Survey on the mode transition technique in combined cycle propulsion systems

New Method for Solving One-Dimensional Transonic Reacting Flows of a Scramjet Combustor

“…(1)(2)(3)(4)(5), p is the pressure, T is the temperature, ρ is the density, u is the velocity, W is the molecular weight of the mixture, _ m is the mass flow rate, _ ω i is the generation rate of species i, Y i is the mass fraction of species i, C f is the wall friction coefficient, D is the equivalent diameter, ε is the fuel jet orientation factor, h t is the stagnation enthalpy, h aw is the stagnation enthalpy at an adiabatic wall, h w is the stagnation enthalpy at the wall, c p is the constantpressure specific heat, and Pr is the Prandtl number. Equations (1)(2)(3)(4)(5) represent the conservation of mass, momentum, energy and mass of each species, and the equation of state. In these equations, the wall heat transfer is calculated from the definition of the Stanton number, which is related to the friction coefficient by a Reynolds analogy.…”

“…(1)(2)(3)(4)(5) to find the solution of the flow, there is another method called the Mach number influence coefficient method that can also be used. In this method, an ODE about the Mach number is used as the governing equation.…”

“…(6) into a differential form and combining Eqs. (1)(2)(3)(4)(5), the differential form of the Mach number along the duct can be written as…”

“…The greatest advantage of a scramjet engine is that it yields a higher specific impulse than other types of engines for hypersonic flight [1][2][3][4][5]. Unfortunately, the single-mode design and operation of a scramjet engine cannot provide satisfactory performance to cover a wide flight trajectory from Mach numbers of 4 to 10.…”

Switching control of thrust regulation and inlet unstart protection for scramjet engine based on strategy of integral initial values resetting

“…Several control methods have been proposed in the control problem of scramjet engine [3,[8][9][10][11][12][13][14][15][16]. Most of these studies focused on the inlet control or the combustion control separately.…”