RU2807624C1 - Multi-functional two-seat stealth aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: multifunctional two-seat stealth aircraft with an integral aerodynamic layout contains a complex of on-board equipment, a fuselage with an overflow, wing consoles with mechanization of the leading and trailing edges, including flaperons, ailerons and rotating wing tips, consoles of an all-moving horizontal and two-fin vertical tail unit mounted on the side tail booms of the fuselage, a two-seat a cockpit with a canopy, a garrot and a radome of the locator antenna, located in the forward part of the fuselage, a power plant with two engines spaced horizontally and equipped with air intakes, located in engine nacelles, the axes of which are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. The aircraft is characterized by the fact that the wing consoles are smoothly coupled with the fuselage, the fuselage overhang is located above the engine air intakes and includes controlled rotating parts, the aircraft engines contain a jet nozzle with a deflectable thrust vector and thrust reverser, the all-moving vertical tail is installed at an acute angle to the vertical plane of the aircraft, the console the wings are trapezoidal in plan with a large sweep along the leading edge with a sweep angle of 49° along the leading edge and with small values of relative wing thicknesses ranging from 3% to 5%, while the area for placing the cockpit, garrot and radar antenna fairing is formed by orienting the tangents to the contour of the cross sections of the fuselage at an angle to the plane of symmetry of the aircraft, and the shape of the surface of the cockpit canopy is formed with angles of inclination of the side tangents to the vertical plane of the aircraft in the range of 20°-30°, in the middle part of the fuselage between the engine nacelles there are payloads, as well as additional fuel tanks. On the upper surface of the cargo compartments there are attachment points for ejection devices for aviation weapons, while the complex of on-board equipment is designed with the possibility of information interaction between different types of aircraft of the group, including in terms of receiving and transmitting data via high-speed communication channels and group communication, including via satellite communication channels, as well as analyzing information coming from its own systems and external sources with the subsequent issuance of recommendations to the crew and/or commands to a group of aircraft, and the cockpit is equipped with controls to transfer control priority from one pilot to another and, according to at least two multifunctional panoramic indicators for controlling the aircraft and weapons.

EFFECT: invention makes it possible to reduce the level of visibility of an aircraft in the radar range, increase the maneuverability of the aircraft, increase the level of aerodynamic characteristics of the aircraft, expand the functionality of the aircraft in terms of information and communications interaction, including in the absence of satellite and long-distance short-wave communications, expand the range of weapons used, increase the flight range of the aircraft, as well as expand the range of altitudes and flight speeds.

4 cl, 6 dwg

Description

The invention relates to the field of aviation, namely to multifunctional two-seat stealth tactical aircraft and is intended to detect and destroy air, surface and ground targets at super- and subsonic flight speeds in a wide range of altitudes, as well as acting as an airborne command post for network-oriented operations mixed groups of aircraft.

The following multifunctional two-seat tactical aircraft are currently known: Dassault Rafale, Eurofighter Typhoon EF-2000, Saab JAS-39NG Grippen, Boeing F/A-18F Super Hornet, McDonnel-Douglas F-15D, Cy-30MK family of aircraft, MiG- 35.

Single aircraft of the integrated aerodynamic layout (patent RU 2400402, MPC B64C 30/00, published on 09/27/2010, Patent RU 2502643, MPC B64D 7/00, publ. 12/27/2011, Patent RU 2440916, MPC B64D 27 are widely known. /20, published 01/27/2012).

Of the analogues presented above, the closest are the aircraft of the Su-30MK family (“Multipurpose highly maneuverable supersonic aircraft, its airframe units, equipment and systems” according to patents RU 4109U1, MPK V64S 30/00, published 05/16/1997; RU 2207968, MPK V64S 30 /00, published July 10, 2003).

The common features of the declared two-seat aircraft and the two-seat Su-30MK aircraft include the following:

- the aerodynamic layout is made according to the integral principle with a smooth coupling of the wing and fuselage;

- the presence of two consoles of all-moving horizontal tail;

- the presence of two vertical tail consoles;

- the power plant is represented by two spaced apart engines with isolated input devices (air intakes);

- two-seater tandem-type crew cabin with a folding canopy.

The disadvantages of the well-known multifunctional two-seater aircraft include the following:

- the shaping of the airframe surface does not allow achieving a low level of visibility in the radar range, which in modern conditions significantly reduces the effectiveness of the combat use of the aircraft;

- the placement of cargo on the external sling also does not allow achieving a low level of visibility in the radar range and creates an increased level of aerodynamic drag in all flight modes of the aircraft;

- limited capabilities of the on-board equipment complex in terms of integrated data processing and work in network-oriented operations in mixed formations of tactical aircraft and in interaction with other branches of the military.

The problem to be solved by the invention is to create a two-seat multifunctional aircraft of an integral aerodynamic configuration with a low level of radar signature, designed to destroy air, ground and surface targets with guided and unguided weapons, capable of acting as an airborne command post for network-oriented operations of mixed groups of aircraft and , as a consequence of this, having a significantly higher level of effectiveness in combat use.

The technical result of the claimed invention is to reduce the level of visibility of the aircraft in the radar range, increase the maneuverability of the aircraft up to super-maneuverability, increase the level of aerodynamic characteristics of the aircraft at super- and subsonic flight speeds, expand the functionality of the aircraft in terms of infocommunication interaction, including in the absence of satellite and long-distance shortwave communications and expanding the range of weapons used, increasing the ferry range of the aircraft, increasing the operational manufacturability of the aircraft, as well as expanding the range of altitudes and flight speeds.

The given technical result is achieved by the present invention. A multifunctional two-seat stealth aircraft with an integral aerodynamic layout contains a complex of on-board equipment, a fuselage with an overflow, wing consoles with mechanization of the leading and trailing edges, including flaperons, ailerons and rotating wing tips, consoles of an all-moving horizontal and two-fin vertical tail mounted on the side tail booms of the fuselage, a two-seat a cockpit with a canopy, a garrot and a radome of the locator antenna, located in the forward part of the fuselage, a power plant with two engines spaced horizontally and equipped with air intakes, located in engine nacelles, the axes of which are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. The aircraft is characterized by the fact that the wing consoles are smoothly coupled with the fuselage, the fuselage overhang is located above the engine air intakes and includes controlled rotating parts, which are the leading edges of the middle flattened part of the fuselage, the aircraft engines contain a jet nozzle with a deflectable thrust vector and thrust reverser, an all-moving vertical tail is installed at an acute angle to the vertical plane of the aircraft, the wing consoles are made of a trapezoidal shape in plan with a large sweep along the leading edge with a sweep angle of 49° along the leading edge and with small values of the relative wing thicknesses, ranging from 3% to 5%, while the placement area The cockpit, garrot and radome of the locator antenna are formed by orienting the tangents to the contour of the cross sections of the fuselage at an angle to the plane of symmetry of the aircraft, and the shape of the surface of the cockpit canopy is formed with the angles of inclination of the side of the tangents to the vertical plane of the aircraft in the range of 20° - 30°, in the middle part of the fuselage between the engine nacelles there are arranged with the possibility of placing and using payloads in flight, as well as connecting additional fuel tanks to the aircraft fuel system, cargo compartments, on the upper surface of which there are attachment points for ejection devices for aircraft weapons, while the onboard equipment complex is made with the ability to provide, through the aircraft information and control system, information interaction between different types of aircraft of the group, including in terms of receiving and transmitting data via high-speed communication channels and group communication, including satellite communication channels, as well as analyzing information coming from its own systems and external sources with the subsequent issuance of recommendations to the crew and/or commands to a group of aircraft, and the cockpit is equipped with controls for transferring control priority from one pilot to another and at least two multifunctional panoramic indicators for controlling the aircraft and weapons.

The aircraft is also characterized by the fact that the lower tail part of the fuselage is equipped with ventral ridges, the plane of the chords of which forms an angle with the vertical plane of the aircraft, while the all-moving vertical tail is mounted on pylons mounted on the side tail booms of the fuselage, and the all-moving vertical tail is made with the possibility of in-phase and differential deviations.

The proposed aircraft design has the following advantages.

Due to the integral aerodynamic layout of the aircraft, which has greater lifting force compared to aircraft with separate airframe components, the use of a modern complex of on-board equipment, including the cockpit information and control field and a communications complex (one and a half times larger display area on multifunctional indicators and the number of frame buttons to control them, increased communication range and data transfer speed via communication channels), as well as the use of universal cargo compartments, providing the ability to accommodate and use a wide range of replaceable target load modules from them.

The low level of radar signature of a two-seat multifunctional aircraft is achieved through the following technical solutions:

- shaping the surface of the fuselage, in particular in the area where the double cockpit, garrot and radome of the locator antenna are located, by orienting the tangents to the contour of the cross sections of the fuselage at an angle to the plane of symmetry of the aircraft. This contributes to the reflection of electromagnetic waves into the upper and lower hemispheres, falling on the airframe elements from lateral angles, thereby reducing the overall level of radar signature of the aircraft in the lateral hemisphere;

- shaping the surface of the canopy of a two-seat cabin with optimal values of side inclination angles (the range of side inclination angles to the vertical is 20...30°) tangent to the vertical plane of the aircraft. This law for specifying the cross sections of the cockpit canopy makes it possible to achieve a minimum level of radar signature while ensuring the required mass of the detachable part of the canopy (OCF) in order to implement the characteristics of the emergency compartment of the CPF. These characteristics are achieved by ensuring the reflection of electromagnetic waves hitting the airframe elements from lateral angles into the upper hemisphere, thereby reducing the overall level of radar signature of the aircraft in the lateral hemisphere. At the same time, the design of the lamp is ensured, allowing to minimize its weight and dimensions;

- placement of universal cargo compartments in the middle part of the fuselage;

- installation of an all-moving vertical tail at an acute angle to the vertical plane;

- the tail booms of the aircraft fuselage are made with the possibility of installing ventral ridges on them;

- minimizing the number of hatches on the outer surface of the fuselage due to the implementation of design and layout solutions (access to on-board equipment units and assemblies is organized through a minimum number of hatches with an increase in the layout density of the serviced units) and the organization of an instrumentation compartment with increased conditions for quality service through the niche of the front landing gear ;

- making fuselage sides and vertical aerodynamic surfaces with slopes in one direction from the vertical axis of the aircraft.

The ability to use a two-seat multifunctional aircraft as an air control point, with the ability to ensure interaction between aviation and military formations when solving combat missions, analyzing information coming from its own systems and external sources of information with the subsequent issuance of recommendations to the crew and commands to the group’s aircraft, as well as as a control point for unmanned aerial vehicles, is achieved through a wide range of communications equipment, including satellite communications, equipment for group transmission of information, equipment for transmitting information over long distances and a high-speed communication channel for receiving and transmitting audio, photo, video, text, voice and telecode information and a specialized command and information field of the rear cockpit (which, compared to the front cockpit, has the following differences: an expanded panoramic aviation indicator and an additional indicator to increase the operator’s working field, controls are installed to transfer control priority from one cockpit to other, and also excludes governing bodies that do not require control by a second crew member), which allows you to quickly receive information from various external sources (both aviation, land and sea), analyze it on board the aircraft and issue recommendations or commands on carrying out a combat mission by the group's aircraft, taking into account their fuel reserves and combat equipment.

An increase in flight range and duration is achieved by increasing the fuel tanks by 10% compared to the prototype when changing the geometric contours of the airframe due to the placement of a second crew member, as well as by placing detachable fuel tanks in the cargo compartments of the aircraft.

The use of various aircraft weapons in a stealthy configuration, as well as unmanned aerial vehicles, inserted fuel tanks and other replaceable target modules from the cargo compartment of a two-seat multifunctional aircraft is achieved due to the design of the cargo compartment (two cargo compartments are located one after the other along the plane of symmetry of the aircraft between the engine nacelles airframe. The compartment consists of structural elements (walls, hatch flaps, etc.), a deflector, flap drives, and structural elements that ensure opening and closing of the compartment. On the upper surface of the compartment there are attachment points for universal ejection devices on which aircraft are placed destruction), made universal, a complex of aircraft on-board equipment capable of ensuring the functioning of replaceable target modules (replaceable target modules (payload) mean the following elements that can be placed in the cargo compartment: aircraft weapons, insertable fuel tanks, unmanned aerial vehicles launch, containers with reconnaissance equipment, containers for personal belongings of the crew and containers for ground support equipment during relocation), as well as general aircraft systems that provide the necessary conditions for the functioning of the payload.

The drawing figures show the following:

in Fig. 1 shows a two-seat multifunctional super-maneuverable aircraft (top view);

in Fig. 2 - two-seat multifunctional super-maneuverable aircraft with ventral ridges - side view;

in Fig. 3 - two-seat multifunctional aircraft with ventral ridges (front view);

in Fig. 4 - two-seat multifunctional super-maneuverable aircraft without ventral ridges (side view);

in Fig. 5 - two-seat multifunctional aircraft without ventral ridges (front view);

in Fig. 6 - typical contour of the cockpit canopy;

In the presented figures, the following elements are designated by positions:

1 - fuselage;

2 - fuselage influx;

3 - wing consoles;

4 - consoles of all-moving horizontal tail (CPGO);

5 - consoles of all-moving vertical tail (CPVO);

6 - flaperons;

7 - ailerons;

8 - rotating wing tips;

9 - rotating parts of the fuselage influx;

10 - cockpit canopy;

11 - ventral ridges.

A two-seat multifunctional aircraft with an integral aerodynamic layout is a monoplane made according to a normal balancing scheme, and containing a fuselage 1 with an influx 2, a wing, consoles 3 of which are smoothly coupled with the fuselage 1, an all-moving vertical tail (hereinafter referred to as the TPV) 4, an all-movable horizontal tail (hereinafter - TsPGO) 5, a twin-engine power plant, the engines of which are located in engine nacelles. In the head part of the fuselage there is a two-seat crew cabin of the 10th tandem type with a folding part of the canopy. The engine nacelles are spaced apart from each other horizontally, and the engine axes are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. The engines are designed with all-angle differential controlled thrust vectoring. The selected layout is a compromise, simultaneously ensuring the implementation of a high level of aerodynamic and weight perfection, as well as compliance with modern requirements for flight performance and the level of radar signature of the aircraft.

The influx 2 of the fuselage 1 is located above the engine air intakes and includes controlled rotating parts 9. The rotating parts 9 of the influx 2 are the leading edges of the middle flattened part of the fuselage 1.

The wing consoles 3, smoothly coupled with the fuselage 1, are equipped with mechanization of the leading and trailing edges, including rotary noses 8, ailerons 7 and flaperons 6.

TsPGO 5 is installed on the side tail booms of the fuselage 1. TsPVO 4 is installed on pylons mounted on the side tail booms of the fuselage 1.

TsPGO 5 provides the ability to control the aircraft in the longitudinal channel with in-phase deflection and in the transverse channel with differential deflection at trans- and supersonic flight speeds.

The aircraft is equipped with a two-fin all-moving vertical tail of a small area, used for directional control and air braking functions throughout the entire range of flight speeds.

This design of the tail of a two-seat multifunctional aircraft, along with the use of an integral load-bearing fuselage and engines with deflectable thrust vectoring, helps ensure super-maneuverability, expanding the range of altitudes and flight speeds.

As an additional means of increasing stability, ridges 11, fixed under the fuselage, can be installed on the tail booms of the fuselage, the plane of the chords of which forms an angle with the vertical plane of the aircraft.

The wing consoles 3 are made of a trapezoidal shape in plan with a sweep angle of 49° along the leading edge, large narrowing, with small values of the relative thickness of the wing, ranging from 3% to 5%, which ensures a high level of aerodynamic quality in subsonic modes, and also reduces the values increase in the force of drag occurring at trans- and supersonic flight speeds.

Composite materials are widely used in the aircraft design, which ensures high weight efficiency under given operating conditions and aircraft service life requirements.

To increase the level of stealth in the aircraft, radio-absorbing materials and coatings are also widely used.

The two-seat multifunctional aircraft with an integral aerodynamic configuration uses the architecture of control levels for the on-board equipment complex (OEC), aircraft weapons (AW) and aircraft based on an information and control system (ICS), implemented for two crew members. In this case, the OBE is built around a single “core” - an information and control system with an integrated computing system and information and executive sensors with multiple redundancy of on-board computers and data buses that perform the functions of monitoring and controlling all systems and weapons of the aircraft.

Due to the larger cross-sectional area of the cockpit, an information and control field with multifunctional indicators of increased area is organized in the area of the instrument panel of the two-seat multifunctional aircraft. To implement a full range of tasks, the information and control field of the cockpit of a multifunctional two-seater aircraft provides the output of various tactical and flight information for all types of frames to indicators in the front and rear cockpits, as well as separate control of the aircraft’s onboard equipment complex between the flight decks.

The rear cockpit information and control field is optimized for the functions of the weapons operator and air command post when performing combat missions by displaying the information required by the crew. To perform this function, the following elements are installed in the rear cabin:

- multifunctional panoramic indicator that performs the following functionality: display of a pilot frame, display of video images from cameras, use of the indicator as a failure simulation console;

- panoramic aviation indicator with a large working field for operator convenience. A large working field also allows you to more flexibly control the size of output frames depending on the task, up to displaying a single frame on the screen. From this indicator, the main control of the aircraft’s on-board equipment complex is carried out;

- lamp buttons for transferring control priority from one cabin to another.

The use of an information and control system on an aircraft with the principles of functional and hardware integration for two crew members allows obtaining the following advantages:

- ensure the multifunctionality of the aircraft in terms of the coordinated simultaneous performance of various combat missions by two crew members;

- minimize the mass and dimensions of OBE elements;

- minimize energy consumption of the equipment;

- increase the reliability of the equipment;

- minimize the contribution of mass to the organization of the information and control field of the second crew member.

The aircraft's communications system provides the ability to communicate between subscribers using a wide range of communication types, operating in both open and encrypted modes. The communications complex of the multifunctional two-seater aircraft operates in the following ranges and modes:

- centimeter wavelengths - for transmitting photo and video images;

- short-wave wavelength range - for transmitting speech (voice) information over long distances;

- ultra-short wave range of wavelengths - for transmitting speech (voice) and telecode information in the "board-to-board" mode;

- using a group action terminal - for group transmission of voice and telecode information between subscribers of a group of aircraft;

- using satellite space communications - for transmitting voice and telecode information via satellites.

The presence of these operating modes of the communications complex allows the multifunctional two-seater aircraft to command a group of different types of aircraft (both manned and unmanned) to ensure flexibility in combat use when solving the tasks of an air command post in any weather conditions and when the enemy is jamming.

Claims (4)

1. Multifunctional two-seat stealth aircraft with an integral aerodynamic layout, containing a complex of on-board equipment, a fuselage with an overflow, wing consoles with mechanization of the leading and trailing edges, including flaperons, ailerons and rotating wing tips, consoles of an all-moving horizontal and two-fin vertical tail mounted on the side tail booms fuselage, a two-seat crew cabin with a canopy, a garrot and a radome of the locator antenna located in the forward part of the fuselage, a power plant with two engines spaced horizontally and equipped with air intakes, located in engine nacelles, the axes of which are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight, characterized in that the wing consoles are smoothly coupled with the fuselage, the fuselage influx is located above the engine air intakes and includes controlled rotating parts, which are the leading edges of the middle flattened part of the fuselage, the aircraft engines contain a jet nozzle with a deflectable thrust vector and thrust reverser, an all-moving vertical tail is installed under acute angle to the vertical plane of the aircraft, the wing consoles are made of a trapezoidal shape in plan with a large sweep along the leading edge with a sweep angle of 49° along the leading edge and with small values of the relative wing thicknesses, ranging from 3% to 5%, while the cabin area crew, gargrot and radome of the locator antenna is formed by orienting the tangents to the contour of the cross sections of the fuselage at an angle to the plane of symmetry of the aircraft, and the shape of the surface of the cockpit canopy is formed by straight lines with angles of inclination of the side of the tangents to the vertical plane of the aircraft in the range of 20° - 30°, in the middle part of the fuselage between the engine nacelles there are payloads designed to be placed and used in flight, as well as additional fuel tanks connected to the aircraft fuel system, cargo compartments, on the upper surface of which there are attachment points for ejection devices for aircraft weapons, while the onboard equipment complex is made with the ability to provide, through the aircraft information and control system, information interaction between different types of aircraft of the group, including in terms of receiving and transmitting data via high-speed communication channels and group communication, including satellite communication channels, as well as analyzing information coming from its own systems and external sources with the subsequent issuance of recommendations to the crew and/or commands to a group of aircraft, and the cockpit is equipped with controls for transferring control priority from one pilot to another and at least two multifunctional panoramic indicators for controlling the aircraft and weapons. 2. Multifunctional aircraft according to claim 1, characterized in that the lower rear part of the fuselage is equipped with ventral ridges, the plane of the chords of which forms an angle with the vertical plane of the aircraft. 3. Multifunctional aircraft according to claim 1, characterized in that the all-moving vertical tail is mounted on pylons mounted on the side tail booms of the fuselage. 4. Multifunctional aircraft according to claim 1, characterized in that the all-moving vertical tail is made with the possibility of in-phase and differential deflection.

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