The problem of how to control an airplane required a programmed motion is considered. The actual motion is compared with the programmed one, and if the discrepancies are detected the control surfaces are deflected so as to counteract these deviations. This method is applied to a stunt flying "Cuban eight" and the control surface deflections necessary for the flying are computed.
A method is described to determine hypersonic flow around a two dimensional flat plate at angle of attack. The existing method of integral relations for asymmetric flow has been combined with the constant density solution, which is valid near the axis of symmetry, Examples are presented for various incidence angles at a Mach number of 6. These are compared with results from standard method of integral relations and with available experimental measurements. It is shown that the stagnation points agree with experimental results closer than the standard method of integral relations.
Aerodynamic characteristics of two-dimensional thin aerofoils having narrow gaps are investigated, being based on the limit matching principle. The flow is assumed to be inviscid, incompressible and steady. Both the camber line and the gap location are assumed to be arbitrary. Lift, pitching moment, and center-of-pressure location are given in closed expressions. It is found that blend of the three concepts-limit matching principle, reciprocal theorem, and membrane-makes calculations drastically simple. Applications are presented for flat and circulararc airfoils. The case of deflected fap is also discussed for the arbitrary hinge location at which the gap exists.
Supersonic panel flutter of truncated conical shells has been analyzed by the FEM incorporated with the conical frustum elements. The effects of the internal and external pressure on flutter as well as buckling instability are examined. Numerical calculations are performed on a conical shell with a semivertex angle of 14° having fixed ends. Results are presented for the flutter, vibration and buckling characteristics.
Payload transportation capabilities of space tug are evaluated in general forms for both the specific impulse limited type and the specific power limited type. The payload mass is non-dimensionalized with the propellant mass initially loaded on departure, since the quantity of the propellant which is required to transport the payload will be a predominant factor influencing on the recurring cost of the transportation. The non-dimensionalized payload mass is given in Figs. 1 and 3, for ΔV and J corresponding to the types of propulsion, under the assumption that ΔV or J are the same for both ways of the round trip. Here ΔV=∫adt and J=∫aa2dt where a is the tug acceleration due to thrust. For specific power limited type, the power plant mass is optimized to maximize the non-dimensionalized payload. Results are shown for three cases of payload transportation, i.e. simple placement, simple recovery and round trip with the payload of equal mass, corresponding to δ=0, 1 and 1/2.