Author name: Akash Babu S L

The Aircraft Maximum Range Equation calculates the maximum distance an aircraft can travel without refueling R: Maximum Range V: True airspeed D: Drag

Satellite Orbital Inclination is the angle between the orbital plane and the equatorial plane of the Earth.   i: Orbital inclination, the angle between the orbital plane and the equatorial plane of the Earth. ℎy​: The y-component of the satellite’s specific angular momentum. ℎ: Magnitude of the specific angular momentum.

Fuel efficiency in aircraft design refers to the ability of an aircraft to cover a certain distance using the least amount of fuel.   Fuel Efficiency is the efficiency of an aircraft in terms of fuel consumption, Specific Fuel Consumption  : the amount of fuel consumed per unit of thrust or power produced by the  engines.

The glide ratio (L/D) is a measure of how efficiently an aircraft can convert altitude into horizontal distance during unpowered flight.   L/D is the glide ratio, CL​ is the coefficient of lift, CD​ is the coefficient of drag.

Thermal Noise Power represents the power of thermal noise generated in a resistor at temperature T across a given bandwidth B   Pn​ is the thermal noise power, k is Boltzmann’s constant T is the temperature in Kelvin, B is the bandwidth of the communication system.

Satellite Solar Panel Power helps determine the electrical power output from solar panels based on their efficiency   P is the power generated, A is the effective area of the solar panels, η is the efficiency of the solar panels, I is the solar flux or irradiance.

The spacecraft propulsion efficiency represents the effectiveness of a propulsion system   Efficiency is the spacecraft propulsion efficiency. Isp​ is the specific impulse of the propulsion system. g0​ is the standard acceleration due to gravity C∗ is the characteristic exhaust velocity.

The Propellant Mass Fraction is a key parameter used in rocket design to quantify the proportion of the rocket’s initial mass that is contributed by the propellant   PMF is the propellant mass fraction. mp​ is the mass of the propellant. mi​ is the initial mass of the rocket (including the mass of the propellant).

The Mass Ratio is a measure of the efficiency of a rocket’s propulsion system   R is the mass ratio. mi​ is the initial mass of the rocket (including propellant) before staging. mf​ is the final mass of the rocket (excluding the mass of the jettisoned stage) after staging.