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This is the second part of the report titled "A New Running Test Facility for the Study of Flight Dynamics" [1]. A support system for free flight of a model aircraft simulated to V/STOL plane or helicopter has been constructed as an additional equipment for the running test facility. The support system is consisted of a free-flight follower and a data reduction system. The free-flight follower can be carried on a carriage moving on a track and supports the model as it can fly either freely or in partly constrained freedom. The flight path and attitude angles of the model during flight can be sensed with potentiometers on the support system and recorded in oscillograms or stored in memories of a miniature computer through an A-D converter, a part of or all of which are boarded on the carriage as the data reduction system. By analyzing the data the aero and/or flight dynamic characteristics of the model will be obtained., 資料番号: SA2400852000

The most satisfactory way to simulate the low friction aspect of the space environment is by the use of the airbearing technique. This paper presents a design theory of a new spacecraft simulator system installing an airbearing. The 80 cm diameter test table is supported by the 15 cm diameter spherical stainless steel bearing, which is lubricated with compressed air through twelve orifices. As the center of rotation, e. I. the center of the airbearing, can be coincided with the center of gravity of the system by adjusting the balancing weights, the test table can rotate about the spin, pitch and yaw axes with almost negligible friction torque less than 100 mg・cm. Therefore this system is available for studying attitude controls of the sattelite and the control systems. The paper also includes a simple explanation of the structural outline and arrangement of the equipments and the results for the mechanical performance of the facility., 資料番号: SA0125344000

In this report, the flight performances of SSR Rockets, HT-110-1, 2 and 3, under the condition of no cross wind are analysed. These three rockets have slightly different characteristics in total weight, configuration and weight of payload except the engine performance. The calculational results show that the maximum altitudes of trajectories of these rockets are about 20～27km when the launching angle is 70°, and that fairly good coincidence with the results of flight testing, hence especially the adequancy of evaluation of drag coefficients, which will be considered mainly to affect the performance of small rockets such as HT-110 types, was corroborated., 資料番号: SA0124900000

This is the first part of a report for "A New Running Test Facility for the Study of Flight Dynamics". The facility may be used to evaluate the aerodynamic and/or flight dynamic characteristics of a model of aircraft or, specifically, V/STOL aircraft loaded on a carriage which can move on a track by the maximum speed of ten meters per second. If the model is fixed on the moving carriage low speed aerodynamic characteristics of the model may be obtained by using the internal balance systems installed in the model with similar treatment as well known in the wind tunnel excepting that the model is running instead of flowing the air. If the model is supported on "A New Free Flight System", which can be carried on the carriage, as to be able to fly the model freely for specified directions in any given degrees of freedom, then the flight dynamic characteristics of the model may be evaluated by analyzing the data of the model trajectory which are recorded during the test run. The present report includes the detailed description of the design philosophy, simple explanation of the structural outline and arrangement of the equipments, and the test results for the mechanical performance of the facility., 資料番号: SA2400629000

In this report, the body divergence speed and the nutter speed of tail fins of rocket SSR under the actual flight conditions are analysed. The calculational results show that the flutter margin of tail fins is minimum at about M=l.0, which is about 70% of atmosphere value, and that the body divergence margin becomes to minimum at about 5 seconds after launching, not at the maximum flight speed, which is about 50% of atmosphere value. Both the aeroelastic instabilities did not occur in flight testing., 資料番号: SA0124874000

In this report, the effects of cross wind on the dispersion of trajectory of SSR Rocket during burning are analysed. The analytical procedure is as follows; (a) Calculate the flight path angles at the end of burning for various launching angles in the case of no cross wind, (b) Calculate the flight path angles at the end of burning for various values of cross winds, (c) Comparing the results of (a) and (b), determine the effective launching angle under cross wind, which gives same flight path angle at the end of burning in the case of (a). The calculational results show that the corrective angles of launching are approximately + 0.6° for 1m/sec of head wind and -0.6°for 1Im/sec of tail wind., 資料番号: SA0124901000

The small test rocket SSR, Which reached the altitude 25.8km in the latest flying test, is still possible to be improved from the structural point of view. From the results of the ground tests, the weight of some structual parts can be reduced and the reducible total weight is estimated about 30% of the total structural weight. It is shown that this weight reduction is also possible from the aeroelastic point of view. By this improvment, the increase of the maximum attainable altitude of SSR will be about 4. 7 km. Furthermore, this result is compared with the effects of aerodynamical improvement and of the improvement of the propellant., 資料番号: SA0124881000

The general equations of motion are derived for spinning elastic rocket with respect to axes attached to the rocket. The equations contain a force and moment system that includes, in addition to the usual quasisteady forces and moments, those due to Magnus effects. As a result, the stability criteria for spinning elastic rocket are approximately derived, including as special cases, those such as for the case of rigid body and for the case of nonspinning elastic rocket, which have been analyzed. Comparing these analytical results with the digital computational results, the applicability of these stability criteria is examined and from these results, empirical formulas for stability boundaries are also presented. Furthermore, clasifying the stability boundaries into seviral types according to the characteristics of motion of rocket at the critical speed, and the physical meaning of each stability boundary is also explained., 資料番号: SA2404929000

資料番号: SA0125521000