CN215285312U - Air-based transmitting system based on double-body flat wing layout aircraft carrier - Google Patents

Abstract

The utility model belongs to the technical field of aircrafts, in particular to a space-based launching system based on a double-fuselage flat-straight-wing aircraft with an outer wing capable of being folded in a C shape; comprises an aerial carrier and an aerospace vehicle; the utility model adopts the air space vehicle aerial launching system and mode of carrying symmetrically distributed outer storage boxes by a large-scale double-fuselage flat and straight wing carrier with C-shaped foldable outer wings; a carrier with an outer wing capable of being folded in a C shape and a double-body straight wing layout is adopted; the problem of reduce the heavy repeatedly usable sky aircraft cost of transmission by a wide margin, increase substantially the problem that the weight of going into the orbit accounts for the gross weight proportion of taking off is solved, make world shuttle aircraft, air suction formula propulsion hypersonic aerocraft, or boosting gliding type hypersonic aerocraft use, and the carrier is the conventional overall arrangement design of high lift-drag ratio, and technical maturity is high, flight control system is simple reliable, and engineering realizability is strong.

Description

Air-based transmitting system based on double-body flat wing layout aircraft carrier

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to air-based transmitting system based on two fuselage straight wing overall arrangement loaders.

Background

With the utility model discloses the closest prior art is "white knight No. two" system and "stratosphere transmitter" system, adopts double fuselage overall arrangement subsonic aircraft, with the aerospace vehicle carry under central wing bridge, bring into stratosphere bottom and put in the back and separate to safe distance, the transmission of firing in the air, aerospace vehicle utilizes self lift airfoil to assist and climbs and adjust the gesture, perhaps relies on the vector control device adjustment gesture of rocket completely, then advances to get into the earth near-ground track by rocket power. The layout of the flat and straight wings of the double airframes is simple and reliable, but the absolute values of the required wingspan and the main starting and outer wheel span are larger, and the limit requirements of a common civil airport are exceeded.

For example, the 4E airport wing span is limited to 65 meters or less, the main starting and exiting wheel span is limited to 14 meters or less, the 4F airport wing span is limited to 80 meters or less, and the main starting and exiting wheel span is limited to 16 meters or less. The double-fuselage layout carrier is to realize heavy-load efficient space-based launching, and both the wingspan and the main starting and outer wheel distance can exceed the limits of common civil airports, for example, the wingspan of a stratosphere launcher in the United states reaches 117 meters, and the wingspan of the airport is far beyond the limit of a 4F grade airport, although the wingspan of the stratosphere launcher in the United states can be claimed to be capable of starting and landing in tens of airports in the United states, the airport limit is certainly exceeded, and the normal order of civil airports is influenced. The civil aircraft exceeding the airport limit is used by an ampere-225 transporter with the wingspan of 88.4 meters, and the ampere-225 transporter can take off and land for a plurality of times in China Shijiazhuang airports (4E grade) and Tianjin airports (4E grade) in recent years, which greatly exceeds the civil aviation limit, but the busy capital airport (4F grade) cannot allow the civil aircraft to take off and land for use.

When the land-based multi-stage rocket is launched, excessive propellant needs to be consumed, most of the propellant is liquid oxygen, most of the propellant is liquid hydrogen, and the final on-orbit weight proportion is extremely low and is about 2-4%; the white knight II and stratosphere launcher system has the mounting mode of the straight wing and the central wing bridge, can be used for launching an aerospace vehicle with certain weight and size on an empty base, and is simple and reliable in mounting type throwing cold launching, high in technical maturity and feasible in engineering reality. The main problem is that the span is too far from the main hoisting and external wheels, which in heavy load situations will exceed the limits of class 4E or 4F airports.

The multi-stage rocket is vertically launched, the thrust of the first stage rocket is necessarily greater than the total takeoff weight, and most of the total takeoff weight is carried oxidant, for example, for a liquid hydrogen liquid oxygen rocket, the weight of liquid oxygen is about 6-8 times of that of liquid hydrogen, and an aircraft engine aircraft does not need to carry the oxidant; in addition, the thrust of the rocket engine is lost by about 10-15% in the running process of the troposphere, the ratio is known to exceed the weight of the land-based multi-stage rocket which is finally sent into space for orbit entering by a plurality of times, and the final orbit entering weight is only 2-4% of the maximum takeoff weight; and the convection layer concentrates 75% of the whole atmosphere mass, the flight resistance is very large, and the gas is only under-expanded for ensuring the safe jet of the tail nozzle, which causes great energy loss.

In addition, in order to fully utilize the speed increasing of the earth rotation linear velocity and the atmospheric circulation, launching sites are constructed on land near the equator and even offshore fixed or movable launching sites are constructed in various countries in the world, the air-based launching technology can solve the problem that the high-latitude countries have no earth territory in the equator, can solve the problem that the sea transportation speed of sea-based launched and transported laundries is too slow, and can also utilize the air refueling technology to solve the problem of too long routes.

Disclosure of Invention

The utility model aims at: the problem of reduce launch heavy repeatedly usable sky aircraft cost by a wide margin and considered engineering realizability, increase substantially the problem that the weight of going into the orbit accounts for the gross weight proportion of taking off is solved, make world shuttle aircraft, or air-breathing type hypersonic aircraft, boosting gliding type hypersonic aircraft use, and the carrier is the conventional overall arrangement design of high lift-drag ratio's double-fuselage straight wing, and technical maturity is high, and engineering realizability is strong.

The technical scheme of the utility model: the air-based transmitting system based on the double-fuselage flat wing layout carrier is characterized by comprising a carrier and an aerospace vehicle; the aerospace craft is mounted below a central wing bridge of a double-fuselage flat wing layout carrier, and comprises two symmetrically distributed outer storage boxes, orbiters and ferry rockets; the ferry rocket is arranged in the orbiter, the outer storage boxes are hung on two sides of the body of the orbiter, and the orbiter is hung below a wing bridge of the carrier.

The carrier is a 300-ton and 1000-ton heavy conveyor, and the lift-drag ratio is more than or equal to 25.

The aircraft adopts the design of a double-cross vertical tail, the problem that the wingspan exceeds the standard is solved by adopting the design of a C-shaped folding mechanism on the outer side of a main wing, and the problem that the aircraft with the main starting wheel and the outer wheel which exceed the standard moves on a narrow airport taxiway is solved by adopting the loading of a multi-wheel flat car with a smaller outer wheel track.

The outer storage box is conical in shape at the head part and cylindrical at the rear part, so that the resistance is reduced, and the volume is large; the propellant outer storage tank is hidden in the Mach cone of the head of the orbiter.

The head part of the orbiter is conical, the rear part of the orbiter is cylindrical, the orbiter is provided with a wing with a small aspect ratio and a V-shaped vertical tail, and the length of the orbiter is smaller than that of the body of the carrier.

The two propellant tanks may also be booster rockets.

The appearance of the orbiter adopts an organic wing design so that the orbiter can horizontally glide and land.

The utility model discloses beneficial effect: the utility model adopts a large subsonic outer wing C-shaped foldable double-body flat wing arrangement carrier to carry an aerospace vehicle aerial launching system and a mode of carrying symmetrically distributed outer storage boxes, and adopts a multi-wheel flat car with a smaller outer wheel base to realize the movement of a narrower airport taxiway and the standard parking of parking spaces; a mounting and releasing cold emission mode is adopted; the large aircraft-mounted aerospace craft adopting a carrier aerodynamic layout with a double-fuselage flat-straight wing layout and a subsonic outer wing capable of being folded in a C-shaped manner horizontally takes off, climbs into the bottom of a stratosphere, is launched in the air after reaching a specified flight speed, and is horizontally glided to land and land after a track device finishes a task; the space-based launching adopts the high-efficiency climbing of an aircraft in a troposphere to avoid a rocket power ascending stage with low efficiency and high resistance, in addition, the space-based launching can be quickly launched near an equatorial region, the earth rotation and atmospheric circulation effect are fully utilized, the cost for building a near-equatorial launching field can be saved compared with the land-based launching, the problem of too low marine speed can be avoided compared with the sea-based launching, the volume and the weight of a propellant consumed by the rocket can be greatly reduced, the proportion of the weight of an aerospace vehicle finally entering a near-earth orbit of the earth to the total takeoff weight reaches 7-12%, the proportion of the weight of a common land-based multi-stage rocket sent into the near-earth orbit to the total takeoff weight is 2-4%, meanwhile, the aircraft is in a conventional layout, the technical maturity is high, the manufacturing is feasible, and the flight control design is simple and reliable.

Compared with a common air-based launching system for mounting a central wing bridge of a large-scale double-fuselage layout aircraft, the aircraft is mounted with the air-based aircraft in the double-fuselage layout, the large-scale subsonic outer wings of the aircraft can be folded in a C shape, the outer wing sections of the aircraft can be folded to be convenient to stay and move in a common civil airport, the aircraft in the pointed cone layout, which carries two propellant outer storage tanks, can be mounted, and enough propellant carrying is ensured, because the first cosmic speed is about 26 Mach, the common transonic passenger plane is about 0.5-0.9 Mach, the existing supersonic aircraft is about 2-3 Mach, and under the current propellant energy density magnitude, the final on-orbit weight and the number of the carried propellant are in positive correlation.

Drawings

Fig. 1 is a top view of the space-based launching system of the present invention;

FIG. 2 is a perspective view of the space based launching system of the present invention;

fig. 3 is a side view of the space-based launching system of the present invention;

fig. 4 is a front view of the space-based launching system of the present invention.

1-ferry rocket, 2-outer storage tank, 3-support wing and 4-orbiter

Detailed Description

The present invention will be further explained with reference to the accompanying drawings

As shown in fig. 1-4, the air-based launching system based on the double-fuselage flat-wing layout air-borne aircraft comprises an air-borne aircraft and an aerospace vehicle; the carrier is a 300-ton and 1000-ton heavy-duty conveyor, the lift-drag ratio is more than or equal to 25, a double-cross vertical tail design is adopted, the outer side of a main wing is designed by a C-shaped folding mechanism, the carrier can realize the movement at a narrow airport taxiway and the parking at a parking place through a multi-wheel flat car with a small outer wheel track, the adaptability of the airport can be enhanced, and for example, the carrier can be lifted and parked at 4E-level and 4F-level airports; the aerospace craft is mounted below the central wing bridge of the carrier with double-body layout; the aerospace vehicle comprises two symmetrically distributed outer storage tanks (which can also be used as boosting rockets), an orbiter and a ferry rocket; the ferry rocket is arranged in the orbiter, the outer storage boxes are hung on two sides of the body of the orbiter, and the orbiter is hung below a wing bridge of the carrier.

The outer storage box is conical in shape at the head part and cylindrical at the rear part, so that the resistance is reduced, and the volume is large; the propellant outer storage tank or the boosting rocket is hidden in the head Mach cone of the orbiter.

The head part of the orbiter is conical, the rear part of the orbiter is cylindrical, the orbiter is provided with a wing with a small aspect ratio and a V-shaped vertical tail, and the length of the orbiter is smaller than that of the body of the carrier.

The transmitting method of the air-based transmitting system based on the double-fuselage flat wing layout carrier comprises the following steps:

(1) the aircraft is mounted on the air-borne spacecraft to take off horizontally, climb and accelerate to the bottom of an stratosphere, and the flying speed reaches Mach 0.5-0.7;

(2) the airborne aerospace vehicle mounted by the carrier climbs to the bottom of the stratosphere, the connection between the carrier and the aerospace vehicle is disconnected, and the aerospace vehicle falls down under the action of gravity, flies out backwards and downwards relative to the carrier and is separated from the carrier to a safe distance;

(3) the carrier automatically returns to the ground and horizontally lands without a cruise stage;

(4) the aerospace vehicle rocket engine is ignited in the air, under the propelling of the rocket engine and the adjustment of the wing and the empennage, the aircraft can quickly climb under the condition of descending height, and the wing, the empennage and the rocket vector nozzle are used for adjusting the aircraft to a launching attitude, so that the aircraft can accelerate to Mach 5-12 at an inclination angle of less than or equal to 60 degrees;

(5) after the propellant of the outer storage box is consumed, the posture is adjusted to be thrown away from the outer storage box, and the outer storage box glides, floats away and decelerates under the action of inertia and gravity, and then is recycled and reused by using the parachute to descend the ground;

(6) the orbiter continuously accelerates and adjusts the posture, accelerates to the first cosmic speed and climbs to the outside of the karman line, at the moment, the air basically disappears, the orbiter becomes an orbital vehicle, a rocket engine can be closed, and the orbital vehicle circularly moves around the earth;

(7) if the target orbit needs to be entered into a higher orbit, the current orbit is transferred into the target orbit through a transfer orbit by using an orbit transfer technology, a ferry rocket can be used for carrying out, an orbiter stays in the current orbit, or the ferry rocket is not used, the orbiter directly transfers the orbit to enter the target orbit, but more propellant is consumed;

(8) after the space operation task is completed, the orbiter returns to the atmosphere in a jumping (Sanger orbit) or balanced gliding (Qian schson orbit) orbit mode, so that a large amount of violent aerodynamic heat is avoided;

(9) the appearance of the orbiter adopts the design of organic wings to enable the orbiter to horizontally glide and land;

(10) because the speed of the orbiter entering the atmosphere again is extremely high, about 7.9 km/s, the altitude is extremely high, at least more than 100 km, the orbiter has extremely large kinetic energy and gravitational potential energy, and the energy is converted into pneumatic heat to be consumed by the airship or the space shuttle through impact friction with the atmosphere, and strict thermal protection measures are required.

(11) In the takeoff and landing stages of the aircraft, the outer wing sections are completely unfolded and locked; when the aircraft needs to move and park in an airport, the outer wing sections are folded and locked, and the multi-wheel flat car loading aircraft with a small outer wheel track is adopted to realize the movement of a narrow airport taxiway and the parking of standard parking spaces.

If the sum of potential energy caused by height and kinetic energy caused by high speed is used for slow release, for example, a Sanger jump type orbit is used for repeatedly playing water drift type gliding and drifting at the edge of the atmosphere, or a Qianshenson balance type gliding orbit is adopted for gliding and advancing at a very small inclination angle, reentry energy can be obviously and slowly released, gliding and flying are extremely long distances, for example, the magnitude can reach two times crossing the Pacific ocean, and the like (the interstate ballistic missile does not cross the Pacific ocean once), when the American space shuttle is re-started, the American space shuttle is shot on the atmosphere at an attack angle of 40 degrees and two side wings are rotated, the rolling amplitude reaches 80 degrees for decelerating as soon as possible, and the damage of aerodynamic heat to the wings is cooled, the gliding distance still exceeds 8000 km, and the high-supersonic speed boosting gliding aircraft has large sailing potential.

Description of the principles

75% of the earth's atmospheric mass is concentrated in the troposphere, the troposphere of dense atmosphere not only provides the resistance of the aircraft, but also seriously reduces the thrust of the rocket engine (the thrust loss is about 10% -15%, the general land-based multi-stage rocket orbit weight is only 2-4% of the gross weight of takeoff, for example, the aerospace vehicle can be launched at the bottom of the stratosphere above the troposphere, the use of the propellant can be greatly reduced, the weight proportion of orbit is obviously improved, in addition, the aircraft is used for horizontal takeoff, the lift climbing mode does not need to use the oxidant, which is a mode for saving gross weight of takeoff, because the aerospace engine can absorb oxygen from the atmospheric layer, and in the liquid hydrogen and liquid oxygen rocket propellant, the weight of liquid oxygen is 6-8 times of that of liquid hydrogen, the proportion can be obtained from the chemical reaction formula of oxyhydrogen combustion, and the extremely low density of liquid hydrogen requires a large amount of internal space to carry (the density of liquid hydrogen is 71 kg/cubic meter, liquid oxygen density 1140 kg/m, which in turn brings additional drag), so space-based launching can significantly reduce propellant volume and weight.

The large-scale double-fuselage flat wing layout aircraft uses flat wings, although the allowable flight speed is low and is 0.5-0.7 Mach, the wing span can be made very large and can be folded in a C shape, so the load and climbing capacity of the aircraft are enhanced; in addition, the mounting mode of the double-body central wing bridge is simple and reliable, the technical maturity is high, and the engineering can be realized strongly; due to the flat wing design, the allowable flight speed of the large-sized double-fuselage flat wing layout is 0.5-0.7 Mach, the speed and the pressure are small, but the wing area can be enlarged, so that the loading potential is increased; although the allowable flight speed of the aircraft is not as high as that of a large supersonic aircraft (such as an XB-70 bomber and the like), the supersonic aircraft has high difficulty (the 'Sanger' plan, the 'spiral plan' and other forward vehicle references), the air launching risk is extremely high, the initial speed provided by the supersonic aircraft can reach Mach 3 due to strong shock wave streaming, the difference is not too large for the large subsonic aircraft, the subsonic aircraft can be designed to have larger load, the propellant carried by the aerospace vehicle is allowed to be more, the rocket thrust used is allowed to be larger, the speed difference of a plurality of Mach can be tracked up by a plurality of seconds under the acceleration of a large-thrust rocket, and the large supersonic aircraft with high technical difficulty and low maturity and even the hypersonic aircraft can not be developed.

Claims (7)

1. The air-based transmitting system based on the double-fuselage flat wing layout carrier is characterized by comprising a carrier and an aerospace vehicle; the aerospace craft is mounted below a central wing bridge of the carrier with a double-body straight wing layout; the aerospace vehicle comprises two symmetrically distributed outer storage tanks, orbiters and ferry rockets; the ferry rocket is arranged in the orbiter, the outer storage boxes are hung on two sides of the body of the orbiter, and the orbiter is hung below a central wing bridge of the carrier.

2. The air-based launching system based on the double-fuselage flat-wing layout carrier as claimed in claim 1, wherein the carrier is a 300-ton 1000-ton heavy-duty conveyor, and the lift-drag ratio is greater than or equal to 25.

3. The space-based transmitting system based on the double-fuselage flat-wing layout carrier of claim 1, wherein the carrier adopts a double-cross vertical tail design, and the outer side of the main wing adopts a C-shaped folding mechanism design.

4. The space-based transmitting system based on the double-fuselage flat-wing layout aircraft as claimed in claim 1, wherein the outer storage box is conical in shape at the head and cylindrical at the rear; the outer storage tank is hidden in the head Mach cone of the orbiter.

5. The space-based launching system of a dual fuselage flat wing layout-based aircraft carrier of claim 1, wherein the orbiter head is conical, the rear is cylindrical, with a low aspect ratio wing, a V-shaped vertical tail, and a length less than the length of the aircraft fuselage.

6. The air-based launching system based on a double-fuselage straight wing layout aircraft as claimed in claim 1, wherein the two outer tanks can also be booster rockets.

7. The space-based transmitting system based on the double-fuselage flat-wing layout aircraft as claimed in claim 1, wherein the configuration of the orbiter is designed by organic wings.

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