WO2015000407A1

WO2015000407A1 - Belt-type carrier-based aircraft booster system, and method of working with centralized and random boosting with distributed energy storage

Info

Publication number: WO2015000407A1
Application number: PCT/CN2014/081448
Authority: WO
Inventors: 姜明; 邱玉成; 霍刚; 姜鹏
Original assignee: 济南环太机电技术有限公司
Priority date: 2013-07-02
Filing date: 2014-07-02
Publication date: 2015-01-08
Also published as: CN103332297A; CN103332297B

Abstract

A belt-type carrier-based aircraft booster system, comprising a booster module assembly, a homing module assembly, a runway module, a sliding shuttle module and a controller module; the booster module assembly, the homing module assembly and the controller module are disposed at the bottom of the runway module; the sliding shuttle module is disposed in the middle of a conveyor belt (15); the conveyor belt is disposed in the runway module; two ends of the conveyor belt are respectively connected to the booster module assembly and the homing module assembly; the booster module assembly and the homing module assembly respectively transfer traction kinetic energy to the sliding shuttle module, so as to enable the sliding shuttle module to work for catapulting or homing. The system has a simple structure and high modularization.

Description

The present invention relates to the field of military equipment technology, and in particular to a belt carrier-based booster system and a distributed randomized energy-concentrated random boosting work method.

At present, there are mainly two kinds of carrier-based catapults used on aircraft carriers. One is a steam catapult used on a US aircraft carrier. The booster uses steam as a power to drive the traction hook through the piston in the open cylinder to accelerate the take-off. . The steam catapult equipment is bulky, occupies a large space, and the production process is complicated. It also consumes a large amount of fresh water. Since the US steam ejector uses a slotted cylinder, the steam leakage is large, the energy consumption is large, and the cylinder seal is used. Short life and high maintenance cost. In the cold or winter, the steam of the Pan leak will freeze on the deck, which will seriously affect the take-off or landing of the carrier. This is also the scope of the US aircraft carrier's activities in winter, or simply do not dare to The root cause of Arctic activities. Due to the confidentiality of technology, only the US military is equipped with steam catapults on 11 aircraft carriers. The disadvantages of steam catapults are as follows:

1) Heavy and bulky, the total weight of a steam-powered booster is nearly 1000 tons. It can be divided into functions according to function: 1. Take-off system 2. Steam system 3. Homing system 4. Hydraulic system 5. Pre-force system 6. Lubrication system 7. Control system. These systems can be broken down into more small systems; the cross-sectional area of the flight deck for the placement of the cylinder is roughly 1.6 * 1.8 - 2.88 square meters, and then consider the booster nearly 100 meters in length, then this part The volume is connected to 300 cubic meters. The volume of the two cans is also more than 200 cubic meters, plus the place occupied by the steam pipe and other devices, the total volume is up to 600 cubic meters, and the total volume of the four sets of boosters is 2,400 cubic meters. As for the weight, one The set of boosters has at least 1,000 tons, and the set of 4 sets has 4,000 tons;

2) High requirements on materials and processes. Now, with the exception of the United States, naval powers, including Britain and France, cannot be manufactured and purchased from the United States;

3) Low efficiency and high cost. A boost will cost 800-1000 kilograms of fresh water. The steam is first produced to desalinate the seawater, and the desalinated water is heated in the boiler into high temperature and high pressure steam. And the conversion of these steam into a driving force is only 4% to 6%! If the boost is carried out at the minimum interval, it is necessary to consume 20% of the steam of the aircraft carrier boiler; 4) The system is complex and has a large number of operators. A booster requires about 120 operators and maintenance personnel. The four boosters require more than 500 operating and maintenance personnel, accounting for about 10% of the total shipbuilding, and the amount of maintenance is large. Each shot of 400 to 500 flights requires 12-day overhaul by the crew.

5) It is a large ejection power. The requirements of the catapult for the catapult carrier are that it requires a huge amount of power in a short period of time. The burst-type 35-60 ton carrier-based aircraft is at a distance of 90 100 meters. The internal projectile hits the takeoff speed. The power of the largest steam catapult is now 4.75 6.3333 million kilowatts! And the work time is only 2.6 seconds! The nuclear power plant of the largest nuclear-powered aircraft carrier in the United States has a total power of 280,000 horsepower and a contract of 200,000 kilowatts! And a steam catapult has a power of more than 64,000 watts! If it is not for two 100-cubic-meter large gas storage tanks to help store energy, the 200,000-kilowatt nuclear reactor will not be able to afford the fourth booster anyway;

6) High cost and high confidentiality of production technology. It is known that a US steam catapult in active service is sold for at least US$80 million. Currently, only the United States has mastered production technology, and its sales scope is only the United States and its allies. The second type is the electromagnetic catapult. Due to the defects of the steam catapult, the US Navy spent 28 years and cost 3.2 billion US dollars. The electromagnetic catapult was successfully developed. Although it has been successfully tested on land, it is huge. The power consumption is huge, the structure is too complicated, the stability is very unreliable, and it can't adapt to the harsh environment of sea moisture and salt spray. So it is still in the research stage, and the US military has not dared to officially equip the aircraft carrier. In summary, there is no carrier-based catapult, no matter the size of the aircraft carrier, can not form combat power, the principle of the steam catapult is a large and long steam engine! The steam engine is characterized by long hours of work, not outbreak work, so he is not adapted to the way the booster works. The principle of an electromagnetic catapult is a linear motor. His work is the same as that of a steam engine, and it is only suitable for long-term work, but not for outbreak work. Regardless of the steam catapult or the electromagnetic catapult, the instantaneous release of huge energy is achieved by energy storage. The power consumption is 64,000 kilowatts. The steam catapult is stored by two 00 cubic meters of steam storage tanks. The high-pressure steam is converted into mechanical kinetic energy through the open cylinder; and the electromagnetic ejector is realized by means of forcibly storing the power station. The so-called forced energy storage station drives the electric power of the traditional power station to drive eight 8000 kW dual-purpose motors respectively. Energy storage, when the electromagnetic ejector requires a large current to do work, the eight motors are immediately converted into eight generators, which convert the rotating potential energy into electrical energy, and concentrate the electric energy in the linear motor of the electromagnetic ejector to convert into magnetic energy, which is driven by magnetic energy. The high-speed movement of the mover is converted into kinetic energy, The quantity consumes 30-50% in the process of multiple conversions. Since the steam catapult and the electromagnetic catapult perform instantaneous work by the steam pressure and the magnetic field potential energy, the initial energy is required, so the energy waste is huge, according to relevant information. The actual energy used on the carrier aircraft is less than 10%, which is the least economical two ejection modes. As shown in the takeoff curve in Figure 6, the carrier aircraft receives huge traction at the initial takeoff, so the speed is fast. As the energy is consumed, the potential energy decreases and the speed gradually decreases. The shadow below the curve indicates the energy consumption; As shown in Figure 7, the initial speed of the carrier aircraft is low, but as the inertial force of the energy release increases, the speed becomes faster and faster, and the curve jumps. This boosting curve and the take-off of the carrier aircraft are empty. Comparing the speed curves, comparing the energy consumption under the curve of Fig. 6, the shadow under the curve of Fig. 7 is significantly smaller than that of Fig. 6, which is the advanced nature of the random boosting principle of the present invention, the smaller the energy consumption, the carrier catapult In terms of it, it means better implementation.

Summary of the invention

The technical problem to be solved by the present invention is to overcome the above disadvantages and provide a simple structure, ingenious design, scientific and reasonable, small size, convenient use, high safety, long service life, energy saving, high energy efficiency, and adaptability to each. The carrier-based aircraft booster system and the distributed energy storage centralized random boosting work method of the carrier-based aircraft are implemented in the following manner: The system includes the boosting module assembly and the homing Module assembly, runway module, shuttle module and controller module, where:

The boosting module assembly is composed of more than one boosting module arranged on the runway module. The boosting module comprises a T-shaped box, a driving belt, a motor, a transmission shaft, a clutch, a brake and a base, wherein the bottom of the T-shaped box is in the middle of the base Fixed, the motor is fixed on the base on both sides of the τ-shaped box, and the transmission shaft is inserted through the bearing seat in the middle of the τ-shaped box. The two ends of the transmission shaft are respectively provided with a clutch and a brake, a passive part of the clutch and a brake The drive shaft is fixed, the active part of the clutch is connected with the pulley, the pulley is connected with the drive shaft through the bearing, and the outer circle of the pulley is connected with the pulley of the motor shaft end through the belt, and the two ends of the folded belt are fixed by the belt pressing plate in the middle of the τ-shaped box On the transmission shaft, the middle portion of the folded belt is connected with the shuttle assembly, and the upper portion of the τ-shaped box is provided with a guide roller, and the meter roller is connected to the guide roller, and the transmission belt passes through between the guide roller and the meter. Both ends of the upper part of the T-shaped box are connected with the runway module, and the top of the τ-shaped box is provided with a grooved track, a grooved track Top of the tank module runway The homing module is composed of more than one homing module arranged in the runway module. The homing module includes a T-shaped case drive belt, a motor, a drive shaft, a clutch, a brake and a base, wherein the T-box The bottom of the body is fixed in the middle of the base, the motor is fixed on the base on both sides of the τ-shaped box body, the transmission shaft is inserted through the bearing seat in the middle of the τ-shaped box body, and the two ends of the transmission shaft are respectively provided with a clutch and a brake, the clutch The passive part and the brake are fixed to the drive shaft, and the active part of the clutch is connected with the pulley. The pulley is connected with the drive shaft through the bearing. The outer circle of the pulley is connected with the pulley of the motor shaft end through the belt, and the two ends of the folded belt are fixed by the belt pressure plate. On the transmission shaft in the middle of the τ-shaped box body, the middle portion of the folded belt is connected with the shuttle assembly, and the upper portion of the τ-shaped box body is provided with a guide roller, and the guide roller is connected with a Η--meter, and the transmission belt is guided from the guide roller. Passing through the middle of the meter, the two ends of the upper part of the τ-shaped box are connected to the runway module, and the top of the τ-shaped box is provided with a groove. The track, the groove track is connected with the groove track at the top of the runway module; the runway module is composed of the runway bracket, the reverse roller, the intermediate roller and the groove track, and the raceway bracket is connected to the boost module and the homing module. Between the two ends, the shuttle module constitutes a linear sliding track, the reverse roller is arranged at the end of the track module to provide a transmission guide for the transmission belt, and the intermediate roller is arranged in the middle of the track module to provide a guiding support for the transmission belt; It is arranged in the groove type track, and its structure is composed of a shuttle, a shuttle frame, a roller, a belt roller and a balance roller, and the belt roller is disposed outside the two ends of the shuttle frame, and the balance roller is disposed on the belt roller. Between the roller and the balance roller, the roller shaft and the balance roller are composed of a roller shaft and a sleeve. The two ends of the roller shaft extend outward through the two non-folding edges of the shuttle frame, and the roller is disposed at both ends of the roller shaft and the groove. The two sides of the track are rollingly connected, and the sleeve is arranged in the middle of the roller shaft between the two downward flanges of the shuttle frame; the intermediate position of the folding belt is connected to the drive shaft of the boost module, from the runway module Middle middle The upper portion of the idler, the end reversing roller and the joining roller are passed over the sleeve of the balancing roller; the intermediate position of the folding belt is connected to the drive shaft of the homing module, from the intermediate roller in the middle of the runway module, The upper end of the end roller and the end of the shuttle frame are sleeved on the sleeve of the balance roller; the controller module is composed of a strong electric control switch, a weak electric control switch and a meter The electric control switch only controls the motor of the boosting module and the motor of the homing module. The weak electric control switch only controls the clutch and the brake, and is set on the boosting module and the returning roller of the homing module. The precise detection of the moving distance of the belt provides a precise switching signal for the weak current control switch. The invention also provides a randomized boosting method for the distributed energy storage concentrated work of the belt carrier-based booster system. According to the maximum boosting carrier aircraft tonnage designed by the booster module assembly, more than one side of the runway module is arranged. The boosting module, at least one end of the drive shaft on each boosting module is connected to a motor through a clutch, in order to solve the problem of grid overload caused by the excessive total load caused by the simultaneous starting of all the motors of the booster, the strong electric control switch pair All the motors are started one by one to make the air load rotate and disperse the energy storage. After the motor starts, the pulley and the normal rotation part of the electromagnetic clutch are also rotated to distribute the energy, so that the motors in all the booster modules in the system rotate at no load. In the process, the electric energy is converted into kinetic energy and stored in a distributed manner. Since the drive shafts of all the boosting modules are connected to the shuttle module through the transmission belt, the shuttle module is connected to the carrier aircraft, and the booster system needs to carry on the carrier aircraft. When boosting traction, the weak current control switch simultaneously sends power to the electromagnetic clutch on the drive shaft of all booster modules, the clutch is engaged, and the transmission is transmitted. The shaft instantaneously combines the rated power of all the booster module motors with the kinetic energy of the idle storage through the clutch, and concentrates on the shuttle module through the transmission belt to complete the centralized random work. The random pride is the boosting speed of the shuttle assembly. The take-off speed of the carrier aircraft itself on the take-off runway is also bound. Because the drive shaft is based on the diameter of the drive shaft at the beginning of the winding drive belt, the transmission belt transmits power at a low rotational speed and large torque, due to the number of winding layers. Increase, the winding speed of the belt increases rapidly, so the boosting acceleration generated by the belt during the winding process coincides with the take-off acceleration of the carrier to achieve random boost; set the length of the boosting runway and the length of the belt winding Equal to 100 meters, as long as the time of winding the belt with the same length of the runway on the drive shaft is set to 2.6 seconds, the carrier can run the 100-meter booster runway in 2.6 seconds, the carrier can smooth take-off from the runway boost, calculated as - carrier machine must be 30m I s ² acceleration is to take off on the runway 100 meters, Takeoff speed and acceleration do not exercise time is calculated as:

V = - 2 L = s/200 x 30 « 77.46m / s (1)

t = /2Ι I a = ^200 / 30 « 2.58s (2)

The length of the belt = the length of the runway, L = the sum of the lengths of the belts wound on the drive shaft, the length of the belt -

L = (L1 + L2 + ''LN) 100 m = length of the booster runway (3) Formula for calculating the length of each belt driven on the drive shaft:

Li=3,14(D+2dn), i=l 2 3...! ! (4) Where D is the diameter of the drive shaft; d the thickness of the drive belt; the number of layers of the drive belt;

It is known that the length of the boosting runway = the length of the belt is 100 meters, ignoring the density of the belt winding, the diameter D of the drive shaft, the value of the thickness d of the belt is substituted into the formula (4) to calculate the length of each belt, and then the belts of each layer The length of the tired-Η-· is close to 100 meters, and the number of layers in the last layer is set to the number of shaft revolutions required to wind the 100-meter belt. Because the drive shaft is wound one turn, the belt is wrapped around one layer, so the cumulative layer Number of revolutions

It is known that the aircraft accelerates the takeoff time on the 100m runway for about 2.6 seconds, the cumulative number of revolutions / 2.6 seconds = design revolutions / sec, the cumulative length of the drive belt under the cumulative number of revolutions is 100 meters, the rated number of revolutions of the selected motor is X rev / sec, the belt speed is adjusted to the design rotation number is Y rev / sec, the speed ratio is X rpm / Y rpm, as long as the motor provides Y rotation for 1 second by the pulley, the boost module can be 2.6 seconds Inside, the carrier aircraft was accelerated to a takeoff speed of 80 m/s on a 100 m runway. The beneficial effects of the present invention are that

1) The design is scientific and reasonable. The acceleration mode of the booster can be seen from the speed time curve. The speed is slower and faster, and the speed is accelerated. If the plane takes off on the 00 meter runway, it is 2.6 seconds. The take-off speed does not exceed 30 meters, and the take-off speed at the second second can reach the take-off speed requirement of 80 m/s. Since the energy is not burst-type release, the energy utilization rate can reach 98% or more, thanks to the boost of the present invention. The instrument is a clever use of pure mechanical principles, including speed, time, power and mechanical strength. All data parameters can be designed and calculated. According to the current state of the art, including power source, electronic controller and drive belt, it can help The pusher boosts the requirements of the various carrier aircraft currently known.

2) Highly humanized, the boosting process of the booster of the present invention has a slow initial speed and strong traction, and the entire acceleration process coincides with the acceleration characteristics of the aircraft at the airport, the acceleration is very human, and the pilot is propelling to take off. The process adapts quickly to the overload response and does not use a constant boosting speed like the traditional booster, causing the pilot to boost the instant coma that occurs during takeoff.

3) Small size, simple structure, less space, no restrictions on the length of the runway, and no arc limit. It can be used not only on the deck of the aircraft carrier, but also on the deck of the plane carrier. The slotting depth on the flight deck is no more than 50 cm, the width is no more than 100 cm, and the cross-sectional area is not more than 0.5 square meters. It can save a lot of space for the aircraft carrier. The space occupied by the main engine does not exceed 30 square meters, the total weight is less than 30 tons.

4) Energy saving, wide choice of power source, 6- 12 sets of 500-1000 kW electric motor or diesel engine for power, total power input power 6000KW, the lower the energy consumption, the higher the implementability.

5) Simple operation, intelligent one-button operation, manual or remote control operation, automatic shuttle boost and automatic return. There are many options for boosting speed. If the motor is controlled by inverter or governor, Adapt to the needs of various carrier aircraft including drones.

6) Simple structure, highly modular, easy to process, easy to transport, easy to install, easy to debug, easy to maintain and so on.

7) High energy utilization rate, no obvious friction and resistance in the whole system of the invention, the sliding lock assembly is small in size and light in weight. J is always in a low-resistance rolling state in the groove type track, and the belt is pushed back from the assisting module. The migration to the homing module is also in the low-resistance rolling contact state on the reversing roller, the guide roller and the intermediate roller, and the low-resistance bearing is used in the above rollers, especially the homing module is not required to provide any shuttle assembly. In the case of energy, the most scientific and reasonable reverse traction damping is provided, so the power consumption can be reduced to a minimum. Since the system switches between the proud part and the energy storage part through the clutch, the energy storage part refers to the motor pulley and the clutch. The active part, the work part refers to the passive part of the drive shaft, the drive belt and the shuttle assembly. After the work part is completed, the clutch is released and the energy storage part immediately enters the energy storage state, so the whole system is always in the best energy saving. State, so the energy utilization rate of the system of the present invention is above 98%.

1 is a schematic structural diagram of a booster system composed of a single boost module and a single homing module;

2 is a schematic structural view of a booster system composed of a multi-boost module and a single homing module; FIG. 3 is a schematic cross-sectional view of a boost module or a homing module; FIG. 4 is a single boost module and a single homing module drive shaft pass Schematic diagram of the connection of the drive belt and the shuttle assembly;

Figure 5 is a schematic diagram of the connection structure between the multi-boost module drive shaft and the single-homing module drive shaft and the shuttle assembly; Figure 6 is the velocity Z-time curve of the steam catapult or the electromagnetic catapult, and the interview below the curve is a power consumption diagram ; Figure 7 is a velocity time curve of the belt carrier booster system. The area under the curve is a schematic diagram of power consumption.

DESCRIPTION OF REFERENCE NUMERALS: base 1, T-shaped case 2, clutch 3, pulley 4, brake 5, transmission belt pressing plate 6, grooved rail 7, combined roller 8, bushing 9, shuttle 10, shuttle frame 1 1. A roller 12, a drive shaft 13, a motor 14, a drive belt 15, a guide roller 16, a counter, a racetrack bracket 18, an intermediate idler 19, and a balance roller 20.

Refer to the Pfi diagram for the belt carrier-based booster system and the distributed energy storage concentrated work method for the following detailed

As shown in Figure 1-7, the booster system includes a boost module assembly, a homing module assembly, a runway module, a shuttle module, and a controller module, wherein: the boost module assembly is composed of more than one boost module. Arranged under the runway module, the boosting module comprises a T-shaped box, a transmission belt 15, a motor, a transmission shaft, a clutch, a brake and a base, wherein the bottom of the T-shaped box 2 is fixed in the middle of the base 1, and the motor 14 is fixed on the base 1. Located on both sides of the T-shaped housing 2, the transmission shaft 13 is inserted through the bearing housing in the middle of the T-shaped housing 2, and the two ends of the transmission shaft 13 are respectively provided with a clutch 3 and a brake 5, a passive portion of the clutch 3 and a brake 5 The driving shaft is fixed, the active part of the clutch 3 is connected with the pulley 4, and the pulley 4 is connected with the transmission shaft 13 through a bearing. The outer edge of the pulley 4 is connected to the pulley of the shaft end of the motor 14 through the belt, and the end of the folded belt 15 passes through the belt pressing plate. 6 is fixed on the transmission shaft 13 located in the middle of the T-shaped box 2, the intermediate part of the folded belt 15 is connected with the shuttle assembly, and the upper part of the T-shaped box 2 is provided with a guiding roller 16, which is guided 16 is connected to the meter 17 , and the belt 15 passes through between the guide roller 16 and the meter 17 . The upper ends of the T-box 2 are connected to the track module, and the top of the T-box 2 is provided with a groove track. 7. The trough track 7 is connected in series with the trough track on the top of the runway module; the homing module assembly is composed of more than one homing module arranged in the runway module - F side, the structure is the same as the boost module, and the homing module includes T a box body 2, a belt 15 motor 14, a drive shaft 13, a clutch 3, a brake 5 and a base 1, wherein the bottom of the T-shaped box 2 is fixed in the middle of the base 1, and the motor 14 is fixed on the base 1 in the T-box 2 On both sides, the transmission shaft 13 penetrates through the bearing housing in the T-shaped housing 2 In the middle, the two ends of the transmission shaft 13 are respectively provided with a clutch 3 and a brake 5, the passive portion of the clutch 3 and the brake 5 are fixed to the transmission shaft 13, the active portion of the clutch 3 is connected to the pulley 4, and the pulley 4 is connected to the transmission shaft 13 through a bearing. The outer circumference of the pulley 4 is connected to the pulley of the motor at the 4-axis end by a belt. The two ends of the folded belt 15 are fixed to the transmission shaft 3 in the middle of the T-shaped box 2 through the transmission belt pressing plate 20, and the belt 15 is folded in the middle. The portion is connected to the shuttle assembly. The upper portion of the T-shaped case 2 is provided with a guide roller 16, and the guide roller 16 is connected with a meter 17 which passes through between the guide roller 16 and the meter 17 and the T-box Both ends of the upper part of the body 2 are connected with the runway module, and the top of the T-shaped box 2 is provided with a trough type track 7, which is connected in series with the trough type track at the top of the runway module; the runway module is composed of the runway bracket 18, It is composed of a roller 14, an intermediate roller 22 and a grooved track 7, and the raceway bracket 18 is connected between the boosting module and the homing module and at both ends thereof, and the shuttle module constitutes a linear sliding track, and the reverse roller 14 is disposed on the runway. Module Portion of the drive belt 15 provides a guide, disposed intermediate the drive roller 22 with the guide 15 provided in the middle of the runway held Torr module is;

The shuttle module is disposed in the channel rail 7, and the structure is composed of the shuttle 10, the shuttle frame 11, the roller 12, the belt roller 8 and the balance roller 20, and the belt roller 8 is disposed on the shuttle frame U. On the outer side of the both ends, the balance roller 20 is disposed between the belt rollers 8, and the belt roller 8 and the balance roller 20 are composed of a roller shaft and a sleeve 9, and both ends of the roller shaft pass through the two downwards of the shuttle frame 11 The flange 12 is outwardly extended, and the roller 12 is disposed at both ends of the roller shaft to be in rolling connection with the groove on both sides of the groove rail 7, and the sleeve 9 is disposed in the middle of the roller shaft at two downward flanges of the shuttle frame 11 Between the intermediate position of the folded-back belt 15 connected to the booster module drive shaft 13, the intermediate roller 19, the end reverse roller 14 and the upper portion of the parallel roller 8 in the middle of the track module are sleeved on the balance roller The sleeve 9 of 20 is connected; the intermediate position of the folding belt 15 on the homing module drive shaft 13 is connected from the intermediate roller 22, the end reverse roller 14 and the end of the shuttle frame 11 in the middle of the track module. The upper portion of the roller 8 is passed over the sleeve 9 of the balance roller 20;

The controller module is composed of a strong electric control switch, a weak electric control switch and a metering device 17, and the high electric control switch only performs switching control on the motor 14 of the boosting module and the motor 14 of the homing module, and the weak electric control switch only applies to the clutch 3 The switch 5 is controlled by the brake 5, and the meter 17 disposed on the boosting module and the homing module guide roller 16 accurately detects the moving distance of the belt 15 to provide a precise switching signal for the weak electric control switch.

Motors, clutches, brakes, high-power control switches, weak current control switches, and metering units are all commercially available general-purpose electromechanical products. Clutches and brakes include electromagnetic or start-up mode. Set the length of the booster runway to be 100 meters equal to the length of the belt winding. As long as the time to wind the belt with the same length of the runway on the drive shaft is set to 2.6 seconds, the carrier aircraft can be in the time of 26 seconds. After running 100 meters to boost the runway, the carrier aircraft can smoothly start from the boosting runway - I calculate the following formula - the carrier aircraft must get 30m / s ² acceleration on the 100m runway to take off, the aircraft takeoff speed And the acceleration motion time is calculated as follows:

V :: ^ϊαϊ. :: 200 x 30 « 77.46m / s (ϊ)

i - lL i a - 200/30 ^ 25%s (2) Length of the belt = length of the runway, L = sum of the lengths of the belts wound around the drive shaft, length of the belt -

D LH-L24 ... LN)=100 m= Length of boosting runway (3) Formula for calculating the length of each belt driven on the drive shaft:

Li-3.14(D+2dn) , 1, 2, 3'ι (4) where D is the diameter of the drive shaft; (^ the thickness of the drive belt; the number of layers of the drive belt

L 100-3.14[(D+2di)+(D+2d2)+(D+2d3)+,,.(D+2dn);| (5) The length of the length of the transmission belt is known to be 100 meters. Ignore the density of the belt winding, the diameter of the drive shaft is 0, the value of the thickness d of the belt is substituted into the formula (4) to calculate the length of each belt, and then the length of each belt is accumulated to nearly 100 meters, the layer of the last layer The number is set to the number of shaft revolutions required to wind the 100-meter drive belt. Because the drive shaft is wound one turn per revolution, the cumulative number of layers is ^ rotation number. It is known that the aircraft accelerates the take-off time on the 100-meter runway. Seconds, cumulative axis revolutions / 2.6 seconds design revolutions / sec, the cumulative length of the drive belt under the cumulative number of revolutions is 100 meters, the rated number of revolutions of the selected motor is X rev / sec, the design of the number of revolutions through the belt shift is Y rev / sec, the speed ratio X turn / Y turn, as long as the motor provides the Y-turn for 1 second speed through the pulley, the booster module can accelerate the carrier aircraft on the 100-meter runway in 2.6 seconds. Takeoff speed of 80 m / s. Calculation of the total power of the boosting module, calculation of the breaking strength of the transmission belt: Calculation of the total power of the boosting module, including the inverse push algorithm and the experimental push algorithm, wherein the reverse push algorithm is: According to the published maximum power of the world The power of the steam catapult is 60,000 kilowatts, its real Only 4%, 64000 kW*4% 2560 kW, based on the actual effective work 3000 kW, each booster module is designed according to two motors, each motor has a power of 500 kW, a total of 1000 kW, the total power of the three booster modules is 3000 kW, and the tonnage of the anti-submarine or early warning aircraft is 60 tons. The boosting mass per kilowatt is 60,000 kg / 3000 kW and 20 kg, that is, the object can be 20 kg per kilowatt of motor. The metering speed is accelerated to a takeoff speed of 80 m/s in 2.6 seconds; since the power used by the system of the present invention can be increased by increasing the power of the motor or increasing the number of boosting modules, it has great flexibility; Because the various various boosting methods include the various parameters of the carrier aircraft, they are all military: dense, difficult for the people to obtain, and the intelligence is obtained through experiments. The method is to design a small belt carrier; Length 100 meters, select motor power 1 kW, run in 2.6 seconds [the quality of the road after the help of the base, base kilograms Z kW, 60000 kg / base = design power; according to the complement method verification The feasibility of the Ming, the full weight of the 歼15 is known to be 33 tons, the unloaded weight is 27 tons, 歼15 can take off on the slide runway under no-load conditions, and can not take off at full load, through this The inductive boosting system of the invention performs the boosting replenishment, and accelerates the lifting force of 6 tons of mass to a speed of 80 m/s to the crucible 15, and the crucible 15 can be fully loaded, according to the above base = kg / kW formula, calculate 6000 Kg/Base = the power required to boost a full load of 歼15.

The design steps are as follows: The carrier aircraft must obtain an acceleration of 30m I s ² on the 100m runway to take off. The formula for calculating the takeoff speed and acceleration motion time of the aircraft is as follows:

V = ΐαί = 200 x 30 « ΊΊ A6m i s (1)

t - ^! 2L I a - /200 / 30 « 2.58s (2) Length of the belt length of the belt, L = sum of the lengths of the belts wound on the shaft, the length of the belt:

L=(L〗+L2"!"... LN 00 m = length of the booster runway (3) Formula for calculating the length of each drive belt of the drive shaft:

Li-3.14(D+2dn) (4) Where D is the diameter of the drive shaft, d = the thickness of the drive belt, ιι = the number of layers of the drive belt;

Know the length of the booster runway = the length of the drive belt is 100 m, ignoring the density of the drive belt winding, setting the diameter of the drive shaft D-axis m; the thickness of the drive belt d).02 m; the winding length of each drive belt

(m) Li=3, 14 (D-i--2dn); Calculate the length of each belt according to formula (4):

L 1-3.14(0.3+0.04* 1)=3.14-0.34-1.676 1 ,676

1,2-3.14(0.3+0, 04*2)^3.14*0,38-1.〗 932 2,8692

L3-3.14(0.3+0.04*3)-3.14-0.42- 1.3188 4.188

L4-3.14(0.3+0.04*4)-3.14-0.46- 1.4444 5.6324

L5=3.14(0.3+0,04*5)=3.14 *0.5- 1.57 7.2024

L6-3.14(0.3+0.04*6)-3.14*0,54=1.6956 8,898

L7-3.14(0.3+0.04*7)-3.14*0.58-1.8212 10,7192

L8-3.14(0.3+0.04*8)- 3, 14*0.72- 2.2608 12,98

L9-3.14(0.3+0.04*9)-3.14 *0.66 -2.0724 15,0524

L10=3, 14(0,3+0,04*1 ())-3, 14*0.7- 2.198 17,2504

L11-3.14(0.3+0,04* 11 )-3, 14*0.74- 2,3236 19.574

L12=3, 14(0,3+0.04*12)= 3.14*0,78=2,4492 22,0232

L13 : 3.14(034-0.04* 13)- 3,14* 0.82-2,5748 24,6016

L14-3.14(0.3+01)4* 14)- 3, 14*0.86=2,7 27.3016

L15-3.14(0.3+0.04*15)- 3.14*0.9- 2.826 30.2532

L16-3.14(0.3+0.04*16)- 3, 14* 0,94=2,9516 33,2048

L17-3.14(0.3+0.04* 17)- 3.14*0.98-3,0772 36.282

L 18-3.14(0.3+0.04* 18)- 3.14* 1,02- 3.2028 39,4848

L19: 3, 14(0.3-f0.04*19)- 3.14* 1.06-3.3284 42.8132

L2 3, 14(0,3+0.04*20)= 3.14* 1,1 =3,454 46.2672 L21- : 3.14 (0.3+0,04*21)= :3,14*1.14=3,5796 49.8468

L30- :3,14(0,3+0.04*30)= :3.14*1,5=4,71 87.754

L31- : 3,14 (0,3+0.04*31)= :3.14* 1.54-4.8356 92.5896

1,32- :3,14(0,3+0.04*32)= :3.14*1,58=4.9612 97.5508

1-33=: 3.14 (0.3+0.04*33 6.14*1,6-5,0868 102,6376

The length of each layer of the belt is placed in the speed time curve coordinates to make a speed time curve, as shown in the figure;

According to the calculation: the total length of the 33rd layer belt is L LI4 L2- L21 02.6 meters, the outermost belt belt diameter is L6 meters, and the maximum diameter of the belt pulley is 2 meters. The width of the belt disc depends on the width of the belt.

It is known that the aircraft accelerates the takeoff time on the 100m runway for about 2.5 seconds, and the rope is 33/25 13 laps per second. The cumulative length of the drive belt on the 33th floor is 】02 meters. If the motor is used for power supply, the rated speed of the motor is 1500 rpm. / Minute, the speed per second is 25 rpm, the speed is adjusted to 13 rev / sec, the gear ratio is 25/13, and the speed of the drive shaft is 13 rev / sec to achieve the take-off speed of the carrier. It can be seen from the above calculation that the first second speed is about 24 meters, the second second is about 70 meters, the second is 102 meters, the belt is wound around the drive shaft for 44 times, and the airplane runs in 2.5 seconds. Throughout the runway, the acceleration of the aircraft on the booster runway is fully synchronized with the winding speed of the drive belt on the reel, and the acceleration mode is very user-friendly, without causing damage to the driver and the aircraft.

Selection of transmission belt, nylon base belt, total thickness 6-10 cm, width 50-100cm, tensile strength The degree is 100-200 tons. If the carbon fiber composite base tape with the same cross-sectional area is selected, the breaking strength can reach 250-300 tons. The Su-33 full load is 33 tons, with a safety factor of 3-10 times, boosting the runway on the deck. The slot width is only 0.6-1.2 meters and the depth is 0.30 0.50 meters. If the power is selected as a diesel engine, the diesel engine provides additional uniform acceleration by adjusting the throttle, and the take-off speed of the carrier aircraft can also float up and down 20-50%. The carrier-assisted steps are as follows -

1) The shuttle is positioned at the starting point of the runway, connected to the front landing gear of the carrier by the hooking device, and the engine is refueled, waiting for the take-off command;

2) The take-off command is issued, the booster module clutch is engaged, the whole energy of the motor is transmitted to the drive shaft through the clutch, the drive shaft rotates to wrap the drive belt, the drive belt transmits the shaft power to the shuttle, and the shuttle pulls the carrier aircraft to start. The number of layers of the drive belt wound on the drive shaft is increased, the traction speed is getting faster and faster, the shuttle moves to the end of the runway, and the carrier aircraft reaches the takeoff speed and takes off smoothly;

3) When the shuttle is about to reach the end of the runway, the meter accurately measures the moving length of the belt. The preset length of the i-meter is equal to the length of the runway. When the set length of the meter is equal to the length of the belt movement, The rice controller sends a brake signal to the control module, the control module controls the clutch release on the boost module, stops the transmission power, and the brakes on the boost module and the homing module simultaneously brake, the booster module and the drive shaft on the homing module At the same time, the rotation is stopped, and the shuttle is accurately positioned at the end of the runway;

4) After the shuttle stops at the end of the runway, the delay is 1-3 seconds. The brakes on the boosting module and the homing module are simultaneously released. The clutch on the homing module is engaged, and the transmission belt wound on the drive shaft of the boosting module is reversed. Winding on the drive shaft of the homing module, the shuttle moves from the end of the runway to the start of the runway, and the meter re-meters the transfer length of the drive belt. When the transfer length of the drive belt reaches the set value, the meter sends a brake signal to the control module. The control module controls the release of the clutch on the homing module, and the brakes on the boosting module and the homing module are simultaneously braked. The shuttle is accurately positioned at the starting point of the runway, and the carrier is not ready to take off.

Claims

claims

1. A belt-type carrier-based aircraft booster system, characterized in that the system includes a boost module assembly, a homing module assembly, a runway module, a shuttle module and a controller module, wherein: boost module assembly , the homing module assembly and the controller module are set at the bottom of the runway module, the shuttle module is set in the middle of the transmission belt, the transmission belt is set in the running module, the two ends of the transmission belt are respectively connected with the boost module assembly and the homing module assembly Connected, the boost module assembly and the return module assembly respectively transfer the traction kinetic energy to the shuttle module to make it eject or return to the position.

2. A belt-type carrier-based aircraft booster system according to claim i, characterized in that the boost module assembly is composed of more than one boost module arranged below the runway module, and the boost module includes a T-shaped Box, motor, transmission shaft, clutch, brake and base. The bottom of the T-shaped box is fixed to the middle of the base. The motor is fixed on the base and is located on both sides of the T-shaped box. The transmission shaft passes through the bearing seat and runs through the T-shaped box. In the middle of the body, clutches and brakes are provided at both ends of the transmission shaft. The passive part of the clutch and the brake are fixed to the transmission shaft. The active part of the clutch is connected to the pulley. The pulley is connected to the transmission shaft through the bearing. The outer circle of the pulley is connected to the transmission shaft through the belt. The pulley at the end of the motor shaft is connected. Both ends of the folded transmission belt are fixed on the transmission shaft located in the middle of the T-shaped box through the belt pressure plate. The middle part of the folded transmission belt is connected to the shuttle assembly. The upper part of the T-shaped box is provided with a guide roller, a meter counter is connected to the guide roller, the transmission belt passes through the middle of the guide roller and the meter counter, the two ends of the upper part of the T-shaped box are connected to the track module, and the top of the T-shaped box is equipped with a scull-shaped track. The track is connected in series with the grooved track on the top of the runway module; the homing module assembly is composed of more than one homing module arrayed on the -F side of the runway module. The homing module includes a τ-shaped box, a motor, a transmission shaft, a clutch, The brake and base are fixed at the bottom of the Φ τ-shaped box and the middle of the base. The motor is fixed on the base and located on both sides of the τ-shaped box. The transmission shaft passes through the bearing seat in the middle of the τ-shaped box. Both ends of the transmission shaft There are clutches and brakes respectively. The passive part of the clutch and the brake are fixed to the transmission shaft. The active part of the clutch is connected to the pulley. The pulley is connected to the transmission shaft through the bearing. The outer circle of the pulley is connected to the pulley at the end of the motor shaft through the belt. After folding, Both ends of the transmission belt are fixed on the transmission shaft located in the middle of the τ-shaped box through the belt pressure plate. The folded middle part of the transmission belt is connected to the shuttle assembly. The upper part of the T-shaped box is provided with a guide roller, and a th meter is connected to the guide roller. The transmission belt passes between the guide roller and the meter counter. The two ends of the upper part of the τ-shaped box are connected to the runway module. The top of the τ-shaped box is provided with a grooved track, and the grooved track is connected to the grooved track on the top of the runway module. Series connection; The runway module is composed of a runway bracket, a reverse roller, an intermediate roller and a trough track. The runway bracket is connected It is connected between the boost module and the return module and at both ends to form a linear sliding track for the shuttle module. The reverse roller is set at the end of the track module to provide transmission guidance for the transmission belt. The middle roller is set in the middle of the track module. The transmission belt provides guide lifting support;

The shuttle module is set in the grooved track. Its structure is composed of a shuttle, a shuttle frame, a roller, a belt roller and a balance roller. The belt roller is set on the outside of both ends of the shuttle frame, and the balance roller is set on the Between the parallel belt rollers, the parallel belt rollers and balance rollers are composed of roller shafts and bushings. The two ends of the roller shafts extend outwards without flanging through the two directions of the shuttle frame. The rollers are set on both sides of the roller shafts. The ends are rollingly connected to the grooves on both sides of the grooved track, and the bushing is set in the middle of the roller shaft between the two downward flanges of the shuttle frame; it is connected to the middle position of the folded transmission belt on the drive shaft of the booster module. Pass through the upper part of the middle idler roller, the end reverse roller and the belt roller in the middle of the runway module and connect it to the bushing of the balance roller; from the middle position of the folded transmission belt connected to the transmission shaft of the homing module, from the runway module The middle intermediate roller, the end reverse roller and the upper part of the parallel roller at the end of the shuttle frame pass through and are connected to the shaft sleeve of the balance roller; the controller module is controlled by a strong current control switch and a weak current control switch. It is composed of a meter counter. The strong current control switch only controls the switching of the motor of the boost module and the motor of the homing module. The weak current control switch only controls the switching of the clutch and brake. It is set in the guide of the boost module and homing module. The -H-· meter on the roller can accurately detect the moving distance of the transmission belt and provide accurate switching signals for weak current control switches.

3. A method of decentralized energy storage, centralized random boosting and power generation of the belt-type carrier-based aircraft booster system described in any one of claims 1-2, characterized in that it includes: hooking the aircraft to the shuttle;

Keep the clutch in a disengaged state, start the motor, so that the motor drives the flywheel to rotate; close the clutch, combine the flywheel with the transmission shaft and drive the transmission shaft to rotate; the rotation of the transmission shaft causes the transmission belt to wrap around the transmission shaft, The transmission belt simultaneously drives the shuttle to slide in the chute on the runway;

The aircraft is boosted to take-off speed while the shuttle slides in the chute on the runway.

4. The dispersed energy storage centralized random boosting method of the belt-type carrier-based aircraft booster system according to claim 3, characterized in that the method specifically includes: All carrier-based aircraft catapults must have powerful The energy storage system, based on the maximum carrier-based aircraft tonnage designed to be boosted by the boost module assembly, arranges one or more boost modules below the runway module, and each boost module Both ends of the transmission shaft on the block are connected to at least one motor through a clutch. In order to solve the problem of grid overload caused by excessive total load caused by all motors of the booster being started at the same time, the strong current control switch starts all the motors one by one to make them unloaded. Rotation disperses energy storage. After the motor is started, it also drives the pulley and the normally rotating part of the electromagnetic clutch to rotate for dispersed energy storage. The motors in all booster modules in the system convert electrical energy into kinetic energy during no-load rotation and store it dispersedly. , since the transmission shafts of all booster modules are connected to the shuttle module through transmission belts, and the shuttle module is in turn connected to the carrier-based aircraft, when the booster system requires huge kinetic energy to accelerate the carrier-based aircraft, weak current control The switch simultaneously sends power to the electromagnetic clutches on the transmission shafts of all boost modules. When the clutches are engaged, the transmission shaft instantly combines and absorbs the rated power of all boost module motors and the kinetic energy stored in idling through the clutch, and centrally applies it to the shuttle through the transmission belt. The centralized random power is completed on the module. The random power is to bind the boost speed of the shuttle assembly to the take-off speed of the carrier-based aircraft itself on the take-off runway. Also, because the transmission shaft is rotated by the diameter of the transmission shaft at the beginning of winding the transmission belt is the base number, so the transmission belt transmits power at low speed and high torque. As the number of winding layers increases, the winding speed of the transmission belt increases rapidly, so the boost acceleration generated by the transmission belt during the winding process is exactly the same as that of the carrier-based aircraft. The takeoff acceleration is consistent to achieve random boost; the boost speed is designed as follows:

Set the length of the boost runway to be equal to the length of the transmission belt winding to 100 meters. As long as the time for the transmission belt equal to the length of the runway to be wound on the transmission shaft is set to 2.6 seconds, the carrier-based aircraft can fly in 2.6 seconds. After running the 100-meter boost runway, the carrier-based aircraft can successfully take off from the boost runway. The calculation formula is as follows: The carrier-based aircraft must obtain an acceleration of 30m/ ^s2 on the 100-meter runway before it can take off. The aircraft's take-off speed is The calculation formula of acceleration motion time is as follows:

V - Ϊ^Ε 200 x 30 « 77.46m I s ( 1 )

ί = B / α 200 / 30 - 2 58Λ' (2)

The length of the transmission belt = the length of the runway, L = the sum of the lengths of each layer of transmission belts wrapped around the transmission shaft, the length of the transmission belt

L-(Ll+L2-i-— LN)-100 meters The length of the boost runway (3) The calculation formula for the length of each layer of transmission belts wrapped around the transmission shaft:

Li-3.14(D+2dn), i=l, 2, 3...! ! (4) Among them, D is the diameter of the transmission shaft; d=thickness of the transmission belt; ri=number of layers of the transmission belt;

L-100-3.14[(D+2dl)+(D+2d2)-i-{D+2d3)+...(D+2dn)] (5:) It is known that the length of the boost runway and the length of the transmission belt are 100 meters. The density of the transmission belt winding is ignored. The diameter of the transmission shaft is 0. The values of the thickness of the transmission belt d are substituted into the formula (4) to calculate the length of each layer of transmission belts. Then the length of each layer of transmission belts is calculated. When the length is nearly 100 meters, set the number of layers of the last layer to the number of shaft revolutions required to wrap a 100-meter transmission belt. Because each time the transmission shaft rotates, the transmission belt is wrapped with one layer, so the cumulative number of layers is the number of shaft revolutions;

It is known that the acceleration take-off time of an aircraft on a 100-meter runway is about 2.6 seconds. The cumulative shaft revolutions / 2.6 seconds = the design revolutions / second. The cumulative length of the transmission belt under the cumulative shaft revolutions is 100 meters. The rated revolution of the selected motor is X revolutions/second, the belt speed is adjusted to the designed number of revolutions Y revolutions/second, the gear ratio = Within seconds, the carrier-based aircraft will be boosted and accelerated to a take-off speed of 80 meters/second on a 100-meter runway.

5. The shuttle end-point reverse traction damping method of the belt-type carrier-based aircraft booster system is characterized by connecting the transmission belts at both ends of the slide lock assembly to the transmission shafts of the boost module and the return module respectively, and boosting The length and speed of the transmission belt wrapped around the module transmission shaft are equal. A meter counter is used as a sensor to accurately detect the moving length of the transmission belt and accurately calculate the moving distance of the slide lock assembly. When the meter counter accurately detects the set slide lock assembly After reaching the moving distance, the control module accurately controls the brake on the drive shaft of the homing module. The J slide lock assembly moves to the end point of the runway module. The winding diameter of the drive belt wrapped around the drive shaft of the homing module is the smallest, so the system The power torque is the largest, and the transmission belt is used as the reverse braking medium to carry out power-free and most effective reverse traction on the shuttle assembly that moves to the end of the runway module, achieving precise point braking of the shuttle assembly at the end of the runway.