RU2715816C1 - Accelerating carrier aircraft (versions) - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: in the first version, a manned or unmanned accelerating carrier aircraft includes a central integrated body shape airframe, a chassis, a combined power plant from jet engines, an integrated control system with elements of a reactive control system, bearing consoles of wings with elements of mechanization, systems of active and passive thermal protection of external structural elements. Proposed power plant consists of bypass turbofan engine or afterburning turbojet engine to accelerate aircraft carrier and rocket engines with liquid fuel or solid fuel. Nozzles of mid-flight engines are located on end of tail part of fuselage of carrier aircraft. Orbital carrier rocket is arranged inside fuselage body. In the second version, carrier aircraft is equipped with accelerators with possibility of autonomous vertical or horizontal landing.

EFFECT: group of inventions is aimed at creation of reliable and energetically effective reusable aerospace system.

2 cl, 40 dwg

Description

The invention relates to aerospace systems for launching payloads into low and medium Earth orbits, and can also be used for the prompt delivery of goods or weapons to remote areas of the Earth or the World Ocean. Currently, various projects of reusable accelerating accelerators of the first stages of launch vehicles with the possibility of autonomous landing on the earth or water surface after separation from the main launch vehicle are known. Known in particular is a reusable booster accelerator (RF patent No. 2148536) comprising a housing including tanks for an oxidizer and fuel, a nose compartment with a cowl, an inter-tank and a tail compartment, a rocket propulsion system, an all-turning wing with devices for its rotation and fixation along the axis accelerator at the stage of launching and turned 90 degrees, the position at the stage of return flight, horizontal and vertical tail, three-bearing landing device, aerodynamic control and docking nodes with second stage of the launch vehicle, while the reusable accelerator is equipped with an air-jet propulsion system, including two engines with air intakes installed in the nose compartment. A booster rocket is also known (RF patent No. 2483030) including a reusable accelerator connected to the second stage, and the reusable accelerator consists of a rocket unit with liquid rocket engines connected to an aircraft kit made in the form of a glider with variable sweep wings, with aerodynamic control elements, a stabilizer , chassis, jet engines with their fuel tank and bow compartment. The pilot's cabin is located in the bow compartment of the missile unit. Aircraft engines are mounted on the upper surfaces of the wings and are equipped with controlled protective shields. Also known is a reusable returnable missile block (RF patent No. 2495799) containing a fuselage, a wing with two consoles, left and right blocks of control engines, while the wing consoles are provided with wingtips, while on the tips of the wing consoles there are nacelles of control engines with the possibility of use on the launch site and return flight site. The axis of the nozzles of the pitch and roll control engines is parallel to the normal axis OY of the returning rocket unit. The axis of the nozzles of the yaw engines is perpendicular to the normal axis OY and form an angle from 0 degrees to 20 degrees with the longitudinal axis OX. The use of reusable boosters should be recognized as rational both for the vertical launch of the launch vehicle and for the horizontal launch of the booster aircraft.

Known design study S.A. Chaplygina (“The Theory of the Lattice Wing”, Selected Works on the Theory of Wing., Leningrad, State Publishing House of Technical and Theoretical Literature, 1949) in which it was proved that the lifting force of a wing of a multidimensional wing significantly exceeds the lifting force of a similar individual wing . A study of the multi-sectional wing S.A. Chaplygina (“Experimental Aerodynamics”, Martynov AK, State Publishing House of the Defense Industry., 1949, see Fig. 8.56, p. 312), which presents data on a significant increase in the lifting force of a multi-sectional wing. The disadvantage of the above wing designs is the high aerodynamic drag in horizontal cruising flight mode. There is also known a technical solution for an aircraft wing with variable aerodynamic characteristics (RF patent No. 2694478), including the main wing profile and additional extendable wing profile elements, with additional extendable wing profile elements made in the form of one or more wing wings extended above the upper surface of the main wing profile , either in the form of one or several wing flaps extended under the lower surface of the main wing profile, or simultaneously in the form of one or several wing liners extended above the upper surface of the main wing profile and one or several wing liners extended below the lower surface of the main wing profile, while in the horizontal cruising flight mode, the main wing profile and additional profile elements form a single streamlined wing profile, while under different flight modes the aircraft associated with take-off, acceleration, climb, descent, maneuvering and landing to change the aerodynamic characteristics of the aircraft the aircraft, the extendable wing slides extend above and beyond the main wing profile, while in the extended position the distance Δ Hn between the wing wing profile and the wing liner, or between the extended wing wings, is at least 0.5Ci (where Ci is the maximum thickness of the main wing in the vertical plane air flow), the extendable wing flaps extend under the main wing profile back and down, while in the extended position the distance Δ Hn between the main wing profile and the wing wheel, or between the extended the wing flaps are not less than 0.5Ci, while with the wing flaps extended, the overlap Δ Ln between the toe of the main wing and the tail part of the wing wing is at least Ci, while with the extended position of the wing flaps the overlap Δ Ln between the wing liner and the tail of the main wing, is not less than Ci, while the overlap Δ Ln between the nose of the second wing liner and the tail of the first wing liner is not less than Ci, while the extended wing profile elements, in the extended position, to change GLA attacks have the ability to rotate about the longitudinal axis. This technical solution is advisable to use to increase the starting lift of the wing of the carrier aircraft.

Over the past 50-55 years, a large number of two-stage aerospace transport systems have been developed in the world cosmonautics, one of the conceptual is the Soviet project “Spiral”. (Central Research Institute-30, Air Force, the beginning of the project in 1964, the chief designer G.E. Lozino-Lozinsky. (See the book. Cosmic wings, M., 2009, pp. 201-218)). This decision was made as a prototype. The project proposed the use of a hypersonic GSR accelerator aircraft (“50-50”), which has a power plant of four turbofan engines or turbofan engines using liquid hydrogen, a triangular wing of variable sweep along the leading edge of the double delta type, vertical stabilizing planes in the form of keels at the ends of the wing . After acceleration to 6M at an altitude of 28-30 km, the separation of the stages was planned, then the orbital OS aircraft was launched into orbit with the help of a launch vehicle, and the GSR was returned to the airfield. It should be recognized as rational to use the winged vehicle as the simplest, mobile and most reliable and practiced method of flying in the atmosphere, in addition, the use of the WFD in dense layers of the atmosphere gives significant fuel savings. The disadvantages of the aforementioned aerospace system and the known similar reusable two-stage aerospace systems include, from an energy point of view, the insufficient height of the separation of the stage of the orbital launch vehicle. It should be recognized as expedient to increase the height at which it is necessary to separate the stage of the booster aircraft from the orbital launch vehicle to 70-80 km. The main objective of this invention is to provide a mobile, technically reliable and energy-efficient reusable aerospace system. This goal is achieved (Option N1) by performing a manned or unmanned booster aircraft with horizontal take-off, horizontal landing, including a central streamlined integrated fuselage module, a landing gear, a combined propulsion system from jet engines, an integrated control system with elements of a reactive control system, bearing wing consoles with mechanization elements, active and passive thermal protection systems of external structural elements, while the power plant and it consists of: to ensure take-off, landing and flight of the carrier aircraft in dense atmospheric layers — from two or more turbojet engines of the turbofan engine or turbofan engine, to ensure acceleration of the carrier aircraft and to ensure the flight path of the carrier aircraft to the upper atmosphere — from marching accelerating liquid propellant rocket engines (liquid propellant rocket engines) or solid propellants (turbojet engines), while the nozzles of mid-flight booster rocket engines are located at the end of the tail of the central fuselage module of the carrier aircraft, when ohm turbojet engines turbofan engines or turbofan engines are located on the perimeter of the cross section of the rear of the hull-fuselage, while the marching boosters of jet rocket engines, the inlets of the air intakes for turbofan engines or turbofan engines are closed by retractable cowls, while the orbital launch vehicle is partially or completely inside the body - the fuselage of the carrier aircraft, while for landing the orbital launch vehicle there is a hatch-valve in the bow of the fuselage of the carrier aircraft, or the lower side of the body-fuselage of the carrier aircraft. (Option 2) A manned or unmanned booster aircraft with horizontal take-off and horizontal landing, includes a central streamlined integrated fuselage module, a landing gear, a combined propulsion system from jet engines, an integrated control system with elements of a reactive control system, bearing wing consoles with mechanization elements , systems of active and passive thermal protection of external structural elements, while the power plant consists of: to ensure takeoff, landing and flight carrier aircraft in dense atmospheric layers — from two or more turbojet engines, turbofan engines, or turbofan engines, to ensure acceleration of the carrier aircraft and to ensure the flight path of the carrier aircraft to the upper atmosphere — from marching liquid-propellant rocket engines (LRE) or solid fuel (turbojet engine), while the nozzles of marching booster rocket engines are located at the end of the tail of the central fuselage module of the carrier aircraft, while turbojet engines turbojet or turbojet engine laid on the perimeter of the cross section of the rear of the hull-fuselage, while during the operation of the marching accelerating rocket engines, the air inlets for the engines of the turbofan engines or turbofan engines are closed by retractable cowls, in order to increase traction during horizontal take-off, as well as starting acceleration of the carrier aircraft along the side to the sides or on the upper side of the central fuselage body, on console pylons detachable manned or unmanned accelerating acceleration modules are provided accelerators with possibly an autonomous vertical or horizontal landing, while the orbital launch vehicle is partially or completely located inside the carrier fuselage body, while for landing the orbital carrier rocket, a hatch valve is provided in the bow of the carrier body fuselage, or from the bottom sides of the body-fuselage of the carrier aircraft.

The illustrative examples of the present invention show the variants of the booster aircraft:

in FIG. 1 is a front view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 with placement of a hatch-valve for landing an orbital launch vehicle in the bow of the fuselage body of the carrier aircraft;

in FIG. 2 is a view from the tail of the layout of a manned or unmanned carrier aircraft according to embodiment N1;

in FIG. 3 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the hull-fuselage of the carrier aircraft in take-off mode, with air-propelled engines running;

in FIG. 4 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the carrier-fuselage of the carrier aircraft in acceleration and climb mode, with air-propelled engines running;

in FIG. 5 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the hull-fuselage of the carrier aircraft in the horizontal flight mode in dense layers of the atmosphere to be brought to the area of the calculated launch, when the aircraft have jet engines;

in FIG. 6 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the fuselage body of the carrier aircraft in the mode of acceleration of the carrier aircraft with rocket engines running at the stage of launching the orbital launch vehicle in the upper atmosphere, while the inlet openings of the air intakes for jet engines closed by retractable fairings;

in FIG. 7 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the carrier-fuselage body in the separation mode of the orbital launch vehicle with the hatch-valve open in the nose of the carrier-vehicle fuselage;

in FIG. 8 is a side view of the layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 in an independent flight mode of an orbital launch vehicle and a maneuver of a carrier aircraft to escape the flight path to return to the landing aerodrome, while the flap planes of the hatch-valve in the bow of the hull -fuselage folded into a streamlined surface;

in FIG. 9 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 in landing mode;

in FIG. 10 is a front view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 with the placement of a hatch-valve for landing an orbital launch vehicle in the bow of the fuselage of the carrier aircraft, while to increase traction during horizontal take-off, as well as launch acceleration carrier aircraft on the sides of the central fuselage body, on console pylons detachable manned or unmanned accelerating accelerators modules with the possibility of autonomous vertical precipitation;

in FIG. 11 is a view from the tail of the layout of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 10;

in FIG. 12 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 10 and 11 with the placement of the hatch-valve for landing of the orbital launch vehicle in the nose of the hull-fuselage of the launch aircraft in take-off mode, with the air-propelled engines of the launch aircraft operating, as well as with the main engines of the accelerating modules of the side accelerators;

in FIG. 13 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 10 and 11 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the carrier-fuselage body of the carrier aircraft in acceleration and climb mode, with air-propelled engines operating, as well as with main propulsion engines for accelerating modules of side accelerators;

in FIG. 14 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N2 and FIG. 1 and 2 with the placement of the hatch-valve for landing of the orbital launch vehicle in the bow of the carrier-fuselage of the carrier aircraft in the horizontal flight mode in dense layers of the atmosphere to be brought to the area of the calculated launch, with working jet engines, as well as with marching engines engines of accelerating modules of side accelerators;

in FIG. 15 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 10 and 11 in the separation mode of the side overclocking modules of accelerators;

in FIG. 16 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 1 and 2 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the fuselage body of the carrier aircraft in the mode of acceleration of the carrier aircraft with rocket engines running at the stage of launching the orbital launch vehicle in the upper atmosphere, while the air inlets for jet engines closed by retractable fairings;

in FIG. 17 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 10 and 11 with the placement of the hatch-valve for landing the orbital launch vehicle in the bow of the fuselage of the carrier aircraft in the separation mode of the orbital launch vehicle with the hatch open in the bow of the shell of the fuselage of the carrier aircraft;

in FIG. 18 is a side view of the layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 in an independent flight mode of an orbital launch vehicle and a maneuver of a carrier aircraft to escape the flight path to return to the landing aerodrome, while the flap planes of the hatch-valve in the bow of the hull -fuselage folded into a streamlined surface;

in FIG. 19 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 in landing mode;

in FIG. 20 is a front view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 with a hatch-valve for landing an orbital carrier rocket in the lower part of the carrier fuselage body, while the orbital carrier rocket is located completely inside the aircraft fuselage body- carrier

in FIG. 21 is a view from the tail of the layout of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20;

in FIG. 22 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20 and 21 with the placement of the hatch-valve for landing the orbital launch vehicle in the lower part of the fuselage of the carrier aircraft, while the orbital launch vehicle is located completely inside the fuselage of the carrier aircraft, in take-off mode, when the aircraft are running ;

in FIG. 23 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20 and 21 in the mode of acceleration and climb, with working jet engines;

in FIG. 24 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20 and 21 in the regime of horizontal flight in dense layers of the atmosphere for removal to the area of the calculated launch, with the working jet engines,

in FIG. 25 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20 and 21 in the acceleration mode of the carrier aircraft with rocket engines running at the stage of launching the orbital carrier rocket in the upper atmosphere, while the inlet openings of the air intakes for jet engines are closed by retractable cowls;

in FIG. 26 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 20 and 21 in the separation mode of the orbital launch vehicle with the flap open at the bottom of the fuselage body of the launch vehicle;

in FIG. 27 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N1 and FIG. 20 and 21 in the independent flight mode of the orbital booster rocket and maneuver of the booster plane to escape the flight path upon returning to the landing aerodrome;

in FIG. 28 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N1 and FIG. 20 and 21 in landing mode;

in FIG. 29 is a front view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 with a hatch-valve for landing an orbital carrier rocket in the lower part of the carrier-aircraft fuselage body, while to increase traction during horizontal take-off, as well as launch acceleration carrier aircraft from the upper side of the central body of the fuselage, on a vertical pylon, a detachable manned or unmanned accelerating accelerator module with the possibility of autonomous horizontal cages;

in FIG. 30 is a view from the rear of the layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 with a hatch-valve for landing an orbital carrier rocket in the lower part of the carrier-aircraft fuselage body, while increasing thrust during horizontal take-off, and launch acceleration of the carrier aircraft from the upper side of the central fuselage body; on a vertical pylon, a detachable manned or unmanned accelerating accelerator module with an autonomous horizon is provided cial landing;

in FIG. 31 is a front view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29 after separation of a manned or unmanned overclocking module with the possibility of autonomous horizontal landing;

in FIG. 32 is a view from the tail of the layout of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 30 after separation of a manned or unmanned overclocking module with the possibility of autonomous horizontal landing:

in FIG. 33 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 with the placement of the hatch-valve for landing the orbital launch vehicle in the lower part of the carrier-fuselage body of the launch aircraft in take-off mode, with the air-propelled engines of the launch aircraft operating, as well as with the main engines of the accelerator accelerator module;

in FIG. 34 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 in the mode of acceleration and climb, when the aircraft engines are running, as well as when the main engines are accelerating the accelerator module of the accelerator;

in FIG. 35 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 in the regime of horizontal flight in dense layers of the atmosphere for removal to the area of the calculated launch, when the aircraft engine is running jet engines, as well as when the main engines are accelerating the accelerator module of the accelerator;

in FIG. 36 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29 and 32 in the mode of separation of the acceleration module of the accelerator;

in FIG. 37 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 in the acceleration mode of the carrier aircraft with rocket engines running at the stage of launching the orbital carrier rocket in the upper atmosphere, while the inlet openings of the air intakes for jet engines are closed by retractable cowls;

in FIG. 38 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 in the separation mode of the orbital launch vehicle with the hatch-valve open at the bottom of the fuselage body of the launch vehicle;

in FIG. 39 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to Embodiment N2 and FIG. 29-32 in the independent flight mode of the orbital booster rocket and maneuver of the booster plane to escape the flight path upon returning to the landing aerodrome;

in FIG. 40 is a side view of a layout diagram of a manned or unmanned carrier aircraft according to embodiment N2 and FIG. 29-32 in landing mode. In the drawings, the positions indicated:

pos. 1 - the central module of the fuselage of the carrier aircraft streamlined integrated form;

pos. 2 - orbital launch vehicle with a cone-shaped body;

pos. 3 - supporting console of the composite wing with elements of mechanization;

pos. 4 - nozzle of a turbofan engine or turbofan engine carrier;

pos. 5 - air intake for the turbofan engine or turbofan engine;

pos. 6 - nozzle marching booster rocket engine for liquid fuel (LRE) or solid fuel (TRD);

pos. 7 - nozzle of the rocket engine of the orbital launch vehicle;

pos. 8 - chassis;

pos. 9 - control cabin;

pos. 10 - a niche for the mechanism of the retractable chassis;

pos. 11 - extendable fairing of the inlet channel of the air intake;

pos. 12 - vertical console tail;

pos. 13 - wing horizontal tail;

pos. 14 - hatch-valve in the bow of the body-fuselage of the carrier aircraft for opening-closing the opening for landing the launch vehicle of the second stage;

pos. 15 - hatch-valve in the lower part of the body-fuselage of the carrier aircraft for opening-closing the opening for landing the launch vehicle of the second stage;

pos. 16 - detachable manned or unmanned accelerator accelerator module with the possibility of autonomous vertical landing;

pos. 17 - detachable manned or unmanned accelerating winged accelerator module with the possibility of autonomous horizontal landing.

Claims (2)

1. A manned or unmanned booster aircraft with horizontal take-off, horizontal landing, including a central streamlined integrated fuselage module, landing gear, a combined propulsion system from jet engines, an integrated control system with elements of a reactive control system, bearing wing consoles with mechanization elements, systems active and passive thermal protection of external structural elements, characterized in that the power plant consists of: to ensure takeoff, landing and flight of a carrier aircraft in dense atmospheric layers — from two or more turbojet engines of a turbofan engine or turbofan engine, to ensure acceleration of the carrier aircraft and to ensure the flight path of the carrier aircraft to the upper atmosphere — from marching liquid-propelled rocket engines (LRE) or solid fuel (turbojet engine), while the nozzles of marching booster rocket engines are located at the end of the tail of the central fuselage module of the carrier aircraft, while turbojet engines of the turbojet engine, or TR Ф are located on the perimeter of the cross section of the rear of the fuselage body, while during the operation of the marching boosted rocket engines, the air inlet openings for the turbofan engines or turbofan engines are closed by retractable cowls, while the orbital launch vehicle is partially or completely inside the carrier body fuselage, at the same time, for landing the orbital launch vehicle, a hatch-valve is provided in the bow of the carrier-fuselage of the carrier aircraft, or on the lower side of the aircraft-fuselage body the settler. 2. A manned or unmanned booster aircraft with horizontal take-off, horizontal landing, including a central streamlined integrated fuselage module, a landing gear, a combined propulsion system from jet engines, an integrated control system with elements of a reactive control system, bearing wing consoles with mechanization elements, systems active and passive thermal protection of external structural elements, characterized in that the power plant consists of: to ensure takeoff, landing and flight of a carrier aircraft in dense atmospheric layers — from two or more turbojet engines of a turbofan engine or turbofan engine, to ensure acceleration of the carrier aircraft and to ensure the flight path of the carrier aircraft to the upper atmosphere — from marching liquid-propelled rocket engines (LRE) or solid fuel (turbojet engine), while the nozzles of marching booster rocket engines are located at the end of the tail of the central fuselage module of the carrier aircraft, while turbojet engines of the turbojet engine, or TR F are located on the perimeter of the cross section of the rear of the fuselage body, while during the operation of the marching boosted rocket engines, the inlet openings for the engines of the turbofan engines or turbofan engines are closed by retractable cowls, in order to increase traction during horizontal take-off, as well as launch acceleration of the carrier aircraft on the sides or on the upper side of the central fuselage body, on console pylons detachable manned or unmanned acceleration acceleration modules with accelerators are provided the possibility of autonomous vertical or horizontal landing, while the orbital launch vehicle is partially or completely located inside the fuselage of the carrier aircraft, while for landing the orbital launch vehicle there is a hatch-valve in the bow of the fuselage of the carrier aircraft, or from the bottom sides of the body-fuselage of the carrier aircraft.

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