The weight factor needs careful distribution across the fusilage. This is to maintain balance and also airframe stress. Documentation is used to provide safety inspections and prove that pilots and ground crews follow specific procedure.
To calculate the maximum takeoff weight, you need to consider the maximum weight that the aircraft structure can safely support during takeoff. This weight includes the combined mass of the aircraft, passengers, cargo, and fuel. The maximum takeoff weight is determined by the aircraft manufacturer and is usually documented in the aircraft's performance specifications.
When we did weight and balance on the small piston engine aircraft I trained on we always used 9lb per U.S. gallon
Aircraft weight limits set by the manufacturer or aviation regulators. Type and size of cargo being transported. Balance and distribution of cargo to ensure proper weight distribution within the aircraft.
Jet fuel is measured in pounds because it is a unit of weight that is used to quantify the amount of fuel loaded onto an aircraft for safe operation. By measuring jet fuel in pounds, it allows for accurate calculation of the weight and balance of the aircraft during flight planning and ensures that the aircraft stays within its weight limitations for takeoff and landing.
It is entirely up to the manufacturer of the aircraft. Usually it is an imaginary point forward of the nose of the aircraft and all points aft of that datum have a positive value. This makes weight and balance calculations easier as there are no negative numbers.
Ya know when you destroy some enemy aircraft, they go neutral (yellow)? You need to balance the destruction of the neutralized aircraft.
The term TE MAC stands for Trailing Edge Mean Aerodynamic Chord. It is the average distance between the leading and trailing edge of an aircraft's wing, taken at the trailing edge of the wing. This measurement is important for calculating the aircraft's balance and stability.
The design process has to take into account weight, lift, drag and thrust. For example smaller engines require larger flying surfaces. Fighter aircraft have less wing square area and have stronger thrust jet engines. Such are the tolerances in modern aircraft that they are generally designed to carry twice there recommended loadings.
When considering cargo for selection on a specific airframe, you should consult the aircraft's Weight and Balance Manual, Aircraft Flight Manual, and any specific cargo loading procedures provided by the aircraft manufacturer. These publications will provide you with important information on weight limitations, cargo compartment configurations, and loading restrictions specific to the aircraft.
Aeronautical engineer is the one who designs aircraft. In the olden days before the inception of aeronautical engineer profession, aircraft designs were prepared by civil engineers. This is the main reason why old aircraft design employed many trusses in the structures because of such they were heavy. One modern design principle is the so called weight-to-strength ratio which contemplates the balance of the aircraft weight and structural strength. Thus, a good aircraft must be lightweight and at the same time structurally strong.
Yes, trapped fuel is included in the basic weight of an aircraft because it represents the weight of fuel that cannot be used for flight. This weight is accounted for in the aircraft's operating weight calculations.