CN215285313U

CN215285313U - Air-jet system of BWB carrier based on C-shaped foldable outer wings

Info

Publication number: CN215285313U
Application number: CN202120751741.9U
Authority: CN
Inventors: 雷国东; 李岩; 徐悦
Original assignee: Chinese Aeronautical Est
Current assignee: Chinese Aeronautical Est
Priority date: 2021-04-13
Filing date: 2021-04-13
Publication date: 2021-12-24
Anticipated expiration: 2031-04-13

Abstract

The utility model belongs to the technical field of aircrafts, in particular to an air-based launching system based on a BWB (wing body fusion) carrier with an outer wing capable of being folded in a C shape; comprises an aerial carrier and an aerospace vehicle; the utility model adopts a large transonic velocity BWB layout airplane to carry an aerospace craft aerial launching system and mode with symmetrically distributed outer storage boxes; two back-loading cold emission methods are adopted: a weightlessness or negative overload method, a jump rolling inverted flight delivery method; adopting a BWB layout carrier with an outer wing capable of being folded in a C shape; the problem of reduce the heavy repeatedly usable sky aircraft cost of transmission by a wide margin, the problem that the weight of going into the orbit accounts for the gross weight proportion of taking off by a wide margin is solved, make world shuttle aircraft, air-breathing type propulsion hypersonic aerocraft, or boosting gliding type hypersonic aerocraft use, and the carrier is the overall arrangement design that the lift-drag ratio is high, and the load is very strong with the climbing ability, can realize remedying the problem that empty base transmitting system initial velocity and height are not enough with the load.

Description

Air-jet system of BWB carrier based on C-shaped foldable outer wings

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to empty base transmitting system based on outer wing can C shape folding BWB year machine.

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 arrangement of the flat and straight wings of the double-fuselage is difficult to fly in a transonic speed stage, so that high altitude pressure is small and the load capacity is influenced; although the wing body fusion layout has high manufacturing difficulty and the flight control system has high design and manufacturing difficulty, the loading and climbing capacity is very strong, and the comprehensive performance of aerodynamics and structure is very superior.

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 3% of magnitude; the ' white knight II ' and ' stratosphere launcher ' system has a flat wing and wing bridge mounting mode, is weak in structural design, and is difficult to mount large-size and heavy-weight aerospace vehicles, because the height width is limited by the height width of the wing bridge, and the speed is too low, so that the speed is too low, and the weight of the aerospace vehicles is affected, for example, although the wing span of the ' stratosphere launcher ' reaches 120 meters, the speed is low due to the use of the flat wing, the maximum total takeoff weight is only 580 tons, unlike the Sufei ' an-225 aircraft, the maximum total takeoff weight is 640 tons, but the wing span is only 88 meters, and the cruising flight speed is higher. The back-loading type can load the launchers with larger size and larger weight relative to the mounting type, and the structural strength of the back of the carrier with the wing body integrated layout is far better than that of a central wing bridge structure.

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 operation of the troposphere, the ratio is known to exceed the final orbital weight of the land-based multi-stage rocket which is finally sent into the space by a plurality of times, and the final orbital weight is only 3% 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 the heavy repeatedly usable sky aircraft cost of transmission 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 the use of boosting gliding type hypersonic speed aircraft, and the carrier is the BWB overall arrangement design of high lift-drag ratio, and load and climbing ability are very strong, very are fit for the application of space-based transmission.

The technical scheme of the utility model: the space-based launching system based on the BWB carrier with C-shaped foldable outer wings is characterized by comprising a carrier and a space vehicle; the aerospace craft is carried on the back of a BWB carrier with an outer wing capable of being folded in a C shape; 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 carried on the back of the carrier.

The carrier is a 300-ton and 1000-ton heavy conveyor, and the lift-drag ratio is not less than 21.

The carrier adopts a V-shaped vertical tail design, and the outer side of the main wing adopts a C-shaped folding mechanism design.

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 transonic outer wing C-shaped foldable BWB carrier back-loading aerospacecraft aerial launching system and mode with symmetrically distributed outer storage boxes; two back-loading cold emission methods are adopted: a weightlessness or negative overload method, a jump rolling inverted flight delivery method; the large airplane with the transonic outer wing capable of being folded in a C-shaped BWB carrier aerodynamic layout is adopted for carrying out horizontal takeoff, the large airplane climbs into the bottom of a stratosphere, the large airplane is launched in the air after reaching the designated flight speed, and the orbiter finishes the task and then lands in a horizontal gliding mode; 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 sea 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 weight of an aerospace vehicle finally entering a near-earth orbit of the earth accounts for 7-12% of the gross takeoff weight, the weight of a common land-based multi-stage rocket sent into the near-earth orbit accounts for 2-4% of the gross takeoff weight, meanwhile, a considerable part of lift can be manufactured by a carrier body, and the loading and climbing capabilities are strong.

Compared with an air-based launching system for mounting a central wing bridge of a large double-fuselage layout airplane, the large transonic-speed outer wing C-foldable BWB carrier is adopted to carry out air launching of the air spacecraft, the carrier has high allowable speed, large pressure and large wing area, this is beneficial to increase the load capacity, the BWB layout central fuselage can bear large weight due to larger absolute thickness, the vibration deformation is far better than that of a single thin double-fuselage central wing bridge, and the acceptable space size of the back loading mode is large, therefore, the pointed cone layout aerospace craft carrying two propellant outer storage tanks can be carried on the back, sufficient propellant carrying is ensured, because the first cosmic velocity is about Mach 26, while a typical transonic airliner is about Mach 0.8, an active supersonic aircraft is about Mach 2-3, under the current propellant energy density magnitude, the final on-track weight is in positive correlation with the amount of the carried propellant.

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 space-based launching system based on the BWB carrier with C-foldable outer wings comprises a carrier and a space vehicle; the carrier is a 300-ton and 1000-ton heavy conveyor, the lift-drag ratio is more than or equal to 21, a V-shaped vertical tail design is adopted, and the outer side of the main wing is designed by a C-shaped folding mechanism, so that the adaptability of the airport can be enhanced, for example, the carrier can be lifted, descended and parked at 4E-level and 4F-level airports; the aerospace vehicle is carried on the back of a BWB layout carrier; 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 carried on the back 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 launching method of the space-based launching system based on the BWB carrier with C-shaped foldable outer wings comprises the following steps:

(1) the air vehicle carrying the carrier horizontally takes off, climbs to the bottom of the stratosphere and accelerates, and the flying speed reaches Mach 0.6-0.8;

(2) the airborne vehicle carries the airborne vehicle to fly obliquely downwards to enter a weightlessness or overload state, the connection between the airborne vehicle and the airborne vehicle is disconnected, and the airborne vehicle flies out backwards and upwards relative to the airborne vehicle and is separated from the airborne vehicle to a safe distance due to the weightlessness effect or the overload effect (at the moment, the gravity of the airborne vehicle disappears or is reversed under an airborne reference system, and the assistance of a control surface and an attitude adjustment engine is used) under the lifting force, the weightlessness effect or a non-inertial system of the airborne vehicle;

(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.

If the energy is used for slow release, for example, the sanger jump type orbit is used for repeatedly beating water at the edge of the atmosphere for drifting in a drifting mode, or the Qiansheng balance type glide orbit is adopted for gliding and advancing at a very small inclination angle, reentry energy can be obviously and slowly released, gliding flight is extremely long, for example, the magnitude can reach two times of crossing the Pacific ocean (the interstate ballistic missile does not cross the Pacific ocean once), the American space shuttle can shoot on the atmosphere at an attack angle of 40 degrees and roll two side wings in turn, the rolling amplitude reaches 80 degrees for decelerating as soon as possible, the damage of aerodynamic heat to the wings is cooled in turn, the unpowered glide distance still exceeds 8000 kilometers, and the high-supersonic speed boosting glide vehicle has high 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 double-fuselage layout aircraft uses straight wings, the allowed flight speed is low and is about Mach 0.6, the speed is too low, the pressure is low, the load potential is low, and the weight of the in-orbit and the weight of the propellant are in positive correlation; in addition, the mounting mode of the double-fuselage central wing bridge has insufficient structural strength potential and large vibration deformation, which is a potential danger; the large BWB layout fuselage has strong structural strength due to large absolute thickness of the central fuselage, the allowed flight speed is about Mach 0.8, the speed and the pressure are large, the wing area is also large, and the loading potential is favorably 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 front vehicle recognization such as a Morger' plan, a spiral plan and the like) and extremely high risk of air launching, 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 transonic aircraft, the transonic aircraft has great weight, the aerospace vehicle carries more propellants, the rocket thrust allowed to be used is larger, the speed difference of the Mach can be tracked up in seconds under the acceleration of the large-thrust rocket, and the large supersonic aircraft and even the hypersonic aircraft cannot be developed.

Claims

1. The space-based launching system based on the BWB carrier with C-shaped foldable outer wings is characterized by comprising a carrier and a space vehicle; the aerospace vehicle is carried on the back of a BWB layout carrier; 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 carried on the back of the carrier.

2. The space-based launching system of a BWB carrier with C-foldable outer wings as claimed in claim 1, wherein said carrier is a 300-ton 1000-ton heavy-duty transport vehicle with lift-drag ratio ≥ 21.

3. The space-based launching system of an outer-wing C-foldable BWB carrier of claim 1, wherein said carrier is of V-tailed design and the outer side of the main wing is of C-foldable design.

4. The space-based launching system of a BWB carrier with C-foldable outer wings according to claim 1, wherein said outer storage box has a conical shape at the head and a cylindrical shape at the rear; the outer storage tank is hidden in the head Mach cone of the orbiter.

5. The space-based launching system of an outer-wing C-foldable BWB vehicle according to claim 1 wherein said orbiter head is conical and the rear is cylindrical with a low aspect ratio wing and V-shaped vertical tail of length less than the length of the vehicle fuselage.

6. The space-based launch system for an outer-wing C-foldable BWB vehicle according to claim 1, wherein said two outer tanks are also booster rockets.

7. The space-based launching system of a BWB vehicle based on C-folding outer wings of claim 1, wherein the orbiter profile is of organic wing design.