Ideal proportional navigation

Abstract

Proportional navigation has been proved to be a useful guidance technique in several surface-to-air and air-to-air homing systems for interception of airborne targets. Besides the familiar pure, true, and generalized proportional navigation guidance laws, a new guidance scheme, called ideal proportional navigation, with commanded acceleration applied in the direction normal to the relative velocity between interceptor and target, is presented. In this study the closed-form solutions of ideal proportional navigation are completely derived for maneuvering and nonmaneuvering targets, and some important characteristics related to the system performance are introduced. Under this scheme the capture criterion is related to the effective proportional navigation constant only, no matter where the initial condition and target maneuver are. With some more energy consumption, this new guidance scheme has a larger capture area and is much more effective than the other schemes. Nomenclature a = acceleration r = distance between interceptor and target T = total time of flight t = time of flight V = velocity v = relative velocity between interceptor and target F = gamma function 6 = angle between line of sight and inertial reference line X = effective proportional navigation constant (/) = angle between relative velocity and line of sight Subscripts c = commanded value / = final value M = missile, interceptor r = parallel to line of sight T = target z = normal to the intercept plane 0 = normal to line of sight 0 = initial value 1 = state at maximum r Superscript ' = time derivative

Guidance laws with input saturation and nonlinear robustH∞observers

“…In the area of homing guidance, proportional navigation (PN) algorithm [1,2] has been widely used because it is highly efficient and easy for implementation, such as true proportional navigation (TPN) [2], realistic true proportional navigation (RTPN) [3], and ideal proportional navigation (IPN) [4]. However, its poor performance in intercepting maneuvering targets has been exhibited because PN has the required accuracy to intercept a nonmaneuvering target or a weakly maneuvering target.…”

Aim Identification with a Minimal Parameter Set

“…In the modified TPN, the commanded acceleration is applied in the direction normal to the LOS and its magnitude is proportional to the product of the LOS angular rate and the closing speed between the missile and aircraft [11]. Generalized proportional navigation (GPN) and ideal proportional navigation (IPN), two more such proportional navigation guidance systems, in which the commanded acceleration is applied in a direction with a fixed bias angle normal to the direction of the LOS and normal to the relative velocity between missile and aircraft, respectively, were presented recently [17], [19].…”

“…There are various guidance systems belonging to the family of proportional navigation. In pure proportional navigation (PPN), the commanded acceleration is applied in the direction normal to the missile's velocity, and the magnitude of the commanded acceleration is proportional to the speed of the missile and the angular rate of the line-of-sight (LOS) between the missile and the aircraft [2], [3], [7], [19]. In the traditional true proportional navigation (TPN), the commanded acceleration is applied in a direction normal to the LOS and its magnitude is proportional to the angular rate of the LOS [11].…”

Analysis of General Ideal Proportional Navigation Guidance Laws

“…The acronym GIPN comes from the guidance velocity vector in the adopted interception scheme being proportional to the relative velocity between the target and missile if the navigation coefficients are constants and equal [1,2]. Although GIPN produces an acceleration command component that cannot be implemented easily in a real missile, it has been extensively studied due to its mathematical tractability.…”