CN112937900A - Aircraft launching system, launching method and aircraft - Google Patents
Aircraft launching system, launching method and aircraft Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/10—Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
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Abstract
The invention discloses an aircraft launching system, a launching method and an aircraft; the method comprises the steps that a huge traction force is applied to the side of a movable pulley of a pulley block, so that the side of the movable pulley of the pulley block obtains a faster moving speed, and the free end of a flexible cable of the pulley block obtains a larger traction force and a particularly fast moving speed by utilizing the amplification effect of the pulley block; the free end of a flexible cable of the pulley block is connected with an aircraft with a certain aerodynamic shape and the surface of which is subjected to heat-proof treatment, the aircraft obtains forward power through traction of the flexible cable and obtains lift force through the aerodynamic shape, and the aircraft flies at high altitude like a kite; after the aircraft reaches the designed speed, the unhooking slow-descent device is unhooked from the aircraft, and the aircraft reaches a preset track by using inertia or self power; after the aircraft reaches a safe distance, the unhooking slow-descending device is opened, so that the flexible cable slowly descends to the ground; meanwhile, the braking device brakes to enable the traction device to stop slowly; traction and speed can be obtained by free fall movement of the weights.
Description
Technical Field
The invention relates to the field of aircraft manufacturing and launching, in particular to the field of spacecraft manufacturing and launching.
Background
In the future, human beings are in intense enthusiasm for exploring space in various countries at present, but due to the launching cost of a launch vehicle technology and the development of a rocket technology, the exploration of space is still in an early stage.
The cost for launching the carrier rocket of No. 3B in China is about 4-5 hundred million RMB; one launch cost is about $ 3-4 billion in europe due to the small volume production of rockets; the cosmos and delta rocket in the united states costs 1.4-2 billion dollars, with a total cost of 4.3 billion dollars for one launch.
The near-earth orbit carrying capacity of a mainstream large carrier rocket in the world is about 20 tons, and the synchronous orbit carrying capacity is 8-12 tons; the carrying capacity of the long sign five rocket in China is 25 tons and below of a near-earth orbit, and the carrying capacity of a synchronous orbit is 14 tons and below; the U.S. space 5 carrier rocket with the first thrust ranking of the world carrier rocket at present has the height of 110.6 meters, the diameter of 10.1 meters, the mass of 3039 tons and the near-earth rail carrying capacity of 119 tons, but is out of service for various reasons; the Changcheng No. 9 carrier rocket which is being developed in China is expected to be successfully developed in about 2028, the thrust is about 3000 tons, the near-earth orbit carrying capacity is at least 100 tons, the earth-moon transfer orbit carrying capacity is at least 50 tons, and the carrying capacity is similar to that of the U.S. Tustar No. 5 carrier rocket;
just because the rocket is developed with great technical difficulty, high launching cost and small effective load, only the big country or the big company with great capital and advanced technology has the capacity of space launching, which influences the speed of human advancing to the star and the sea.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide an aircraft launching system, an aircraft launching method and an aircraft, so as to reduce launching cost, increase effective load and accelerate flight speed, and a new way is made to solve the technical bottleneck problem in the aircraft launching field at present.
The purpose of the invention is realized by adopting the following technical scheme:
in a first aspect the present invention provides an aircraft launching system:
this transmission system includes when draw gear is the heavy object: the device comprises a pulley block, a steering fixed pulley, a flexible cable, a runway, an aircraft, a separating device, a unhooking slow descending device, a temperature control device, a braking device, a resetting traction device, a heavy object, a buffer water tank, a base, a grounding device and a launching control system;
the following steps: the pulley block fixed pulley side, the steering fixed pulley, the separating device, the temperature control device, the braking device and the reset traction device are all connected with the base of the pulley block fixed pulley side; the pulley block, the steering fixed pulley, the separating device, the braking device and the reset traction device are all connected with the own grounding device; the side of a movable pulley of a pulley block is connected with a heavy object, the free end of a flexible cable of the pulley block is connected with an unhooking slow-descending device through a braking device after passing around a plurality of steering fixed pulleys and then is connected with an aircraft through a separation device, the aircraft is stopped on a runway, and a buffer water pool is arranged below the heavy object; the emission control system is responsible for controlling the safe and orderly operation of all devices and parts.
This transmission system includes for the transmission draw-vehicle of draw gear: the system comprises a pulley block, a steering fixed pulley, a flexible cable, a runway, an aircraft, a separating device, an unhooking slow descending device, a temperature control device, a braking device, a resetting traction device, a launching tractor, an inclined pavement, a base, a grounding device and a launching control system;
the following steps: the pulley block fixed pulley side, the steering fixed pulley, the separating device, the temperature control device, the braking device and the reset traction device are all connected with the base of the pulley block fixed pulley side; the pulley block, the steering fixed pulley, the separating device, the braking device, the reset traction device and the launching tractor are all connected with the own grounding device; the side of a movable pulley of a pulley block is connected with a launching tractor, the launching tractor stops on an inclined road surface, the free end of a flexible cable of the pulley block is connected with an unhooking slow-descending device after passing around a plurality of steering fixed pulleys through a braking device and then passing around a plurality of steering fixed pulleys, the unhooking slow-descending device is connected with an aircraft, the aircraft is connected with a base through a separating device, and the aircraft stops on a runway; the emission control system is responsible for controlling the safe and orderly operation of all devices and parts.
When the traction device is a launching tractor, the launching system comprises: the device comprises a pulley block, a steering fixed pulley, a flexible cable, a runway, an aircraft, a separating device, a unhooking slow descending device, a temperature control device, a braking device, a resetting traction device, a launching tractor, a base, a grounding device and a launching control system;
the following steps: the pulley block fixed pulley side, the steering fixed pulley, the separating device, the temperature control device, the braking device, the reset traction device and the emission traction machine are connected with the base of the pulley block fixed pulley side; the pulley block, the steering fixed pulley, the separating device, the braking device, the reset traction device and the launching traction machine are all connected with the own grounding device; the side of a pulley block movable pulley is connected with a flexible cable of a launching tractor, the launching tractor is connected with a base, the free end of the flexible cable of the pulley block is connected with an unhooking slow-descending device after passing around a plurality of steering fixed pulleys through a braking device and then passing around a plurality of steering fixed pulleys, the unhooking slow-descending device is connected with an aircraft, the aircraft is connected with the base through a separating device, and the aircraft stops on a runway; the emission control system is responsible for controlling the safe and orderly operation of all devices and parts.
In a second aspect the invention provides an aircraft launching method:
fixing the fixed pulley side of the pulley block on the base, applying a huge traction force to the movable pulley side of the pulley block to ensure that the movable pulley side of the pulley block obtains a faster moving speed, and utilizing the amplification effect of the pulley block to ensure that the free end of the flexible cable of the pulley block obtains a particularly fast moving speed and a larger traction force;
pulley block:
the pulley block is a machine assembled by a plurality of movable pulleys and fixed pulleys, and can save labor and change the force application direction;
pulley block labor saving formula: f ═ GArticle (A)+GMovable part) The tensile force/n is (object gravity + movable pulley gravity)/the number of the flexible cable sections on the movable pulley:
a pulley block flexible cable free end moving distance formula: the moving distance of the free end of the nh flexible cable is equal to the moving distance of the object on the flexible cable section on the movable pulley;
a pulley block flexible cable free end moving speed formula: v ═ nVArticle (A)Moving speed of free end of flexible cable is equal to number of flexible cable sections on movable pulleyThe speed of movement.
Pulley:
the pulley is a small wheel with a groove at the periphery and capable of rotating around a shaft, and the pulley is a simple machine which is composed of a disc with a groove and capable of rotating around a central shaft and a flexible rope (a rope, an adhesive tape, a steel cable, a chain and the like) crossing the disc and capable of rotating around the central shaft;
the free end of a flexible cable of a pulley block is connected with an aircraft with a certain aerodynamic shape and aerodynamic layout, the surface of the aircraft is subjected to heat protection treatment, the aircraft obtains forward power through traction of the flexible cable, obtains lift force through the aerodynamic shape, or obtains lift force through the aerodynamic layout, or obtains lift force through self power, or obtains lift force through all or partial combination of the three, and the aircraft flies in the sky like flying a kite;
after the aircraft reaches the designed speed, the unhooking slow-descent device is unhooked from the aircraft, and the aircraft reaches a preset track by using inertia or self power;
after the aircraft reaches a safe distance, the unhooking slow-descending device is opened, so that the high-altitude flexible cable slowly descends to the ground; meanwhile, the braking device brakes to enable the traction device to stop slowly;
the huge traction force applied by the pulley block sliding pulley side can be obtained by 3 methods:
the first method comprises the following steps:
fixing the side of a fixed pulley of the pulley block at a very high position, such as a canyon top side, a mountain top and a deep well top side, by utilizing gravity antigravity, suspending a heavy object at the side of a movable pulley of the pulley block, and obtaining traction force and speed by utilizing huge height difference through free falling motion of the heavy object;
acceleration of gravity: generally, the acceleration g of an object near the ground falling in vacuum under the action of gravity is taken as an approximate value of 9.8 m/s for calculation2；
Formula of gravitational acceleration: g is GM/r2g is the gravitational acceleration, GM is a constant related to the earth mass, and R is the distance or radius from the earth center to the calculation point; the falling acceleration of an object in the vicinity of the surface of the moon, other planets or stars, respectively, is called the gravitational acceleration of the moonSome planet or star gravitational acceleration.
The formula of the relationship between the falling time and the distance of the free falling body motion is as follows: gt2The square of the time of fall of 2h gravity acceleration is 2 fall distance.
We calculate the effective drop height of the weight of 2000 m, hanging 10000 tons of weight, and 100 pulley blocks (this calculation is only used as an example, neglecting the weight of the movable pulley and the weight of the flexible cable, neglecting the system resistance):
the weight drop time was about 20.19 seconds and the end of drop velocity was about 197.9 m/s;
the flying moving distance of the free end of the flexible cable is about 200 kilometers, the final moving speed of the free end of the flexible cable is 19790 m/s, and the traction force of the free end of the flexible cable is about 100 tons;
namely: it is theoretically possible to provide nearly 100 tons of tractive effort to the aircraft within 20.19 seconds to launch the aircraft at 19.79 km/sec, which has exceeded the third cosmic speed of 16.7 km/sec.
Three major cosmic velocities: the minimum launch velocity required for a spacecraft to reach the earth-surrounding, earth-free, and fly out of the solar system is commonly referred to as the first, second, and third cosmic velocities, respectively; the first cosmic velocity is 7.9 km/s; a second cosmic velocity of 11.2 km/s; the third cosmic velocity is 16.7 km/s;
density of iron: 7.86g/cm310000 tons of iron, approximately a cube 11 meters on a side.
Aircraft lift formula: l ═ V (ρ × V)2sCI)/2 lift (airflow density speed)2Wing area lift coefficient)/2
At present, the biggest airplane in the world, russian's ann 225 adopts 6D-18T turbofan engines with 229kN thrust, the thrust of each engine is about 23 tons, the total thrust of 6 engines is about 140 tons, the takeoff weight of the airplane is 600 tons, and the carrying capacity of the airplane is 250 tons;
the Yangtze river-1000 turbofan engine developed by China for the domestic large aircraft C919 has the advantages that the single thrust is about 15 tons, the total thrust of 2 engines is about 30 tons, the takeoff weight of the aircraft is 77 tons, and the carrying capacity of the aircraft is 20 tons.
The five most deep canyons in the world:
the first is that: the average depth of the big canyon of Bluejiang in Yalu-Tibetan China is 2268 meters, and the deepest depth reaches 6009 meters;
secondly, the following steps: the kariygen canyon of nipaler is 60 kilometers long, and the deepest part of the canyon is 4403 meters;
the third is that: the Hu-Ju-xia in China is located in Jinshajiang river in Yunnan, and the depth is 3790 meters;
the fourth is: peru's alca canyon, the deepest canyon being about 3400 meters;
the fifth is: colorado canyon in the united states, 446 km in total length, 2133 m deepest;
the second method comprises the following steps:
the movable pulley side of the pulley block is fixed on a launching tractor, and the launching tractor placed on a long downhill is utilized to obtain traction force and speed through the gravity and power of the launching tractor.
The third method comprises the following steps:
the movable pulley side of the pulley block is fixed on a flexible cable of a launching tractor, and the traction force and the speed are obtained by utilizing a large tractor.
The function introduction of the device is as follows:
the braking device has the functions of:
controlling the moving speed of the flexible cable; controlling and assisting to control the speed of the traction device; the disorder of the flexible cable is prevented; the number of the braking devices is determined according to actual conditions on site, and a plurality of the claims mean that the number is uncertain. .
The temperature control device has the following functions:
the overheating of the flexible cable, the pulley block, the steering fixed pulley and the braking device is prevented; prevent the water in the buffer pool from freezing at low temperature.
The function of the flexible cable intermediate connecting device is as follows:
connecting flexible cables with different performances together, and using different flexible cables in different sections so as to realize different functions of heat prevention, braking and the like; the emission cost can also be reduced.
The heat-proof material and the heat-proof device have the following functions:
prevent the flexible cable, the unhooking slow-descent device, the aircraft and the like from rubbing and extruding with air to generate high-temperature damage during high-speed flight.
The reset traction device has the following functions:
and after the transmission is finished, quickly resetting the transmission system.
The unhooking slow-descending device has the functions that:
after the aircraft reaches the designed speed, the flexible cable is unhooked from the aircraft; after unhooking, slowly dropping the high-altitude flexible cable to the ground; the unhooking slow-descending device can be designed into one device, and can also be designed into two devices, namely an unhooking device and a slow-descending device, so that the unhooking function and the slow-descending function are realized respectively.
The buffer pool has the following functions:
buffering the heavy object falling at high speed, and reducing the load borne by the braking device; preventing the weight from being damaged.
The runway has the following functions:
the aircraft can safely and quickly run when the aircraft does not reach the takeoff speed.
The separating device has the functions of:
securing the aircraft on a runway prior to launch; at launch, the separation device is separated from the aircraft and launch begins.
The launching tractor has the following functions:
applying traction to the side of a movable pulley of a pulley block to obtain required traction and speed;
braking after the launching is finished;
tension is provided during resetting, so that the launching system is orderly reset.
The function of the launching tractor is as follows:
applying traction to the side of a movable pulley of a pulley block to obtain required traction and speed;
braking after the launching is finished;
tension is provided during resetting, so that the launching system is orderly reset.
The weight has the following functions:
storing potential energy at high altitude;
converting potential energy into kinetic energy in the launching process to provide traction and speed for the system;
tension is provided during resetting, so that the launching system is orderly reset.
The function of the inclined road surface is as follows:
the function of the initial downhill is to convert the potential energy of the tractor into kinetic energy and provide traction force and speed for the movable pulley side of the pulley block;
the effect of ascending the slope after launch is to assist the tractor in slowing down.
The launching vehicle has the following functions:
the method for installing the running device is provided for the aircraft, so that the aircraft can share the launching vehicle, the aircraft accessories are reduced, and the launching cost is reduced; if the water surface and the ice surface are used as the runway, the launching vehicle can be changed into a launching boat and a launching sled.
And after the aircraft reaches the takeoff speed, the launching vehicle unhooking device is unhooked, and the aircraft takes off.
The grounding device has the following functions:
the whole emission system is too large in coverage area, so that the emission system is prevented from being damaged by thunder and lightning, and workers are protected.
The effect of the diverting fixed pulley is:
changing the direction of the flexible cable; lifting the flexible cable below the flexible cable to prevent the flexible cable from contacting the ground or crossing objects; the number of diverting pulleys is determined according to the actual situation of the terrain on site, and several of the claims mean that the number is not determined.
The emission control system has the following functions:
is responsible for coordinating and controlling the safe and orderly operation of each device and part.
In a third aspect the present invention provides an aircraft:
the aircraft comprises: the aircraft comprises an aircraft body, a separation device or a separation device hanging point, a unhooking slow-falling device or a unhooking slow-falling device hanging point, a sliding device or a launching vehicle and launching vehicle unhooking device, and a heat-proof material or a heat-proof device;
the following steps: the rear end of the aircraft is provided with a separating device or a hanging point of the separating device is connected with the base, the front end of the aircraft is provided with a unhooking slow-descending device or a hanging point of the unhooking slow-descending device is connected with the traction flexible cable, a sliding device or a launching vehicle and a unhooking device of the launching vehicle are arranged below the aircraft, and the surface of the aircraft is provided with a heat-proof material or a heat-proof device for heat protection;
compared with the prior art, the invention has the beneficial effects that:
saving the fund:
the launching system can be used repeatedly, the launching cost is low, the resetting tractor can reset the system through electric power to store energy, and rockets and fuel filling are not needed.
The method is simple:
the launching threshold is very low, a height difference is utilized, the problems of heat prevention and flexible cables are solved, and most of major countries and large companies can implement the launching technology;
the heat-proof technology of China's Shenzhou airship re-entry capsule is leading worldwide, the Shenzhou airship adopts low-density ablation heat-proof materials, the speed of the airship re-entering the atmosphere is 7.9-11.2 km/s, the air is strongly rubbed and extruded, the temperature of the surface of the airship is up to more than 2000 ℃, the whole re-entering process is 530 seconds, but spacemen are arranged in the Shenzhou airship, and the temperature in the Shenzhou airship is not more than 30 ℃;
the technology of the carrier landing arresting cable of the aircraft carrier in China is leading worldwide, and the arresting cable is a steel wire rope made of special alloy steel and has extremely high strength and toughness; taking the arresting cable used in the United states as an example, the arresting cable made of steel wire twisted nylon polyester fiber has the diameter of about 36.5 mm and can resist 93 tons of destructive force; in addition, the blocking cable is required to be nonmagnetic, so that the iron particles are prevented from being worn on the adsorbing cable to reduce the service life, and the blocking cable is also resistant to high temperature, and is required to be resistant to 800-.
Energy conservation and environmental protection:
the use of rockets and chemical propellants is reduced, and the space garbage is reduced.
The use is flexible:
by adjusting the number of pulleys of the pulley block, the traction force of the traction device and the speed of the traction device, the amplification factor, the traction force and the traction speed of the free end of the flexible cable can be flexibly adjusted, so that the launching system can be large or small, the launching aircraft can be light or heavy, and the launching speed can be high or low.
The explosive power is strong:
by utilizing the gravity acceleration, the aircraft can be launched within a few seconds to tens of seconds, and the first, second and third cosmic velocities are easily reached or exceeded.
The effective load is large:
the launch need not carry a large amount of fuel, increasing the payload.
The equipment maintenance is simple:
the applied equipment is basically traditional equipment applied in a large amount at present, and the equipment has rich operation experience and simple maintenance.
The application range is wide:
the launching system can be applied to other celestial bodies without atmosphere or with thin atmosphere, and the aircraft can be launched by utilizing the falling height difference of mountains of other celestial bodies after being suspended by the power of the aircraft; the construction of a moon base and a Mars base can be promoted; the aircraft can be launched from the moon to transport minerals and drive the lunar helium 3 mining activities; the satellites can be transmitted in a large batch at a time; can be used for aircraft space exploration; the space launching can be rapidly carried out in many countries, and the human space exploration is promoted; it can also be applied to aerodynamic experiments.
Drawings
FIG. 1 is a schematic diagram of a transmitting system
FIG. 2 is a schematic view of a system for launching a heavy object as a traction device
FIG. 3 is a schematic view of a launching system of a towing device as a launching tractor
FIG. 4 is a schematic diagram of a transmission system of a traction device as a transmission traction machine
FIG. 5 is a schematic view showing the connection of the aircraft, the separation device and the unhooking descent control device
FIG. 6 is a schematic view showing the connection of the aircraft, the launch vehicle, the separation device and the unhooking descent control device
FIG. 7 is a schematic diagram of a 5-5 pulley block composed of 10 pulleys
FIG. 8 is a schematic diagram of a pulley block array composed of 4 3-3 pulley blocks
In the figure: 1. pulley block 2, steering fixed pulley 3, flexible cable 4, runway 5, aircraft 6, separating device 7, unhooking slow descending device 8, temperature control device 9, brake device 10, reset traction device 11, weight 12, buffer pool 13, launching tractor 14, launching tractor 15, flexible cable intermediate connecting device 16, launching vehicle 17, inclined road surface 18, base 19, traction device 20, launching tractor flexible cable 21, launching vehicle unhooking device 22, grounding device 23, sliding device 24, heat-proof material
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
example 1: aircraft launching system and launching method when traction device is heavy object
Referring to fig. 2, the launching system comprises, when the traction device is a heavy object: the device comprises a pulley block (1), a steering fixed pulley (2), a flexible cable (3), a runway (4), an aircraft (5), a separating device (6), an unhooking slow-falling device (7), a temperature control device (8), a braking device (9), a resetting traction device (10), a heavy object (11), a buffer water pool (12), a base (18) and a grounding device (22);
the following steps: the fixed pulley side of the pulley block (1), the steering fixed pulley (2), the separating device (6), the temperature control device (8), the braking device (9) and the reset traction device (10) are all connected with a base (18) of the pulley block; the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9) and the reset traction device (10) are all connected with a grounding device of the pulley block; the side of a movable pulley of a pulley block (1) is connected with a heavy object (11), the free end of a pulley block flexible cable (3) is connected with a unhooking slow-descending device (7) after passing around a plurality of steering fixed pulleys (2) through a braking device (9) and then passing around the plurality of steering fixed pulleys (2), the unhooking slow-descending device (7) is connected with an aircraft (5), the aircraft (5) is connected with a base (18) through a separating device (6), the aircraft (5) stops on a runway (4), and a buffer water pool (12) is arranged below the heavy object.
The following describes a specific launching process of the launching method by taking a traction device as a weight as an example:
in the first step, the separating device (6) acts to be disconnected with the aircraft (5), the aircraft (5) is dragged by the flexible cable (3) to rapidly slide on the runway (4), and meanwhile, the temperature control device (8) begins to cool the pulley block (1), the steering fixed pulley (2) and the flexible cable (3).
And secondly, after the running speed of the aircraft (5) reaches the takeoff speed, the aircraft leaves the runway (4) and starts flying.
And thirdly, after the flying speed of the aircraft (5) reaches the designed speed, the unhooking slow-descending device (7) is unhooked from the aircraft (5), and the aircraft (5) goes to the target track by utilizing inertia or self power.
Fourthly, after the aircraft (5) leaves the unhooking slow-descending device (7) to reach a safe distance, the unhooking slow-descending device (7) is opened, and the high-altitude flexible cable (3) is slowly descended to the ground; and simultaneously, the braking device (9) starts braking, so that the speed of the flexible cable (3) and the weight (11) starts to be reduced, and simultaneously, the temperature control device (8) starts to cool the braking device (9).
And fifthly, the brake device (9) continues to work, the speed of the flexible cable (3) and the heavy object (11) is reduced to 0 m/s, and meanwhile the buffer pool (12) buffers the heavy object (11) to enable the heavy object (11) to land softly.
And sixthly, the unhooking slow descending device (7) is continuously opened, so that the high-altitude flexible rope (3) is slowly descended to the ground, and the flexible rope (3) is in soft landing.
And seventhly, the flexible cable (3), the heavy object (11) and the movable pulley of the pulley block (1) are lifted to the initial position by the reset traction device (10), and the reset is completed.
And step eight, stopping the temperature control device (8) to complete the emission.
Example 2: aircraft launching system and launching method for launching towing vehicle by using towing device
Referring to fig. 3, the present launching system for launching a towing vehicle comprises: the device comprises a pulley block (1), a steering fixed pulley (2), a flexible cable (3), a runway (4), an aircraft (5), a separating device (6), an unhooking slow-descent device (7), a temperature control device (8), a braking device (9), a reset traction device (10), a launching tractor (13), an inclined pavement (17), a base (18) and a grounding device (22);
the following steps: the fixed pulley side of the pulley block (1), the steering fixed pulley (2), the separating device (6), the temperature control device (8), the braking device (9) and the reset traction device (10) are all connected with a base (18) of the pulley block; the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9), the reset traction device (10) and the launching tractor (13) are all connected with the grounding device of the self; the side of a movable pulley of a pulley block (1) is connected with a launching tractor (13), the launching tractor (13) stops on an inclined road surface (17), the free end of a pulley block flexible cable (3) bypasses a plurality of steering fixed pulleys (2), passes through a braking device (9), bypasses a plurality of steering fixed pulleys (2), and is connected with a unhooking slow-descending device (7), the unhooking slow-descending device (7) is connected with an aircraft (5), the aircraft (5) is connected with a base (18) through a separating device (6), and the aircraft (5) stops on a runway (4).
The following takes the traction device as an example to illustrate the specific launching process of the launching method:
in the first step, the launching tractor (13) is started to tighten the launching system and the flexible cable (3) to bear the initial tension and prepare for launching.
And secondly, the launching tractor (13) accelerates for traction while the separating device (6) acts to disconnect from the aircraft (5).
And thirdly, the aircraft (5) is dragged by the flexible cable (3) to rapidly slide on the runway (4), and meanwhile, the temperature control device (8) begins to cool the pulley block (1), the steering fixed pulley (2) and the flexible cable (3).
Fourthly, after the running speed of the aircraft (5) reaches the takeoff speed, the aircraft leaves the runway (4) and starts flying.
Fifthly, after the flying speed of the aircraft (5) reaches the designed speed, the unhooking slow-descending device (7) is unhooked from the aircraft (5), and the aircraft (5) goes to the target track by utilizing inertia or self power.
Sixthly, after the aircraft (5) leaves the unhooking slow-descending device (7) to reach a safe distance, the unhooking slow-descending device (7) is opened, and the high-altitude flexible cable (3) is slowly descended to the ground; meanwhile, the braking device (9) starts braking, the launching tractor (13) starts decelerating, and the speed of the flexible cable (3) starts to decrease; simultaneously, the temperature control device (8) starts to cool the brake device (9).
And seventhly, the brake device (9) continues to work, the speed of the flexible cable (3) and the speed of the launching tractor (13) are reduced to 0 m/s, and meanwhile, the launching tractor (13) is braked when the speed is reduced to 0 m/s, so that the system and the flexible cable are tensioned to bear initial tension.
And eighthly, continuously opening the unhooking slow descending device (7) to slowly descend the high-altitude flexible rope (3) to the ground, and softly landing the flexible rope (3).
And ninthly, the resetting traction device (10) starts to pull, and the launching tractor (13) is matched to lift the flexible cable (3), the launching tractor (13) and the movable pulley of the pulley block (1) to the initial position, so that resetting is completed.
And step ten, stopping the temperature control device (8) to complete the emission.
Example 3: aircraft launching system and launching method when towing device is launching tractor
Referring to fig. 4, the launching system when the towing apparatus is a launching tractor comprises: the device comprises a pulley block (1), a steering fixed pulley (2), a flexible cable (3), a runway (4), an aircraft (5), a separating device (6), an unhooking slow-falling device (7), a temperature control device (8), a braking device (9), a resetting traction device (10), a launching tractor (14), a base (18) and a grounding device (22);
the following steps: the fixed pulley side of the pulley block (1), the steering fixed pulley (2), the separating device (6), the temperature control device (8), the braking device (9), the reset traction device (10) and the launching traction machine (14) are connected with a base (18) of the pulley block; the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9), the reset traction device (10) and the launching traction machine (14) are all connected with the own grounding device; the side of a movable pulley of a pulley block (1) is connected with a launching tractor flexible cable (20), a launching tractor (14) is connected with a base (18), the free end of the pulley block flexible cable (3) is connected with a unhooking slow-descending device (7) after passing around a plurality of steering fixed pulleys (2) through a braking device (9) and then passing around a plurality of steering fixed pulleys (2), the unhooking slow-descending device (7) is connected with an aircraft (5), the aircraft (5) is connected with the base (18) through a separating device (6), and the aircraft (5) stops on a runway (4).
The following takes the traction device as a transmitting traction machine as an example to explain the specific transmitting process of the transmitting method:
in the first step, the launching tractor (14) is started to tighten the launching system and the flexible cable (3) to bear the initial tension, and the launching preparation is made.
And secondly, the launching tractor (14) accelerates for traction while the separating device (6) is disconnected from the aircraft (5).
And thirdly, the aircraft (5) is dragged by the flexible cable (3) to rapidly slide on the runway (4), and meanwhile, the temperature control device (8) begins to cool the pulley block (1), the steering fixed pulley (2) and the flexible cable (3).
Fourthly, after the running speed of the aircraft (5) reaches the takeoff speed, the aircraft leaves the runway (4) and starts flying.
Fifthly, after the flying speed of the aircraft (5) reaches the designed speed, the unhooking slow-descending device (7) is unhooked from the aircraft (5), and the aircraft (5) goes to the target track by utilizing inertia or self power.
Sixthly, after the aircraft (5) leaves the unhooking slow-descending device (7) to reach a safe distance, the unhooking slow-descending device (7) is opened, and the high-altitude flexible cable (3) is slowly descended to the ground; meanwhile, the braking device (9) starts braking, the launching tractor (14) starts decelerating, and the speed of the flexible cable (3) starts to decrease; simultaneously, the temperature control device (8) starts to cool the brake device (9).
And seventhly, the brake device (9) continues to work, the speed of the flexible cable (3) and the launching tractor (14) is reduced to 0 m/s, and the launching tractor (14) is locked when the speed is reduced to 0 m/s, so that the system and the flexible cable are tensioned to bear initial tension.
And eighthly, continuously opening the unhooking slow descending device (7) to slowly descend the high-altitude flexible rope (3) to the ground, and softly landing the flexible rope (3).
And ninthly, the resetting traction device (10) starts to pull, and meanwhile, the launching traction machine (14) is matched to pull the flexible cable (3), the pulley block (1) side and the launching traction machine flexible cable (20) to initial positions, and resetting is completed.
And step ten, stopping the temperature control device (8) to complete the emission.
Example 4: aircraft structure one
Referring to fig. 5, the aircraft comprises: the device comprises an aircraft (5), a separation device (6), a unhooking slow-descent device (7), a sliding device (23) and a heat-proof material (24);
the following steps: the rear end of the aircraft (5) is provided with a separating device (6) connected with a base (18), the front end is provided with a unhooking slow descending device (7) connected with a traction flexible cable (3), a sliding device (23) is arranged below the aircraft, and the surface of the aircraft is provided with a heat-proof material (24) for heat protection;
example 5: aircraft structure two
Referring to fig. 6, the aircraft comprises: the aircraft separation device comprises an aircraft (5), a separation device (6), a unhooking slow-descending device (7), a launching vehicle (16), a launching vehicle unhooking device (21) and a heat-proof material (24);
the following steps: the rear end of the aircraft (5) is provided with a separating device (6) connected with a base (18), the front end is provided with a unhooking slow descending device (7) connected with a traction flexible cable (3), the lower part is provided with a launching vehicle unhooking device (21) connected with a launching vehicle (16), and the surface is provided with a heat-proof material (24) for heat protection;
the above examples are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and those skilled in the art should make insubstantial changes and substitutions based on the present invention.
Claims (15)
1. An aircraft launching system, characterized by:
the method comprises the following steps: the device comprises a pulley block (1), a flexible cable (3), an aircraft (5), a separating device (6), a unhooking slow-descending device (7), a base (18) and a traction device (19);
the following steps: the fixed pulley side of the pulley block (1) is connected with the base (18), the movable pulley side of the pulley block (1) is connected with the traction device (19), the free end of the flexible cable (3) of the pulley block (1) is unfolded and then connected with the unhooking slow-descending device (7), the unhooking slow-descending device (7) is connected with the aircraft (5), and the aircraft (5) is connected with the base (18) through the separation device (6).
2. The aircraft launching system according to claim 1, characterized in that: further comprising: a steering fixed pulley (2), a runway (4) and a braking device (9);
the following steps: the fixed pulley side of the pulley block (1) is connected with the base (18), the movable pulley side of the pulley block (1) is connected with the traction device (19), the free end of the flexible cable (3) of the pulley block (1) bypasses a plurality of steering fixed pulleys (2), then bypasses a plurality of steering fixed pulleys (2) through the braking device (9), is connected with the unhooking slow-descending device (7) after being unfolded, the unhooking slow-descending device (7) is connected with the aircraft (5), the aircraft (5) is connected with the base (18) through the separating device (6), and the aircraft (5) stops on the runway (4).
3. The aircraft launching system according to claim 1 or 2, characterized in that: the following features or some of them are also included:
the traction device (19) is a heavy object (11) with a falling height difference;
the traction device (19) is a launching tractor (13);
the traction device (19) is a launching tractor (14);
the pulley block (1), the steering fixed pulley (2) and the braking device (9) are provided with a temperature control device (8);
the launching end of the aircraft (5) is provided with a resetting traction device (10);
a launching vehicle (16) is arranged below the aircraft (5), and the aircraft (5) is connected with the launching vehicle (16) through a launching vehicle unhooking device (21);
the pulley block (1) can be a pulley block formed by a plurality of pulleys or a pulley block array formed by a plurality of sets of pulley blocks, and the number and arrangement mode of the pulleys are determined according to actual requirements;
the flexible cable (3), the aircraft (5) and the unhooking slow-descending device (7) adopt heat-proof materials or adopt heat-proof devices or adopt heat-proof materials to be coated or covered to prevent heat and insulate heat;
the flexible cables (3) are provided with flexible cable intermediate connecting devices (15) which are used for connecting the flexible cables with different performances together;
the aircraft (5) uses the traction force of the flexible cable (3) as launching power, obtains lift force through aerodynamic configuration, or obtains lift force through aerodynamic layout, or obtains lift force through self power, or obtains lift force through the combination of all or part of the three components;
the braking device (9) can be one set or a plurality of sets, and can be arranged on the flexible cable (3) or the pulley;
the unhooking slow-descending device (7) can be a set of device, can also be formed by separately arranging the unhooking device and the slow-descending device, and can also be formed by only arranging the unhooking device;
the disengaging parts in the disengaging device (6) and the disengaging slow descending device (7) can be arranged independently or can be integrated on the aircraft (5);
the runway (4) can be a runway on land, an overwater runway taking the water surface as the runway, and an ice runway taking the ice surface as the runway;
the emission control system is arranged and used for coordinating and controlling the safe and orderly operation of all the parts.
4. The aircraft launching system according to claim 3, characterized in that: further comprising: a buffer pool (12);
when the traction device (19) is a heavy object (11) with a falling height difference, a buffer pool (12) is arranged below the heavy object (11); if the water temperature reaches or is lower than the freezing point temperature, the buffer water tank (12) is provided with a temperature control device (8) to prevent the water from freezing.
5. The aircraft launching system according to claim 3, characterized in that: further comprising: an inclined road surface (17);
when the traction device (19) is a launching tractor (13), the launching tractor (13) is placed on the inclined road surface (17).
6. The aircraft launching system according to claim 3, characterized in that: further comprising: a grounding device (22);
the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9), the reset traction device (10), the launching tractor (13) and the launching tractor (14) are all required to be provided with grounding devices (22).
7. An aircraft launching method, characterized by:
fixing the fixed pulley side of the pulley block (1) on a base (18), tightening the pulley block (1), unfolding the free end of a flexible cable (3) of the pulley block (1), applying traction force and traction speed on the movable pulley side of the pulley block (1), towing an aircraft (5) by using the free end of the flexible cable (3) of the pulley block (1), providing flight speed and traction force for the aircraft (5) by using the speed amplification effect of the pulley block (1), obtaining the lift force by the aircraft (5) through pneumatic appearance, or obtaining the lift force through pneumatic layout, or obtaining the lift force through self power, or obtaining the lift force through the combination of all or part of the three, and flying in the sky like a kite;
when the aircraft reaches the designed flying speed, the unhooking slow-descending device (7) acts to unhook the aircraft (5) from the flexible cable (3), and the aircraft (5) reaches the preset orbit by using inertia or self power.
8. The aircraft launching method according to claim 7, characterised in that: the speed magnification factor and the traction force reduction factor of the free end of the traction flexible cable (3) are adjusted by adjusting the number of pulleys of the pulley block (1).
9. The aircraft launching method according to claim 7, characterised in that: the speed and the traction force of the free end of the traction flexible cable (3) are adjusted by adjusting the traction speed and the traction force of a traction device (19) at the fixed pulley side of the pulley block (1).
10. The aircraft launching method according to claim 7, characterised in that: the following features or some of them are also included:
the traction force and the traction speed are obtained by utilizing the gravity acceleration of a heavy object (11) which is hung at a high place and has a drop height difference, or the traction force and the traction speed are obtained by launching a tractor (13), or the traction force and the traction speed are obtained by launching a tractor (14);
controlling the speed of the traction means (19) by using the braking means (9);
the aircraft (5) is unhooked from the flexible cable (3) by using an unhooking slow descending device (7), and the high-altitude flexible cable (3) is softly landed after unhooking;
the unhooking slow-descending device (7) can be a set of device, can also be formed by separately arranging the unhooking device and the slow-descending device, and can also be formed by only arranging the unhooking device;
the temperature control device (8) is used for keeping the pulley block (1), the steering fixed pulley (2), the braking device (9) and the buffer pool (12) at a temperature suitable for working;
the flexible cable (3), the aircraft (5) and the unhooking slow-descending device (7) are heat-proof and heat-insulating by adopting a heat-proof material or adopting a heat-proof device or coating the heat-proof material or covering the heat-proof material;
the runway (4) is used to ensure that the aircraft (5) safely runs when the takeoff speed is not reached;
resetting the system by using a resetting traction device (10);
grounding devices (22) are arranged on the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9), the reset traction device (10), the launching tractor (13) and the launching tractor (14) to prevent a launching system and workers from being damaged by lightning;
by using the launching vehicle (16), the parts of the aircraft (5) are reduced, and the purposes of saving money and protecting the environment are achieved;
the pulley block (1), the steering fixed pulley (2), the separating device (6), the braking device (9), the reset traction device (10), the launching traction machine (14) and the temperature control device (8) are firmly fixed by using a base (18);
the flexible cable (3) is changed in direction by using the steering fixed pulley (2), or the flexible cable (3) is lifted under the flexible cable (3) to prevent the flexible cable (3) from contacting the ground or crossing objects;
the flexible cables with different performances are connected together by using the flexible cable intermediate connecting device (15), so that different functions can be realized at different parts of the flexible cables, and the fund can be saved;
when traction force and traction speed are obtained by utilizing the gravity acceleration of the weight (11) with the falling height difference, the weight (11) falling at high speed can be buffered through the buffer water pool (12) below the weight (11), the weight (11) is prevented from being damaged, and the load born by the braking device (9) is reduced;
when the traction force and the traction speed are obtained through the launching tractor (13), the launching tractor (13) can be placed on an inclined road surface (17), the potential energy of the launching tractor (13) is converted into kinetic energy through the inclined road surface (17), and partial or all traction force and speed are provided for the movable pulley side of the pulley block (1);
the emission control system is arranged and used for coordinating and controlling the safe and orderly operation of all the parts.
11. An aircraft, characterized in that: the method comprises the following steps: the aircraft (5), the flexible cable unhooking device or the hanging point of the flexible cable unhooking slow-descending device (7);
the aircraft (5) obtains launching power through the traction of the flexible cable (3), obtains lift force through the pneumatic appearance, or obtains lift force through the pneumatic layout, or obtains lift force through self power, or obtains lift force through the whole or partial combination of the above three, flies in the sky like flying a kite, and is provided with a flexible cable unhooking device or a flexible cable unhooking device hanging point or a flexible cable unhooking slow-falling device (7) hanging point.
12. The aircraft of claim 11, wherein: further comprising: devices or materials that protect or insulate against heat;
the aircraft (5) adopts heat-proof materials or adopts a heat-proof device or is coated with the heat-proof materials or is covered with the heat-proof materials to prevent heat and insulate heat.
13. The aircraft of claim 11, wherein: further comprising: separation device (6) or separation device (6) hang point:
the aircraft (5) is provided with a separating device (6) or a hanging point of the separating device (6).
14. The aircraft of claim 11, wherein: further comprising: a launch vehicle unhooking device (21) or a launch vehicle unhooking device (21) hanging point;
the aircraft (5) is provided with a launching vehicle unhooking device (21) or a hanging point of the launching vehicle unhooking device (21).
15. The aircraft of claim 11, wherein: further comprising: a running device (23);
the aircraft (5) is provided with a running device (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2022/000020 WO2022170888A1 (en) | 2021-02-10 | 2022-02-08 | Spacecraft launch system and launch method, and spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110181762 | 2021-02-10 | ||
| CN2021101817626 | 2021-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110330760.9A Pending CN112937900A (en) | 2021-02-10 | 2021-03-29 | Aircraft launching system, launching method and aircraft |
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| WO (1) | WO2022170888A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2022170888A1 (en) * | 2021-02-10 | 2022-08-18 | 张志刚 | Spacecraft launch system and launch method, and spacecraft |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2726533B1 (en) * | 1994-11-04 | 1996-12-27 | Giat Ind Sa | DEVICE FOR LAUNCHING AN AIRCRAFT |
| DE102006002921A1 (en) * | 2005-04-28 | 2006-11-02 | Bosch Rexroth Ag | Hydraulic catapult drive for accelerating e.g. car of fairground ride, has disk sets moving through hydro cylinder, where traction force is transferred into actuator depending upon controlling of hydro cylinder |
| US7530532B2 (en) * | 2006-07-03 | 2009-05-12 | Keith Peter Watts | Counterweight based rocket launch platform |
| CN201343147Y (en) * | 2008-12-03 | 2009-11-11 | 北京航天发射技术研究所 | Emitting system for ejecting aircraft in pneumatic track |
| CN102152856B (en) * | 2010-12-31 | 2014-04-16 | 朱惠芬 | Pneumatic ejector for carrier-based airplanes of airplane carrier |
| CN103863571B (en) * | 2012-12-12 | 2016-11-23 | 中航商用航空发动机有限责任公司 | Aircraft ejection kit and airplane catapult method |
| US9074844B2 (en) * | 2013-07-25 | 2015-07-07 | Alexander Dankwart Essbaum | Rocket launch tower |
| CN203733379U (en) * | 2013-12-30 | 2014-07-23 | 广州广船国际股份有限公司 | Ejection device of test dolly |
| CN104760706B (en) * | 2014-05-12 | 2017-03-15 | 葛愉成 | A kind of flywheel energy storage propulsion plant |
| CN104803006B (en) * | 2015-04-27 | 2016-08-31 | 西北工业大学 | A kind of unmanned aerial vehicle ejecting launching apparatus |
| CN105667835A (en) * | 2016-03-25 | 2016-06-15 | 济南环太机电技术有限公司 | Heavy lift launch vehicle catapult and ejection method thereof |
| CN105836152B (en) * | 2016-03-25 | 2017-12-05 | 济南环太机电技术有限公司 | Synchronous acting catapult technique is concentrated in heavy spacecraft ejection system and its scattered accumulation of energy |
| CN109733631B (en) * | 2019-01-09 | 2020-12-18 | 嘉兴恒益安全服务股份有限公司 | Superspeed aircraft launching simulation platform |
| CN211893698U (en) * | 2020-03-27 | 2020-11-10 | 魏永久 | Rocket launching pad |
| CN112937900A (en) * | 2021-02-10 | 2021-06-11 | 张志刚 | Aircraft launching system, launching method and aircraft |
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2021
- 2021-03-29 CN CN202110330760.9A patent/CN112937900A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022170888A1 (en) * | 2021-02-10 | 2022-08-18 | 张志刚 | Spacecraft launch system and launch method, and spacecraft |
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