Patent WO-2014027919-A1 (WO)
Title: Front compartment of an aerial vehicle
Inventor: LEONOV ALEKSANDR GEORGIEVICH
IPC: F42B15/34
Filed: 2013-02-15
Abstract: The invention relates to a controllable missile weapon, and more specifically, to the design of aeroballistic missiles (ABMs) with target-seeking guidance in the final portion of the trajectory. The problem addressed by the proposed invention is that of creating a front compartment (FC) of an aerial vehicle (primarily an ABM) with the possibility of simultaneously assembling therein a plurality of active and/or passive on-board front sensors for target-seeking guidance and/or a route-navigation system, said front compartment being aerodynamically efficient in terms of drag and the level of cross-communications between control channels, and permitting the possibility of independent roll stabilization of the on-board guidance and/or navigation systems. The problem mentioned is solved in that, in the front compartment of an aerial vehicle (AV), said compartment comprising a leading panel with flat illuminators and a lateral shell with a junction frame, the leading panel is in the form of a wedge, with a flare angle of the wedge planes of 60...170 degrees in the pitching plane of the AV, in which a minimum of one flat illuminator is installed, and the lateral shell is formed axisymmetrically with an alternating section along the external contour, and with a maximum section diameter in the plane of the junction frame. When two or more illuminators are installed, said illuminators can have different spectral transmission ranges. Furthermore, the lateral shell is formed as follows: conically - with an angle of inclination of the generatrix of the cone to the plane of the junction frame of 60...89 degrees, biconically - with an angle of inclination of the generatrix of the leading cone to the plane of the junction between the leading cone and trailing cone of 60...89 degrees, and with an angle of inclination of the generatrix of the trailing cone to the plane of the junction frame of 15...89 degrees. The generatrix of the profile of the lateral shell can also be constructed to be ogival, parabolic, in the form of a spline and as a combination of said forms. A prismatic or cylindrical insert which can be optically transparent or radar-transparent can be formed in the lateral shell of the FC. The front compartment of the AV can also be constructed with the possibility of the leading panel and of part of the lateral shell adjacent thereto rotating relative to the longitudinal axis of the AV. Furthermore, the rotatable part of the FC can be separated from the immovable part by a hermetic membrane. A bearing can be installed in the separation plane between the rotatable and immovable parts of the FC. Heat insulation can be installed on the FC of high-velocity AVs on the internal side of the lateral shell and leading panel, excluding the illuminators. Furthermore, the heat insulation can be formed from material having a phase transition within a temperature range of 30...75 degrees Celsius. Moreover, the illuminators can be covered on the internal side by movable heat-insulating plates. The front compartment of high-velocity AVs can also be provided with an aerodynamic needle, including with the possibility of stowing the latter: for example, telescopically within the FC or with a prefiring inclination to an angle of up to 120 degrees relative to the longitudinal axis of the AV. The positive effect which is achieved when the technical solution presented is used comprises: - the possibility of efficiently assembling a front compartment on high-velocity AVs with high-precision on-board guidance and/or flight trajectory correction systems, including multi-channel active and/or passive systems; - the possibility of varying the quantity of autonomous guidance/navigation channels of the AV for an FC of fixed geometry; - the possibility of stabilizing the on-board guidance/navigation systems of the AV by roll control by means of independent stabilization of the rotatable part of the FC. At the same time, the front compartment according to the proposed technical solution can comprise additional elements (components, units, mechanisms, etc.) making it possible to ensure normal operation of the article under conditions of extreme air velocity pressures, heat flows, heavy-duty loads, vibration and other flight factors characteristic of modern and prospective AVs.