The present invention relates to aeronautical engineering and is intended for use when manufacturing aircrafts.
There has been known an aircraft comprising, inter alia, a fuselage, a wing, a tail unit, a landing gear, main and auxiliary power plants, a system for controlling a general-purpose aircraft equipment having two automatic control loops structurally embodied in the main and reserve conversion and calculation units that are connected to actuators through a monitoring and control unit. A manual control loop is provided with control panels, an enunciator panel and a central signal light. A control system is engaged via a multiplexer channel with a set of on-board digital computers, electronic control systems of port and starboard engines, a recording and monitoring system, a guidance and landing equipment and a complex control system. Said control system is engaged through code communication lines with a fuel control and monitoring system, a voice message equipment, a complex electron display system and said auxiliary power plant (RU 2263044 C1, B 64 C 13/00, Oct. 27, 2005).
The drawback to the known aircraft is associated with the need for improving its survivability, decreasing mass-dimensional characteristics and realizing conditions of multipurpose.
There has been known a light multi-purpose aircraft at enhanced maneuvering properties comprising, inter alia, a fuselage, a wing, a fin assembly, a landing gear, a power plant and a controlling integrated complex consisting of an information exchange system, an on-board digital computer system for controlling flight and training and combat operations, an external storage and an information input system, a radio inertial navigation and landing system, a complex aircraft control system with consoles arranged in a pilot and operator cockpit, an armament control system with consoles arranged in a pilot and operator cockpit, a complex system for electronic display, control and sighting, an emergency warning board, a two-fold redundant aircraft equipment control system, an on-board objective monitoring system, a speech information control system, an electric power supply system, internal and external lighting facilities, an emergency escape complex system, a two-fold redundant power plant control system. In doing so, the information exchange system is divided into three independent multiplexer information exchange channels, radial couplings are made between the computing system and the aircraft equipment control system and also between the complex system for electronic display, control and sighting and the complex aircraft control system (Patent RU 2252899 C1, B64C 13/00).
The drawback to the known aircraft is also associated with the need for improving its survivability, decreasing mass-dimensional characteristics and realizing conditions of multipurpose.
The closest prior art to be used for the claimed invention is the SU-25 attack aircraft (see, Bedretdinov I.A., The SU-25 Attack Aircraft and Its Derivatives, M., OOO “B & Co Publishing Group”, p. 15) comprising a fuselage; a wing; a fin assembly; a landing gear; a power plant and also a controlling complex incorporating an information exchange system; an on-board digital computer system for controlling flight; a radio inertial navigation and landing equipment; an aircraft control system with consoles arranged in a pilot cockpit; an armament control system with consoles arranged in a pilot cockpit; a system for electronic display, control and sighting; an emergency warning board; an electric power supply system; lighting facilities; a crew protection system; an emergency escape system; a power plant control system in which said crew protection system is made in the form of essentially complete armoring of the bottom of a crew cabin (cockpit) and partial armoring of the walls of consumable fuel tanks and also partial armoring of engine nacelle bonnets from bullet-dangerous directions. In addition, an armored helmet and armored vest form a part of the pilot equipment.
The drawback to the known aircraft consists in inconsistency of its mass-dimensional characteristics and survivability characteristics with the specifics of using thereof as a light multi-purpose aircraft.
It is an object of the present invention to create a light multi-purpose aircraft enabling improvements in its survivability, decrease in mass-dimensional characteristics and realization of conditions of multipurpose.
The present invention is explained by the following drawings in which:
With reference to
When the destruction means (7.62 mm caliber bullets) hit the aircraft from the aspect angle A (at the front—from below;
A type II injury zone is located from the aspect angles B (from below—at the front;
The aspect angle D (
Breaking-down into injury zones according to I, II and III types may be, if necessary, yet more detailed.
Such an approach enables provision of optimal efficiency of the crew protection in terms of both an additional weight within the aircraft and minimization of sophistications in the aircraft design.
The above measures leading to the improved aircraft survivability make it possible to increase the probability of a pilot invulnerability:
Optimal use of the screening, selection of the most likely aspect angles of approaching the destruction means and also the destruction means themselves which are the most likely for the aircraft, enable decrease in additional crew protection expenditure from 300 Kg to 95 Kg, i.e. about one-third as large.
By this means the proposed scheme for protecting the aircraft crew cabin with a substantial decrease in additional weight for armoring enables increase in the probability of a pilot invulnerability by approximately 40 percent.
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/RU2007/000381 | 7/11/2007 | WO | 00 | 10/8/2009 |