A gyro horizon with laterally inclined axis can prevent the occurrence of the turning errors when the condition y₀=αV/g is atisfied, y0 being the lateral inclination of the gyro axis, V the flyng speed of the airplane, α the precessional speed due to the pendulosity of the gyro system, g the acceleration of gravity. The electrically driven gyro horizon constructed by this principle was examined theoretically and tested in the laboratory and showed very small turning errors. The pendulosity of the gyro system was 60 gr-cm and 105 gr-cm, longitudinally and laterally respectively. y°=10', α=0.0234(rad/sec), v=73.1(m/s)=263(km/h) are the values satisfying the turning error preventhing condition for the inclined axis gyro horizon. The flying speed of the airplane could be increased indefinitely if the special alternating current generator whose frequency is proportional to the flying speed is used for the rotation of the gyro.

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A preliminary experimental study on shock ignition was made by use of shock tubes with a flat end-plate, a conical end-tube and a shock concentration device at the end of the test chamber for the purpose of determining the minimum shock strength capable of igniting various fuel-oxygen and fuel-air mixtures. Ehylene, propane, hydrogen and commercial fuel-gas were used as fuels. The minimum shodk ignition temperature of stoichiometric ethylene-oxygen mixture was found to be between 100°C and 300°C which was considerably lower than those normally associated with the mixture. In order to amplify the strength of the incoming shock, and thus, to economize the initial pressure ratio in the shock-tube, conical end-tubes of various angles and a shock concentration device originated by Kantrowitz were used in place of the flat end-plate. Among them, the shock concentration device was found to be most effective for the purpose and the conical end-tube of 90 deg. to be the next. The effect of mixture ratio on the critical ignition pressure was also investigated and it was found that most of the mixtures except for hydrogen-oxygen mixture had the minimum of the critical ignition pressure near stoiehiometric mixture ratio. When air was used as oxide in place of oxygen, shock ignition of the mixture was a far difficult problem and its igniting region became narrow. Throughout the experiment, it was found that pressure effect on shock ignition was considerabke. Scale effect also seemed to be influencial to the problem.

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