CN215285311U - Air-based launching system based on support wings and H-shaped empennage aircraft - Google Patents
Air-based launching system based on support wings and H-shaped empennage aircraft Download PDFInfo
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- CN215285311U CN215285311U CN202120751718.XU CN202120751718U CN215285311U CN 215285311 U CN215285311 U CN 215285311U CN 202120751718 U CN202120751718 U CN 202120751718U CN 215285311 U CN215285311 U CN 215285311U
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Abstract
The utility model belongs to the technical field of aircrafts, in particular to an air-based launching system based on a support wing and an H-shaped tail wing carrier; comprises an aerial carrier and an aerospace vehicle; the utility model adopts a large transonic support wing and an H-shaped empennage layout plane 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 weight loss and load overload method and a jump rolling inverted flight delivery method; the carrier aerodynamic layout of the transonic support wing and the H-shaped tail wing is adopted; 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 round trip aircraft, air suction type propulsion hypersonic aerocraft, or boosting gliding type hypersonic aerocraft use, and the aircraft is the conventional overall arrangement design of high lift-drag ratio, and flight control system is simple and possesses engineering realizability.
Description
Technical Field
The utility model belongs to the technical field of the aircraft, concretely relates to air base transmitting system based on prop wing and H type fin carrier.
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; the problem of the wing body fusion layout is that the manufacturing difficulty is high and the design and manufacturing difficulty of a flight control system is high; the transonic support wing layout belongs to a conventional layout, and the defects can be avoided.
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 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. Compared with a mounting type, the back-mounted type aircraft can be used for loading missiles with larger sizes and heavier weights, and the structural strength of the back of the aircraft with the supporting wing structure 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 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 entering 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 conventional overall arrangement design of high lift-drag ratio, flight control system is simple and possesses engineering realizability.
The technical scheme of the utility model: an empty foundation launching system based on a support wing and an H-shaped empennage carrier is characterized by comprising a carrier and an aerospace vehicle; the aerospace vehicle is carried on the back of the carrier with the support 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 carried on the back of the carrier.
The carrier comprises a supporting wing carrier, an H-shaped empennage carrier, a BWB carrier with an outer wing capable of being folded in a C shape, and a C-shaped folded carrier with a double-body straight wing layout.
The carrier is a 300-ton and 1000-ton heavy conveyor, and the lift-drag ratio is not less than 20.
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 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 support wing and an H-shaped empennage layout plane 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; a large airplane carrying air-borne spacecraft which is pneumatically distributed by transonic support wings and H-shaped tail wing carriers 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 and landed 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 weight of an aerospace vehicle finally entering a near-earth orbit of the earth accounts for 7-12% of the total launching weight, the weight of a common land-based multi-stage rocket sent into the near-earth orbit accounts for 2-4% of the total launching weight, meanwhile, the aircraft is in a conventional layout, the manufacturing is practical, and the flight control design is simple and reliable.
Compared with an air-based launching system for mounting a central wing bridge of a large double-fuselage layout airplane, the air-based launching system for mounting the central wing bridge of the airplane adopts a large transonic speed support wing layout carrier to carry an air spacecraft to launch in the air, the allowable speed of the carrier is high, the pressure is high, the wing area is controllable, the supporting wing layout central fuselage can bear large weight due to sufficient structural strength of the supporting design, the vibration deformation is far better than that of a single-thin double-fuselage central wing bridge, the acceptable space size of a 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 air-based launching system based on the carrier with the support wings and the H-shaped tail wings comprises the carrier and an aerospace vehicle; the carrier is a 300-ton and 1000-ton heavy conveyor, the lift-drag ratio is more than or equal to 20, an H-shaped vertical tail design is adopted, and the outer side of the main wing is designed by a folding mechanism, so that the adaptability of the airport can be enhanced, and the airport can be lifted, descended and parked at 4E and 4F levels, for example; the aerospace vehicle is carried on the back of the carrier with the support wing 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 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 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 launching method of the air-based launching system based on the support wing and the H-shaped empennage carrier 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-scale supporting wing layout fuselage has strong structural strength due to the enhancement of the supporting structure, the allowable flight speed is about Mach 0.8, the speed pressure is large, the wing area is also large, and the supporting wing layout fuselage and the supporting structure are favorable for increasing the loading potential; 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 (7)
1. An empty foundation launching system based on a support wing and an H-shaped empennage carrier is characterized by comprising a carrier and an aerospace vehicle; the aerospace vehicle is carried on the back of the carrier with the support 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 carried on the back of the carrier.
2. The air bearing fin and H-tail fin based aerial lift launch system of claim 1 wherein said lift is a 300-1000 ton heavy conveyor with a lift-drag ratio of 20 or greater.
3. The system of claim 1, wherein the vehicle is of an H-shaped vertical tail design and the outboard side of the main wing is of a folding mechanism design.
4. The buttress and H-tail based airborne aircraft air-based airborne launcher system according to claim 1, wherein said outer reservoir 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 support wing and H-tail based space launch system of claim 1 wherein the orbiter head is conical, the rear is cylindrical, with a low aspect ratio wing, V-shaped vertical tail, 1/3 to 1/2 in length of the fuselage of the vehicle.
6. The strut and H-tail based air-based launcher system according to claim 1, wherein said two outer tanks are also booster rockets.
7. The support wing and H-tail based space launch system of claim 1 wherein the orbiter profile is of organic wing design.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114313324A (en) * | 2022-01-26 | 2022-04-12 | 中国科学院力学研究所 | Horizontal interstage separation wind tunnel experiment combined structure of two-stage orbit entering aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114313324A (en) * | 2022-01-26 | 2022-04-12 | 中国科学院力学研究所 | Horizontal interstage separation wind tunnel experiment combined structure of two-stage orbit entering aircraft |
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