Analysis of generic reentry vehicle flight dynamics

IET Radar, Sonar & Navigation, 2007

Theoretical bounds for estimating the ballistic coefficient of a ballistic object during the re-entry phase have been addressed. One essential characteristic of the vehicle trajectory is its deceleration when it reaches dense atmospheric layers. The intensity of the phenomenon is proportional to a scalar, called the ballistic coefficient. This leads to an highly nonlinear time-varying dynamic. To understand the dimensioning parameters for estimating the ballistic coefficient, accurate approximations of the Fisher information matrix are developed. The main result is a closed-form expression of a lower bound for the variance of the ballistic coefficient estimate.

Advances in Military Technology, 2019

This paper deals with one of the possible methods of a qualified estimation of tactical and technical parameters of surface-to-air or air-to-air guided missiles. This method is designed to estimate missile flight parameters if they are unavailable from public sources. Although the method does not provide exact values, it is sufficient for modelling and subsequent simulation. This method is based on the use of so-called "characteristic numbers" of the missile and on the assumption of validity of the hypothesis about the similarity of characteristic missile numbers of equal or, respectively, similar technological levels. To validate the obtained parameters, a method of mathematical modelling of the missile guidance process is used. The method can also be used for a qualified estimation of missile parameters in the case of an acquisition process.

13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference, 2010

International Conference on Aerospace Sciences and Aviation Technology, 2015

Separating a reentry vehicle into warhead and body is a conventional and efficient means of producing a huge decoy and increasing the kinetic energy of the warhead. This procedure causes the radar to track the body, whose radar cross section is larger, and ignore the warhead which is the most important part of the reentry vehicle. The aerodynamic Coefficients models play an essential part in the simulation and the analysis of the supersonic and hypersonic of the ballistic missiles, especially in the dynamic trajectory planning. This paper builds the aerodynamic coefficients models by the nonlinear least square method based on the separable warhead re-entry vehicle using lebedev aerodynamic calculations. The lift and drag coefficients models can be expressed with the polynomial and the exponential function. So the models fit the aero characteristic well and can be used in practical design and simulation as a reference.

A Missile is a self-propelled guided weapon system that travels through air or space. A powered, guided munitions that travels through the air or space is known as a missile (or guided missile). The Missile is defined as a space transversing unmanned vehicle that contains the means for controlling its flight path. The aerodynamic characteristics of a missile components such as body, wing and tail are calculated by using analytical methods to predict the drag and the normal forces of the missile. The total drag of the body is computed by using the parasite drag, wave drag, skin friction drag and base drag. The wing surface normal force coefficient (C N) Wing is a function of Mach number, local angle of attack, aspect ratio, and the wing surface plan form area (C N) Wing , based on the missile reference area, decreases with increasing supersonic Mach number and increases with angle of attack and the wing surface area. When the wing surface area is reduced the total weight of the missile and drag are reduced thereby increasing the lift and achieve excessive stability.

Mathematical and Computer Modelling, 2009

A mathematical model is developed for an anti-tank missile and its guidance algorithms. The aerodynamic model is separated into two parts, the airframe and external lifting surfaces in order to model damage to the airframe. Radar data is compared to that of the proposed model and it is shown that the model accurately replicates the true flight dynamics. Two types of field handling damage are modeled, a damaged mid-body wing with 50% of its planform area missing, and an un-deployed mid-body wing. Monte Carlo simulations are performed for each type of damage and the eight possible mid-body wing locations. The results predict that the anti-tank guided missile's performance in response to damage is extremely sensitive to the radial location of damage. Vertical mid-body wing damage had little effect on performance while damage to horizontal and adjacent midbody wings resulted in significant failures. The failure mode demonstrated was not a large increase in impact errors, but rather failure of the seeker used for guidance due to excessive roll and yawing of the airframe.

IEEE Transactions on Aerospace and Electronic Systems, 2000

In this paper an acceleration model and a jerk model are proposed for estimation of the kinematic state of reentry ballistic targets (RBTs) using extended Kalman filters (EKF). The models proposed here use the equations of target kinematics only and do not assume any model parameterization for variation of the ballistic coefficient and air density a priori, as found in the literature. The novelty lies in estimation of the ratio (°) of air density and ballistic coefficient and its time derivatives using a separate Kalman filter (KF) (°-filter) which utilizes pseudo measurements of°computed from the velocity and acceleration estimated by the EKF at each time step. The parameter°and its derivatives estimated by the°-filter are, in turn, used for the estimation of position, velocity, acceleration, and jerk in the EKF. The use of the pseudo measurements of°makes the algorithms inherently adaptive to variations of the ballistic coefficient and air density during reentry. A comparative assessment of several dynamic models for reentry of ballistic targets reported in the literature and those proposed here demonstrates that the estimation errors in velocity and acceleration are significantly less for the proposed models compared with the existing ones.

4th Atmospheric Flight Mechanics Conference, 1978

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