The load factornis produced by the aircraft accelerating upwards at (n− 1)g, wheregis the acceleration due to gravity. In straight and level flight,n= 1 and thrustT= dragD. In a particular maneuver, it is possible to calculate the value of the load factor from which the total lift ...
Load factor in a bank depends only on the angle of bank 1.As the bank steepens, the horizontal lift component increases, centrifugal force increases, and the load factor increases (equation below). 2.If the load factor becomes so great that an increase in angle of attack cannot provide enou...
As these were derived from data on other aircraft, it is likely that a better selection can improve the design. This process will also indicate which of the constraints on the problem are most critical. The equation below, as developed from the specific excess power relationship in Chapter 2,...
A shrinking factor equal to 0.5 is applied to all blending constraints to help the retrieval of a blended solution. 4.1.5 Aileron effectiveness constraints Aileron effectiveness is a crucial parameter for aircraft handling quality. Aileron downwards deflection results in a local lift increment and ...
First, operational load-time histories at critical locations in question of each aircraft are obtained according to the flight-data based load equation and transfer function relating the monitored load to the critical location stresses. Then, the fatigue notch coefficient in local stress-strain method...
Under the circumstance of no digital-analogic simulation system in simulative laboratory this paper presents a dynamic physical simulative method of flight control system for a remote pilotless aircraft on an anologue computer,in which the nonlinear equation of six degrees-of-freedom is adopted and ...
The load characteristics for the flow regulator of a solid ducted rocket are discussed in this paper. The mechanism and the influence factor of the load in the flow regulator were studied both theore...
Design and application of aircraft load simulation loading vehicle The results show that the loaded onboard heavy system can reach a maximum of 50 t, which can simulate the loading effect of all active aircraft with ... J Zhang,XU Wei,Z Quan,... - 《Experimental Technology & Management》 ...
Practical CPLs can be found in aircraft, electric vehicles, ships, spacecraft, telecommunication networks and residential DC loads and many others [5]. CPLs are nonlinear loads that act as a negative incremental impedance. This behavior of this type of load arises from simultaneous increases/...
During a steady glide with zero thrust at 250 m/s EAS in which CL = 0.08, the aircraft meets a downgust of equivalent “sharp-edged” speed 6 m/s. Calculate the tail load, the gust load factor, and the forward inertia force, ρ0 = 1.223 kg/m3. Ans. P = −28 902 N (down)...