing range, due to the requirements for detonation stabilization. Their performance is always lower than that of the conventional ramjet and turbojet because of the total pressure loss across the detonation.