CN109229412B - Ejector - Google Patents
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- CN109229412B CN109229412B CN201810241500.2A CN201810241500A CN109229412B CN 109229412 B CN109229412 B CN 109229412B CN 201810241500 A CN201810241500 A CN 201810241500A CN 109229412 B CN109229412 B CN 109229412B
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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
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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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 relates to an ejector which is used for the ejection take-off of an aircraft carrier, the cold launching of a carrier rocket and the vertical launching system of various missiles. The invention firstly stores the mechanical energy emitted by the prime mover through the flywheel, and then drives the traction trolley to realize ejection by the variable-pitch screw rod rotating at the quasi-constant speed. When the sliding block on the traction trolley is inserted into the starting groove of the variable-pitch screw, the variable-pitch screw can complete the complete set of precise movement of ejection and brake parking with constant acceleration in one step through the spiral groove with the lifting change of the spiral lead angle and the ending groove; the multi-slide-block hydraulic balanced stress mechanism can simultaneously use a plurality of slide blocks in a variable-pitch spiral groove, and the problem that a single slide block cannot provide enough thrust is solved. The invention has the advantages of small power of the prime motor, light system weight, high efficiency, stable ejection acceleration, high ejection frequency, simple manufacturing process, low cost, strong electromagnetic strike resistance, simple maintenance and less maintenance personnel, and the comprehensive performance of the invention is superior to that of a steam ejector and an electromagnetic ejector.
Description
Technical Field
The invention relates to an ejector, which is suitable for the ejection take-off of an aircraft carrier, the cold launching of a carrier rocket and the vertical launching system of various missiles.
Background
As is known, the main advantage of taking off of the carrier-based aircraft by the catapult is that the carrier-based fighter can take off in full load, so that the combat radius and the combat capability of the carrier-based aircraft can be fully exerted.
The existing aircraft carrier catapult in service mainly has two forms of steam catapult and electromagnetic catapult.
The steam catapult is characterized in that water is burnt by a boiler to store high-temperature and high-pressure steam in a special high-pressure container, and then the high-pressure steam is converted into catapulting power by a special open cylinder and a piston; the electromagnetic ejection is to excite the stator of the linear motor by using the electric energy stored in the capacitor or the storage battery or the flywheel battery through a set of power electronic converter to drive the rotor of the linear motor to push the carrier-based aircraft to move.
The energy required for launching the carrier-based aircraft is not large, namely dozens of kWh of energy, but the power of the carrier-based aircraft is huge in less than 2 seconds, and at least hundreds of thousands of kW can be achieved. Therefore, the technical difficulty of catapult takeoff is how to obtain a power supply with such strong electric power in a very short time and how to convert and output such strong mechanical power, so that a carrier-based aircraft weighing tens of tons is accelerated from rest to a takeoff speed higher than the takeoff speed in a distance less than one hundred meters.
The catapult is divided according to the final power provider of the catapult, and can be divided into various types such as a pure mechanical type, a thermal engine type and an electric motor type.
The steam catapult and the internal combustion piston catapult are both in a thermal engine type, the electromagnetic catapult is in an electric motor type, and the spring catapult, the flywheel-steel wire and the like are in a mechanical type.
Although the steam ejector is the most practical ejector at present, the steam ejector is increasingly not seen due to the maintenance of high-pressure and high-temperature boilers, containers, pipelines, valves and open cylinders and the consumption of a large amount of purified water.
Electromagnetic ejection is an ejection mode which uses ultra-high power electrons to operate a linear motor for direct drive. For this purpose, corresponding very high-power supplies, electronic converter devices and linear motors must be provided, and the electrical energy stored in the high-power batteries is discharged rapidly by the motors in the form of mechanical kinetic energy. Electromagnetic ejection is a new technology, and has many advantages but obvious disadvantages. Firstly, the power of main electrical equipment of the device is the same as the maximum power at the moment of ejection, and the equipment has huge number of parts, components and wires, so that the reliability in wartime is difficult to guarantee; secondly, due to the structure, the armature of the linear motor cannot be shielded, and once the electromagnetic catapult is attacked by an electromagnetic pulse weapon, the standing horse can be completely paralyzed.
In order to replace a steam catapult, besides an electromagnetic catapult, people also propose a plurality of novel catapults, and the typical CN103121509B spiral flywheel catapult invented by Huangshang and the application thereof, a variable-frequency screw catapult invented by Weibuqin for 201210527653.6 aircraft carriers and a takeoff catapult invented by Zhang-Tao for 210420517797.8 spiral aircraft carriers are provided.
The catapult of the Huangshang CN103121509B is of a mechanical type, and has the advantages that mechanical kinetic energy stored in a flywheel is directly wound on a traction rope through a reducing rope drum to drag a carrier-based aircraft, the system structure is simpler, and the energy conversion efficiency is high; the defects are that the moment of inertia of the reducing rope drum is huge, a powerful quick clutch is needed for combining the reducing rope drum with the flywheel, and a powerful brake is needed for quickly braking the reducing rope drum and the traction tackle after ejection is finished.
The catapult of Wei Burqing 201210527653.6 belongs to motor type in nature, and the effect of screw rod slider mechanism is only to change rotary motion into linear motion, and final catapult power source is the huge rotating electrical machines of power. The rotating motor has mature manufacturing process and is easy to shield an electromagnetic loop, and the defect is that a set of power supply and power electronic converter with huge power in a short time is needed as the existing electromagnetic catapult. The solution is not as advantageous as the existing electromagnetic catapults using linear motors, since the rotational inertia of the screw will add extra load to the motor's drag.
The ejector of 210420517797.8 by zhang tao is also of an electric motor type, the function of the screw with variable pitch is only the conversion of rotary motion and linear motion, and the 'engine requiring strong torque' is used as the power source, and the proposal is not essentially different from the ejection mechanism of 201210527653.6 of Wei Bo Fang.
Disclosure of Invention
The invention provides an ejector, which aims to solve the defects of the prior art, and adopts a prime mover with lower power as power, energy is accumulated through a flywheel, then the rotary motion of a variable-pitch screw rod linked with the flywheel is directly converted into the linear motion of a traction trolley through the combined action of the variable-pitch screw rod and a telescopic slide block on the traction trolley which can only do linear motion along a track, the traction trolley accelerates a shipboard aircraft to a specified take-off speed at a stable acceleration by virtue of the change of a helix angle beta of a thread groove of the variable-pitch screw rod, then the traction trolley decelerates rapidly and breaks away from the shipboard aircraft, the telescopic slide block breaks away from the variable-pitch screw rod after the traction trolley stops, and a resetting device on the traction trolley can drive the traction trolley to automatically move backwards and return to the initial position before ejection again to prepare for next ejection. The energy required at the ejection moment of the ejector mainly comes from the kinetic energy stored by the flywheel and the variable-pitch screw, so the ejector belongs to a mechanical ejector.
The invention is realized by adopting the following technical scheme:
an ejector comprises a variable-pitch screw, a traction trolley and a power driving device for driving the variable-pitch screw to rotate; wherein the content of the first and second substances,
the variable-pitch screw is of a cylindrical structure, the kinetic energy stored during normal work can reach more than 5 times of the kinetic energy required by an ejected object, two ends of the variable-pitch screw are movably mounted, a starting groove, a spiral groove and an ending groove are sequentially formed in the outer circle of the variable-pitch screw along the axial direction, the starting groove and the ending groove are both circular grooves, the starting groove is an incomplete circular groove with the length less than one circle, the ending groove is a complete circular groove, an opening is formed at the joint of the ending groove and the spiral groove, the spiral groove starts from one end of the starting groove, the spiral lead angle beta gradually increases from zero degree, the spiral lead angle beta gradually decreases to zero after reaching the highest speed point, and the starting groove and the ending groove are in smooth transition with the variable-pitch spiral groove;
the traction trolley is characterized in that a traction hook is arranged above the traction trolley, at least one telescopic cylinder is arranged below the traction trolley, a piston in each telescopic cylinder is connected with one end of one telescopic sliding block, the other end of each telescopic sliding block extends out of each telescopic cylinder, each telescopic sliding block can slide up and down in each telescopic cylinder, one end of each telescopic sliding block extending out of each telescopic cylinder is inserted into a thread groove of each variable-pitch screw, and when the variable-pitch screws rotate, the traction hooks above the traction trolley and the traction trolley are driven to move linearly along the axial direction of each variable-pitch screw through each telescopic sliding block.
The power driving device comprises a prime motor arranged at any end of a variable pitch screw, an output shaft of the prime motor is connected with an input end of a hydraulic torque converter, an output end of the hydraulic torque converter is connected with an input end of a speed changer, and an output end of the speed changer drives the variable pitch screw to rotate;
or the power driving device comprises a motor arranged at any end of the variable pitch screw, an output shaft of the motor drives the variable pitch screw to rotate through a gear reducer, and the gear reducer comprises a pinion arranged at the output shaft of the motor and a bull gear arranged at the input end of the variable pitch screw;
or the power driving device comprises a motor arranged on the inner side of any one end of the variable pitch screw, the inner side of the variable pitch screw is provided with an inner gear ring, and an output shaft of the motor drives the variable pitch screw to rotate through a quasi-planetary gear formed by a sun gear pinion, a planetary gear bull gear and the inner gear ring.
The invention is further improved in that the output end of the speed changer is also provided with a flywheel for making up the deficiency of energy storage of the variable-pitch screw.
The invention has the further improvement that the spiral groove is divided into an acceleration section and a deceleration section, the rotating speed of the variable pitch screw in the ejection process is set to be n, the diameter of the variable pitch screw is set to be D, and the length of the acceleration section is set to be L1The length of the deceleration section is L2Acceleration of the acceleration section is a1Acceleration of the deceleration section is a2The displacement of the tractor is s, the helix angle of the acceleration section
At the end of the acceleration section, s1＝L1Angle of helix beta1To a maximum value betaM，
The speed of the tractor reaches a maximum value VT，VTN pi D tg beta M, lead angle of the deceleration section
At the end of the acceleration section s2＝L1+L2Angle of helix beta2At 0 deg., the speed of the tractor is reduced to zero and the advance is stopped.
The invention further improves that when the ejector is used as an aircraft carrier catapult, the catapult is arranged in a catapult ground groove below a deck, an aircraft carrier detachable deck is arranged above the catapult ground groove, a slit is arranged on the aircraft carrier detachable deck, two sides in the catapult ground groove are provided with tracks, wheels below a traction trolley are arranged in the tracks, a traction hook extends out of the slit on the aircraft carrier detachable deck to the upper side of the deck and is used for being connected with a catapult rod of a carrier-based aircraft, and two sides of a variable-pitch screw rod are provided with auxiliary support wheels.
The invention is further improved in that a lubricating oil spraying device is arranged on the traction trolley and is used for spraying lubricating oil to the spiral groove and the telescopic sliding block for lubrication in the advancing process of the traction trolley.
The ejector is further improved in that the ejector also comprises a multi-slide-block hydraulic automatic balancing stress mechanism arranged below the traction trolley, and the ejector comprises a group of acceleration buffer hydraulic cylinders, a group of deceleration buffer hydraulic cylinders and an air bag type energy accumulator, wherein each group of buffer hydraulic cylinders comprises a group of one-way piston oil cylinders, pistons arranged in the one-way piston oil cylinders, and push rods, one ends of the push rods are connected with the pistons, the other ends of the push rods extend out of the one-way piston oil cylinders, all the acceleration buffer hydraulic cylinders and the deceleration buffer hydraulic cylinders are communicated with the air bag type energy accumulator through hydraulic pipelines, the air bag type energy accumulator provides high-pressure hydraulic oil, and each one-way piston oil cylinder automatically adjusts the position of the telescopic slide block relative to the traction trolley in the advancing direction through the push rods so as to adapt to the change of the helix angle beta of the spiral groove and balance the acting force borne by each telescopic slide block.
The invention has the further improvement that the thread grooves on the variable-pitch screw are multi-thread threads which are uniformly distributed, and the traction trolley is provided with a plurality of groups of telescopic slide blocks so as to improve the stress condition of the variable-pitch screw; each screw groove in the multi-start thread is connected with one end of an independent initial groove, the initial grooves are not communicated with each other but are the same in the axial position of the variable-pitch screw, the lifting rule of the helix angle of each screw groove is the same and finally the screw grooves enter the same ending groove, and the ending groove and each screw groove are provided with an independent opening at the joint.
The catapult is further improved in that the catapult also comprises a reset device arranged below the traction trolley, wherein the reset device comprises a power supply, a controller, a reset motor, a gear and a rack, a guide groove on the traction trolley is clamped between rails on two sides of a trench of the catapult, a gap is reserved between the guide groove and the rails, and the traction trolley can move back and forth along the rails; the rack is arranged in parallel with the track and is arranged on two sides of the ground groove of the ejector; the gear is arranged on an output shaft of the reset motor; when the driving trolley moves forward, the controller does not excite the reset motor, the gear can freely rotate along with the output shaft of the reset motor, and after one-time ejection is completed, the controller of the reset device excites the reset motor and drives the gear to reversely rotate through the output shaft, so that the traction trolley automatically returns to the starting position.
The invention has the further improvement that the front surface and the rear surface of the telescopic sliding block, which are contacted with the thread groove, are cambered surfaces, and the bending radius of the cambered surfaces is close to but not larger than the minimum bending radius of the two contact surfaces of the thread groove as much as possible; the telescopic sliding block can rotate the telescopic cylinder at a limited rotation angle along the axis of the telescopic sliding block, the limited rotation angle starts from zero degree, and the maximum rotation angle is larger than the maximum helix angle of the spiral groove.
The invention has the following beneficial technical effects:
the invention can ensure that the telescopic sliding block can complete the complex accurate movement of constant acceleration accelerated ejection and deceleration braking parking in one go after inserting the variable-pitch screw rod rotating at a constant speed through the lifting change of the spiral angle of the spiral groove and the special starting groove and finishing groove. In addition, the multi-slider hydraulic balanced stress mechanism can simultaneously use a plurality of sliders to move in a variable-pitch spiral groove, so that the problem that a single slider cannot provide enough thrust is solved.
In summary, the present invention has the following distinct technical advantages over other known ejectors:
1. the device is free of seawater desalination equipment, a water storage tank, a high-pressure water pump, a boiler, an exhaust valve safety valve and other high-pressure high-temperature equipment which are necessarily required by a steam catapult, and also free of forced energy storage devices, ultrahigh-power controllers, ultrahigh-power linear motors and other high-difficulty complex equipment which are required by electromagnetic catapults;
2. the whole system has no exposed circuit, can perform good electromagnetic shielding and can withstand strong electromagnetic pulse attack.
3. The acceleration is stable in the ejection process, and the shipboard aircraft body and the pilot cannot be injured.
4. The catapulting preparation time is short, the catapulting frequency is high, and various carrier-based aircrafts with different weights can be catapulted;
5. the telescopic sliding block has small volume, light weight and quick action, and the power for controlling the telescopic sliding block to stretch is small.
6. The energy form conversion is less, and the energy efficiency of the system is high.
7. The pure mechanical device has strong damage resistance and good maintainability.
8. Small volume and light weight. The whole system can be intensively arranged in the grooves of the ejectors, does not occupy other spaces of an aircraft carrier, and has the total weight of about 300 t.
9. The manufacturing process is mature, the manufacturing cost is low, noble metals and special materials are not used, and the manufacturing cost is far lower than that of a steam catapult and an electromagnetic catapult.
10. The whole catapult has the advantages of small quantity of parts, small motive power, high reliability, simple maintenance and operation and few maintenance personnel.
11. The catapult can be used for cold launching of a carrier rocket and vertical launching of a tactical missile besides catapult of an aircraft carrier.
Drawings
FIG. 1 is a schematic view of an overall construction of the present invention;
FIG. 2 is a schematic view of a variable pitch screw;
FIG. 3 is a schematic longitudinal section of the wagon;
FIG. 4 is a transverse schematic view of the wagon;
FIG. 5 is a schematic view of an overall construction of the present invention using an electric motor as the prime mover;
FIG. 6 is a schematic view of a multi-telescopic-slider hydraulic automatic-balancing buffering mechanism in an initial position;
FIG. 7 is a schematic diagram of the operation of the multi-telescopic-slider hydraulic automatic balancing and buffering device at the position of an acceleration section;
FIG. 8 is a schematic diagram of the operation of the multi-telescopic-slider hydraulic automatic balancing buffer device at the position of the deceleration section;
FIG. 9 is a schematic view of the shape of the start groove of the thread groove of a variable pitch screw;
FIG. 10 is a schematic view of the shape of the thread groove ending groove of the variable pitch screw;
FIG. 11 is a schematic view of an ejection device with a motor and speed reducer built into a variable pitch screw;
FIG. 12 is a schematic view of a return device for the wagon;
FIG. 13 is a graph showing the speed versus distance of the wagon during ejection;
FIG. 14 is a graph showing the acceleration of the wagon versus distance during the launch;
figure 15 is a schematic view of the invention for cold launch of a launch vehicle.
In the figure: 1-a prime mover, 2-a hydraulic torque converter, 3-a speed changer, 4-a flywheel, 5-a pinion, 6-a telescopic slide block, 7-a variable pitch screw rod, 8-a spiral groove, 10-a first bearing, 11-a traction trolley, 12-a detachable deck of a aircraft carrier, 13-an auxiliary supporting wheel, 14-a bull gear, 15-a second bearing, 16-a third bearing, 17-a track, 18-a wheel, 19-a deck, 20-a traction hook, 21-a motor, 32-a starting groove, 33-a finishing groove, 34-a spring, 35-a telescopic cylinder, 36-a deceleration buffer hydraulic cylinder, 37-a guide groove, 38-an acceleration buffer hydraulic cylinder, 39-a push rod, 40-a piston, 41-a hydraulic pipeline and 42-high-pressure hydraulic oil, 43-high-pressure air bag, 44-high-pressure air, 45-air bag type energy accumulator, 46-carrier aircraft, 47-ejection rod, 48-ejector ground groove, 49-opening, 50-slot, 51-one-way piston oil cylinder, 52-steel cylinder, 53-internal gear ring, 55-output shaft, 56-reset motor, 57-movable well cover, 58-gear, 59-rack, 60-carrier rocket and 61-wellhead.
Detailed Description
The invention is further described below with reference to the figures and examples.
As shown in fig. 1 to 15, the catapult provided by the invention is mainly used for catapult take-off of aircraft carrier and cold launching of carrier rockets and vertical launching systems of various missiles, and mainly comprises a prime mover 1, a speed changer 3, a flywheel 4, a variable pitch screw 7, a telescopic slide block 6, a traction trolley 11 and a track 17, wherein except that a towing hook 20 at the top of the traction trolley 11 extends out of an aircraft carrier detachable deck 12 from a slit 50, the rest is arranged in a catapult ground groove 48 below the aircraft carrier detachable deck 12 of a take-off runway; the prime mover 1 drives the flywheel 4 and the variable pitch screw 7 to rotate in an accelerating way through the speed changer 3, and the output end of the speed changer 3 is provided with a third bearing 16; the flywheel 4 and the variable-pitch screw 7 store mechanical kinetic energy emitted by the prime mover 11; the variable pitch screw 7 is arranged in parallel under a slot 50 of an aircraft carrier detachable deck 12 of a take-off runway, and a first bearing 10 and a second bearing 15 are arranged at two ends of the variable pitch screw 7, wherein at least one of the first bearing and the second bearing is a thrust bearing; a spiral groove 8 with a variable helix angle beta is arranged on the outer cylindrical surface of the variable pitch screw 7; the telescopic sliding block 6 is a component of a traction trolley 11 and can be controlled to be inserted into or separated from a thread groove 8 of the variable-pitch screw 7; the rails 17 are arranged on two sides of the ejector ground groove 48 and are parallel to the axis of the variable-pitch screw 7; the traction trolley 11 is arranged above the variable-pitch screw 7, and wheels 18 or a thread groove 8 of the traction trolley 11 are in contact with the track 17, so that the traction trolley 11 can move forwards or backwards along the track 17; the towing hook 20 on the top of the towing trolley 11 is used for hanging the ejection rod 47 of the carrier-based aircraft 46.
The variable-pitch screw 7 is made of a thick-wall steel pipe with a large diameter, and is also used as the flywheel 4, and a huge inner space can also be used as a gas container.
The groove width of a thread groove 8 on the variable-pitch screw 7 is slightly larger than the width of the telescopic sliding block 6; the starting end A of the spiral groove 8 is connected with a section of starting groove 32 with a zero pitch, the starting groove 32 is an incomplete circular groove, the length is less than one circle, and the groove width is obviously greater than the width of the spiral groove 8; the length of the acceleration section AB of the variable-pitch screw 7 is longer, and the helix angle beta of the thread groove 8 is gradually increased from zero and reaches the maximum value at the point B; after the acceleration section AB is finished, the mixture enters a deceleration section BC, the length of the deceleration section BC is short, the helix angle beta of a spiral groove 8 of the deceleration section BC is gradually reduced, and the numerical value of the change rate of the helix angle beta is larger than that of the acceleration section AB; and after the spiral groove 8 of the deceleration section BC is finished, the spiral groove enters an ending groove 33 with a spiral angle beta of zero, the ending groove 33 is a complete circular groove, and a section of opening 49 is arranged at the joint of the ending groove 33 and the spiral groove 8.
The traction trolley 11 comprises a multi-slider hydraulic balanced stress mechanism, the mechanism consists of a set of hydraulic system and a plurality of telescopic cylinders which can move back and forth relative to the traction trolley, an accelerating buffer hydraulic cylinder 38 is arranged at the front side, a decelerating buffer hydraulic cylinder 38 is arranged at the rear side, each telescopic cylinder 35 is propped by a front push rod 39 and a rear push rod 39 before the telescopic sliders 6 enter the starting groove 32, hydraulic pipelines 41 of high-pressure hydraulic oil 42 are communicated, and the same air bag type energy accumulator 45 provides the high-pressure hydraulic oil 42.
The reset device of the traction trolley 11 is an electric vehicle driving system and comprises a power supply, a controller, a reset motor 56, a gear 58 and a rack 59; the racks 59 are parallel to the rails 17 and are arranged on two sides of the ejector ground groove 48; the guide groove 37 on the traction trolley 11 is clamped between the rails 17 on two sides of the ejector ground groove 48, a certain gap is reserved between the guide groove 37 and the rails 17, and the traction trolley 11 can move back and forth along the rails 17; a gear 58 is mounted on the output shaft 55 of the reset motor 56; when the wagon 11 needs to be backed up, the controller of the resetting device activates the resetting motor 56 and drives the gear 58 via the shaft 55 to rotate in the reverse direction, so that the wagon 11 automatically returns to the starting position.
The thread groove 8 on the variable pitch screw 7 is a multi-thread which is uniformly distributed, and the traction trolley 11 is provided with a plurality of groups of telescopic slide blocks 6.
The main body of the variable pitch screw 7 is a hollow cylinder, a convex variable pitch spiral steel rail is arranged on the outer side of the variable pitch screw, and the telescopic sliding block 6 on the traction trolley 11 can be in contact with the front side surface of the variable pitch spiral steel rail and enables the traction trolley 11 to move forwards along the track 17 under the pushing of the telescopic sliding block.
The traction trolley is provided with a lubricating oil spraying device which sprays oil lubrication to the spiral groove 8 and the telescopic sliding block 6 in the advancing process of the traction trolley.
The section of the telescopic sliding block adopts a quasi-rectangular section or a quasi-long circular section with a round angle, the front contact surface and the rear contact surface are cambered surfaces which slightly bulge outwards, and the bending radius of the cambered surfaces is close to the minimum bending radius of the two contact surfaces of the spiral groove as much as possible but not larger than the minimum bending radius of the two contact surfaces of the spiral groove; the telescopic sliding block can rotate along the axis of the telescopic sliding block relative to the telescopic cylinder by a limited rotation angle, the limited rotation angle starts from zero degree, and the maximum angle is slightly larger than the maximum helix angle of the thread groove.
The change relation between the helix angle beta of the helical groove and the traction trolley displacement s basically follows the following design concept:
assuming that the stored energy before the flywheel and the variable pitch screw are ejected is infinite, the rotational speed of the variable pitch screw during ejection can be considered as a constant rotational speed n. Assuming that the diameter of the variable pitch screw is D and the length of the acceleration section is L1The length of the deceleration section is L2Acceleration of the acceleration sectionDegree is a1Acceleration of the deceleration section is a2Then the helix angle of the acceleration section
At the end of the acceleration section, s1＝L1Angle of helix beta1To a maximum value betaM，
The speed of the tractor also reaches a maximum value VT，VTN · pi · D · tg β M. Lead angle of deceleration section
At the end of the acceleration section s2＝L1+L2Angle of helix beta2When the angle is 0 DEG, the speed of the traction trolley is reduced to zero, and the forward movement is stopped.
The energy stored by the actual flywheel and the variable-pitch screw before ejection cannot be infinite, so that the rotation speed of the flywheel and the variable-pitch screw is reduced slightly in the ejection process because the carrier-based aircraft needs to absorb certain kinetic energy from the flywheel and the variable-pitch screw when accelerated. In order to maintain stable acceleration, the helix angle beta of the helical groove can be properly corrected according to the rotation speed change of the variable-pitch screw during actual design.
Although the telescopic slider is rapidly rotated before being inserted into the start groove of the variable pitch screw, in order to ensure accurate insertion, a synchronous trigger mechanism may be provided to allow the telescopic cylinder of the telescopic slider to operate just before the telescopic slider reaches the start position of the start groove of the variable pitch screw, and to wait until the next turn. As the initial groove arc length of the variable-pitch screw is larger, the telescopic sliding block can be accurately inserted into the initial groove as long as the action time of the telescopic cylinder is accurate.
The driving mechanism of the telescopic sliding block is not necessarily a structure of a cylinder and a piston, and is not necessarily arranged on the traction trolley, and also can be arranged at two ends of a trench of the catapult, the starting end is provided with a synchronous insertion driving mechanism, the ending end is provided with a drawing driving mechanism, and the traction trolley is only provided with a state maintaining mechanism of the telescopic sliding block. When the synchronous insertion driving mechanism at the starting end drives the telescopic sliding block on the traction trolley to be inserted into the starting groove of the variable-pitch screw, the state maintaining mechanism of the telescopic sliding block on the traction trolley keeps the telescopic sliding block in an inserted state all the time and drives the traction trolley to advance under the action of the screw groove until the telescopic sliding block enters the ending groove, and then the extraction driving mechanism at the ending end drives the telescopic sliding block to be extracted from the ending groove of the variable-pitch screw.
Considering that the variable-pitch screw has strong gyroscopic effect when rotating, when the catapult is applied to catapult take-off of a carrier-based aircraft, the catapults can be preferably used in pairs on an aircraft carrier, and the turning directions of the variable-pitch screws and the turning directions of the spiral grooves of two adjacent catapults are designed to be opposite.
In addition, a controllable flip cover is arranged below the slit position of the ejector of the detachable deck, and the slit is automatically blocked when the ejector is not used, so that sundries are prevented from entering.
The operating steps of the ejector are as follows:
1) starting a prime motor 1, driving a flywheel 4 and a variable pitch screw 7 to rotate in an accelerating way through a speed changer 3, and storing energy for the flywheel 4 and the variable pitch screw 7;
2) stopping the traction trolley 11 at a starting position A, placing the telescopic slide block 6 on the traction trolley at the side of the starting groove 32 at the initial end of the variable-pitch screw 7, and then hanging an ejection rod 47 of the carrier-based aircraft 46 on a traction hook 20 at the top of the traction trolley 11;
3) when the rotating speeds of the flywheel 4 and the variable-pitch screw 7 reach rated values, starting the telescopic cylinder 35 of the telescopic sliding block 6 to quickly push the telescopic sliding block 6 into the starting groove 32 of the variable-pitch screw 7;
4. with the rotation of the variable-pitch screw 7, the telescopic sliding block 6 enters the screw groove 8 of the acceleration section AB, the helix angle beta of the screw groove 8 begins to increase continuously, and the carrier-based aircraft 46 is dragged by the traction trolley 11 to advance in an accelerated manner;
5) when the telescopic sliding block 6 of the traction trolley 11 reaches a point B with the maximum helix angle beta, the traction trolley 11 reaches the highest speed, and then enters a deceleration section BC of the variable-pitch screw 7, and the speed of the carrier-based aircraft 46 reaches the takeoff speed;
6) as the lead angle beta of the variable-pitch screw 7 is reduced and the traction trolley 11 starts to decelerate, the ejection rod 47 of the carrier-based aircraft 46 automatically disengages from the traction hook 20 to continue to advance;
7) after the traction trolley 11 passes through a deceleration section BC of the variable-pitch screw 7, the telescopic slide block 6 finally enters an ending groove 33 with a zero pitch, and the traction trolley 11 stops advancing;
8) the telescopic sliding block 6 is drawn out from the ending groove 33 of the variable-pitch screw 7;
9) and starting the reset driving device to push the traction trolley 11 to the initial end A of the variable-pitch screw 7 to prepare for next ejection.
The first embodiment is as follows:
the shipboard aircraft catapult described in this embodiment is a mechanical catapult device driven by a flywheel energy storage and variable-pitch screw, and is shown in fig. 1. The ejection device mainly comprises a prime mover 1, a hydraulic torque converter 2 speed changer 3, a flywheel 4, a variable pitch screw 7, a telescopic slide block 6, a traction trolley 11 and a track 17, wherein except that a traction hook 20 at the top of the traction trolley 11 extends out of an aircraft carrier detachable deck 12, the rest parts are all arranged in an ejector ground groove 48 below the aircraft carrier detachable deck 12 of a take-off runway; the prime mover 1 drives the flywheel 4 and the variable pitch screw 7 to rotate in an accelerating way through the speed changer 3; the flywheel 4 and the variable pitch screw 7 store mechanical kinetic energy emitted by the prime mover 1; the variable pitch screw 7 is arranged below a split 50 of a detachable deck 12, a first bearing 10 and a second bearing 15 are arranged at two ends of the variable pitch screw 7, and a spiral groove 8 with a spiral angle beta changed is arranged on the outer cylindrical surface of the variable pitch screw 7; the telescopic sliding block 6 is a component of the traction trolley, can be stretched under the action of the telescopic cylinder 35, and is inserted into or separated from the thread groove 8 of the variable-pitch screw 7 according to a control command; the rails 17 are arranged on two sides of the ejector ground groove 48 and are parallel to the axis of the variable-pitch screw 7; the traction trolley 11 is arranged above the variable-pitch screw 7, wheels 18 of the traction trolley 11 are in contact with the track 17, and the traction trolley 11 can move forwards or backwards; the towing hook 20 on the top of the towing trolley 11 is an open semicircular groove for hanging the ejection rod 47 of the carrier-based aircraft 46.
At least one of the first bearing 10 and the second bearing 15 arranged at the two ends of the variable pitch screw 7 is a thrust bearing; the outer surface of the variable pitch screw 7 is provided with a thread groove 8, as shown in fig. 2. An initial groove 32 with a helix angle beta of zero less than one circle is arranged at the position of the outgoing end A of the variable pitch screw 11, the tail end of the initial groove 32 is connected with an AB thread groove 8 of the acceleration section, and the groove width of the initial groove 32 is larger, as shown in figure 9; the length of the acceleration section AB of the spiral groove 8 is longer, the helix angle beta of the spiral groove 8 is gradually increased from zero degree until the point B is reached, and the helix angle beta of the spiral groove 8 reaches the maximum value; entering a deceleration section BC from a point B, wherein the length of the deceleration section BC is shorter, the helix angle beta of the spiral groove 8 is gradually reduced, and the change rate of the helix angle beta is larger than that of the acceleration section AB; after the deceleration section BC spiral groove 8 is finished, the deceleration section BC enters an end groove 9 with a zero helix angle beta, the end groove 9 is a complete circular groove 33, and a section of opening 49 is arranged at the joint of the end groove 9 and the spiral groove 8, as shown in figure 10; the groove widths of the spiral grooves 8 of the acceleration section AB and the deceleration section BC are slightly larger than the width of the telescopic sliding block; in practice, the vicinity of the junction of any two stages should contain a short transient of variable acceleration.
The towing trolley 11 is elastically connected with the telescopic sliding block 6 arranged on the towing trolley in the advancing direction so as to buffer the impact force of the sharp change of the acceleration on the carrier-based aircraft 46 and the towing trolley 11.
The flywheel 4 and the variable pitch screw 7 are in gear reduction transmission, the number of teeth of the small gear 5 on one side of the flywheel 4 is small, and the number of teeth of the large gear 14 on one side of the variable pitch screw 7 is large, so that the rotating speed of the flywheel 4 is improved to the greatest extent, the energy storage density is improved, and the weight of the ejection system is reduced.
The operating mode of the ejector is as follows: firstly, a prime motor 1 is started, the prime motor 1 drives a flywheel 4 through a hydraulic torque converter 2 and a speed changer 3, and then drives a variable pitch screw 7 to rotate in an accelerating way after being decelerated by a small gear 5 and a large gear 14, so that mechanical kinetic energy emitted by the prime motor 1 is accumulated in the flywheel 4 and the variable pitch screw 7; when the rotating speed of the variable-pitch screw 7 reaches the set value, ejection can be carried out; before ejection, a traction trolley 11 is placed at the initial end of a variable-pitch screw 7 in advance, a telescopic slide block 6 on the traction trolley 11 is positioned beside an initial groove 32, and an ejection rod 47 on a front landing gear of a carrier-based aircraft 46 is hung in a semicircular groove of a traction hook 20 on the upper portion of the traction trolley 11; when the rotating speed of the variable-pitch screw 7 reaches a specified value, the telescopic cylinder 35 is started to quickly push the telescopic slide block 6 into the initial groove 32 of the variable-pitch screw 7, along with the rotation of the variable-pitch screw 7, the telescopic slide block 6 enters an acceleration section AB screw groove 8 with a gradually increased helix angle beta, and the telescopic slide block 6 drives the traction trolley 11 to drag the carrier-based aircraft 46 to advance along the track 17 in an accelerated manner; the speed of the carrier-based aircraft 46 reaches the takeoff initial speed at the moment when the telescopic slide block 6 on the traction trolley 11 reaches the point B of the variable-pitch screw 7; then, the towing trolley 11 enters a deceleration section BC, the helix angle beta of the variable-pitch screw 7 starts to be gradually reduced, the towing trolley 11 decelerates, and the carrier-based aircraft automatically breaks away from the towing hook 20 of the towing trolley 11 and is pushed by an engine of the carrier-based aircraft to continue accelerating and complete takeoff from the carrier; after the traction trolley 11 reaches the tail end of the variable-pitch screw 7, the telescopic sliding block enters the ending groove 9 with the pitch being zero, and the traction trolley 11 stops advancing; and finally, the telescopic cylinder 35 is started to draw out the telescopic sliding block 6 from the ending groove 33, and the traction trolley 11 is pushed to the initial end of the variable-pitch screw 7 by the reset driving device to prepare for next ejection.
Because the telescopic sliding block 6 is light, the telescopic cylinder 35 can adopt various forms such as pneumatic, hydraulic or electromagnetic and the like. Because the telescopic sliding block 6 is inserted in the wider starting groove 32, the process of inserting the telescopic sliding block 6 does not generate acting force with the variable-pitch screw 7; similarly, the separation of the telescopic sliding block 6 from the variable-pitch screw 7 is also carried out in the end groove 33 with the pitch being zero, and the separation process of the telescopic sliding block 6 does not generate acting force with the variable-pitch screw 7.
In the embodiment, a diesel engine of about 600kW is selected, theoretically, the preparation time from the starting of the internal combustion engine to the reaching of the rated rotating speed of the flywheel is about 20 minutes, and then the carrier-based aircraft can be continuously ejected at the speed of ejecting one carrier for 30t class or 15t class in 2 minutes or 1 minute. Four such ejectors can lift 40-rack 30 t-grade or 80-rack 15 t-grade carrier aircraft off in 20 minutes.
Description of the drawings: in the power analysis of the embodiment, various mechanical losses are ignored, and the energy supplement of a prime motor and the action of the self power of the carrier-based aircraft are also ignored.
Example two:
this embodiment is a simplified version of the invention, see fig. 2. The ejection device mainly comprises a motor, a variable pitch screw, a telescopic slide block, a traction trolley and a track, and is mainly different from the embodiment 1 in that a hydraulic torque converter 2, a speed changer 3 and a flywheel 4 are omitted, and the motor 21 is used as a prime mover, so that the ejection device is particularly suitable for ships with sufficient electric power.
The variable-pitch screw 7 in the embodiment is a thick-wall hollow pipe with the length of about 70m, the diameter of 3.2m, the wall thickness of 0.06m and the weight of 320t, a spiral groove 8 is processed on the outer side of the hollow pipe, the length of an accelerating section is about 59m, the length of a decelerating section is about 10 m, and the maximum helix angle beta at the end of the accelerating section reaches 45 degrees. The moment of inertia of the variable pitch screw 7 itself is large enough to act as a flywheel.
The motor 21 is an alternating current motor with the rated rotation speed of 1575rpm and the rated power of 1200 kW. The gear ratio of the small gear to the large gear is 0.28. When the variable pitch screw 7 works, the motor 21 drives the variable pitch screw 7 to rotate after being decelerated by a gear. The ejection can be carried out when the rotation speed of the motor 21 reaches the rated rotation speed. The rotating speed of the variable pitch screw 7 before ejection is 7.35 revolutions per second, the linear speed of the outer surface of the variable pitch screw 7 is 73.5m/s, the kinetic energy of the variable pitch screw 7 is about 10 times of the kinetic energy required for ejecting a 30t heavy carrier-based aircraft, when the ejected carrier-based aircraft is finished in an acceleration section, due to energy transfer, the speed of the variable pitch screw 7 is reduced to 7 revolutions per second at a point B, the linear speed of the outer surface of the variable pitch screw 7 is 70m/s, and the fastest sliding speed of the sliding block in the spiral groove is 99 m/s. The maximum helix angle beta is 45 degrees, so that the maximum speed of the ejected carrier-based aircraft is 70 m/s; then the slide block 6 of the traction trolley 11 enters the deceleration section BC of the variable pitch screw 7, the helix angle beta of the thread groove 8 is sharply reduced along with the increase of the axial distance, the traction trolley 11 is also rapidly decelerated until the speed is zero and stops in the ending groove 33, and the relationship between the advancing speed V and the axial distance S of the traction trolley in the whole ejection process is shown in figure 13. The spiral angle beta of the spiral groove 8 of the variable-pitch screw 7 is designed in the whole ejection process according to the principle of equal acceleration, the acceleration of the traction trolley in an acceleration section is 4.2g, and the acceleration of a deceleration section is-25 g, and the drawing is shown in figure 14. If the acceleration a value of the acceleration section or the deceleration section needs to be reduced, the axial length of the acceleration section AB or the deceleration section BC of the variable pitch screw 7 can be lengthened.
Theoretically, one such catapult needs about 10 minutes of preparation time from the start of the motor 21, can carry out normal catapult, and can continuously catapult at the speed of 1 minute for catapult of a carrier-based aircraft of 30t class. Four ejectors can lift 80 carriers with the weight of 30t off in 20 minutes.
Description of the drawings: in the power analysis of the embodiment, various mechanical losses are ignored, and the energy supplement of a prime motor and the action of the self power of the carrier-based aircraft are also ignored.
Example three:
the embodiment is a multi-slide hydraulic automatic balance stress mechanism, and is shown in figures 6-8. The device mainly comprises a group of acceleration buffer hydraulic cylinders 38, a group of deceleration buffer hydraulic cylinders 36 and an air bag type energy accumulator 45. Each group of buffer hydraulic cylinders comprises a group of independent one-way piston cylinders 51, pistons 40 and push rods 39, and the hydraulic pipelines 41 of all the one-way piston cylinders 51 are communicated and are provided with high-pressure hydraulic oil 42 by the air bag type energy storage devices 45. A group of hydraulic cylinders communicated with the liquid path automatically adjusts the position of the telescopic sliding block 6 relative to the traction trolley in the advancing direction so as to adapt to the change of the helix angle beta of the thread groove 8 and balance acting forces borne by the telescopic cylinders 35 of different telescopic sliding blocks 6. Each group of one-way piston hydraulic cylinders can only bear the acting force in one direction, and the stress in different directions during acceleration and deceleration can be solved by using the front and rear groups of one-way piston hydraulic cylinders.
The state of the multi-telescopic-slide-block hydraulic automatic balance stress mechanism when the traction trolley 11 is at the initial position is shown in fig. 6, all push rods 39 of the acceleration buffer hydraulic cylinder 38 and the group of deceleration buffer hydraulic cylinders 36 just abut against the telescopic cylinder 35 of each telescopic slide block 6, and all telescopic slide blocks 6 are right opposite to the initial groove 32.
When the telescopic sliding blocks 6 enter the spiral groove 8 of the acceleration section AB, the telescopic sliding blocks 6 are different from each other in the front and back direction of the variable pitch screw 7 in the axial direction, as shown in fig. 7. At this time, all the push rods 39 of the deceleration buffer hydraulic cylinders 36 are separated from the telescopic cylinders 35 of the telescopic sliders 6, and all the push rods 39 of the acceleration buffer hydraulic cylinders 38 are pressed against the telescopic cylinders 35 of the telescopic sliders 6.
When the telescopic sliding blocks 6 enter the thread grooves 8 of the deceleration section BC, the telescopic sliding blocks 6 are different from each other in the front and back direction of the variable pitch screw 7 in the axial direction, as shown in fig. 8. At this time, all the push rods 39 of the acceleration damping hydraulic cylinders 38 are separated from the telescopic cylinders 35 of the telescopic sliders 6 by the inertia of the traction trolley 11, and all the push rods 39 of the deceleration damping hydraulic cylinders 36 are pressed against the telescopic cylinders 35 of the telescopic sliders 6.
The air bag type energy accumulator 45 is a container for storing a certain volume of high-pressure hydraulic oil, and is composed of a steel cylinder 52 and a high-pressure air bag 43, and the high-pressure air bag 43 is filled with high-pressure air 44. The high pressure hydraulic oil 42 in the steel cylinder 52 has a high pressure under the action of the high pressure air bag 43.
Example four:
this embodiment is an ejector with a variable pitch screw 7 with a built-in motor and speed reducer, see fig. 11. The ejection device mainly comprises a motor, a planetary reducer, a variable pitch screw, a telescopic sliding block, a traction trolley and a track, and is mainly different from the embodiment 2 in that a motor 21, a gear 5, a gear 14 and an inner gear ring 53 of the ejection device are all arranged inside a variable pitch screw 7, so that the installation space is saved overall, and the working mode and the effect are the same as those of the embodiment.
Example five:
the embodiment is a resetting device arranged on a traction trolley, and is shown in figure 12. The reset device of the traction trolley 11 is an electric vehicle driving system, and comprises a power supply, a controller, a reset motor 56, a gear 58 and a rack 59; the guide groove 37 on the traction trolley 11 is clamped between the rails 17 on two sides of the ejector ground groove 48, a certain gap is reserved between the guide groove 37 and the rails 17, and the traction trolley 11 can move back and forth along the rails 17; the racks 59 are parallel to the rails 17 and are arranged on two sides of the ejector ground groove 48; a gear 58 is mounted on the output shaft 55 of the return motor 56; the controller deactivates the reset motor 56 when advancing the cart 11 and the gear 58 is free to rotate with the output shaft 55 of the reset motor 56. After a launch is complete, the controller of the reset device activates the reset motor 56 and causes the gear 58 to rotate in the reverse direction via the output shaft 55, thereby automatically returning the wagon 11 to the starting position. The reset motor 56 may be an asynchronous induction motor or an SR motor that generates a low voltage when the motor is open-circuited. The power supply of the resetting device can also be provided from the outside, and the traction trolley 11 is obtained by electric brushes through the power supply contact nets arranged on two sides of the ejector ground groove 48.
Example six:
this embodiment is an example of the use of the variable pitch screw catapult of the present invention for cold launch of a launch vehicle, see fig. 15. A plurality of synchronously running variable-pitch screws 7 are vertically arranged around the underground launching well, and a carrier rocket 60 is fixed on a traction trolley 11; the telescopic slide block 6 on the traction trolley 11 is inserted into the spiral groove 8 outside the variable-pitch screw 7 during the ejection time, and the carrier rocket 60 is ejected and lifted off under the action of the spiral angle of the spiral groove 8 along with the rotation of the variable-pitch screw 7. The operation process of the ejector is the same as that of the first embodiment and the second embodiment.
This cold launch is different from the conventional hot launch of a launch vehicle and from the conventional cold launch of an intercontinental ballistic missile.
Before launching, the driving motor 21 is started firstly to store energy for the variable-pitch screw; after the rotating speed of the variable-pitch screw 7 reaches a rated value, the movable well cover 57 is opened; then starting the telescopic cylinder 35 to enable the telescopic sliding block 6 to be inserted into the starting groove 32 of the thread groove 8 outside the variable-pitch screw 7, enabling the traction trolley 11 to accelerate the loaded carrier rocket 60 upwards along with the rotation of the variable-pitch screw 7, and enabling the traction trolley 11 to start decelerating after the maximum speed is reached, so that the carrier rocket 60 is separated from the traction trolley 11 and flies away from a wellhead 61 under the action of inertia; the moving manhole cover 57 is then quickly closed, and the launch vehicle 60 is then fired in the air and continues flying under its own power. Most of the residual energy of the variable-pitch screw after the rocket is ejected can be fed back to the power grid through the motor.
The maximum speed of ejection depends on the height at which the launch vehicle needs to be ejected. For example, by designing the velocity of the bottom of the rocket 60 away from the ground to be 50m/s, only the kinetic energy of the catapult applied to the launch vehicle 60 can fly the bottom of the launch vehicle 60 into the air at 170 m.
The carrier rocket adopting the cold launching mode has the greatest advantage of low requirements on weather conditions, and can be launched in any weather in principle as long as the carrier rocket does not meet strong wind, which is significant for the construction and material transportation of space stations in the future.
The existing missile vertical launching device for cold launching and hot launching by air pressure launching cannot be loaded on a ship because a launching tube must be sealed, and has to be loaded in a port, and a 5 kiloton-class missile driving and protecting ship can only be equipped with less than hundreds of missiles. The catapult adopting the principle of the invention does not need a sealed launching tube, has no flame, smoke dust and blast of high-pressure gas during catapult, is particularly suitable for a missile vertical launching system of a ship, and can quickly load a missile to continue launching after one-time catapult.
The above-mentioned embodiments are merely preferred embodiments of the present invention, which are not intended to limit the scope of the present invention, and therefore, all equivalent changes made by the contents of the claims of the present invention should be included in the claims of the present invention.
The data listed are only for the sake of brevity in describing the workings of the invention and do not represent necessary values.
Claims (9)
1. The catapult is characterized by comprising a variable-pitch screw (7), a traction trolley (11) and a power driving device for driving the variable-pitch screw (7) to rotate; wherein the content of the first and second substances,
the variable-pitch screw (7) is of a cylindrical structure, the kinetic energy stored during normal work can reach more than 5 times of the kinetic energy required by an ejected object, two ends of the variable-pitch screw are movably mounted, a starting groove (32), a spiral groove (8) and an ending groove (33) are sequentially formed in the outer circle of the variable-pitch screw (7) along the axial direction, the starting groove (32) and the ending groove (33) are both circular grooves, the starting groove (32) is an incomplete circular groove with the length less than one circle, the ending groove (33) is a complete circular groove, a section of opening (49) is formed in the joint of the ending groove (33) and the spiral groove (8), the spiral groove (8) starts from one end of the starting groove (32), the spiral rising angle beta gradually increases from zero degree, the spiral rising angle beta gradually decreases to zero after reaching the highest speed point, and the starting groove (32) and the ending groove (33) are in smooth transition with the variable-pitch spiral groove;
a traction hook (20) is arranged above the traction trolley (11), at least one telescopic cylinder (35) is arranged below the traction trolley (11), a piston in each telescopic cylinder (35) is connected with one end of one telescopic sliding block (6), the other end of each telescopic sliding block (6) extends out of each telescopic cylinder (35), each telescopic sliding block (6) can slide up and down in each telescopic cylinder (35), when one end of each telescopic sliding block (6) extending out of each telescopic cylinder (35) is inserted into a thread groove (8) of each variable-pitch screw (7), and when the variable-pitch screws (7) rotate, the telescopic sliding blocks (6) drive the traction trolley (11) and the traction hook (20) above the traction trolley (11) to move linearly along the axial direction of the variable-pitch screws (7);
the spiral groove (8) is divided into an acceleration section and a deceleration section, the rotating speed of the variable pitch screw (7) in the ejection process is set to be n, the diameter of the variable pitch screw (7) is set to be D, and the length of the acceleration section is set to be L1The length of the deceleration section is L2Acceleration of the acceleration section is a1Acceleration of the deceleration section is a2The displacement of the traction carriage (11) is s, the helix angle of the acceleration section
At the end of the acceleration section, s1＝L1Angle of helix beta1To a maximum value betaM，
The speed of the traction carriage (11) reaches a maximum value VT，VT＝n·π·D·tgβMAngle of helix of deceleration section
At the end of the deceleration section s2＝L1+L2Angle of helix beta2At 0 deg., the speed of the traction trolley (11) is reduced to zero and the advance is stopped.
2. An ejector according to claim 1, wherein the power drive means comprises a prime mover (1) disposed at either end of the variable pitch screw (7), the output shaft of the prime mover (1) being connected to the input of a torque converter (2), the output of the torque converter (2) being connected to the input of a variator (3), the output of the variator (3) driving the variable pitch screw (7) in rotation;
or the power driving device comprises a motor (21) arranged at any end of the variable pitch screw (7), an output shaft of the motor (21) drives the variable pitch screw (7) to rotate through a gear reducer, and the gear reducer comprises a pinion (5) arranged at the output shaft of the motor (21) and a bull gear (14) arranged at the input end of the variable pitch screw (7);
or the power driving device comprises a motor (21) arranged on the inner side of any one end of the variable pitch screw (7), an inner gear ring (53) is arranged on the inner side of the variable pitch screw (7), and an output shaft of the motor (21) drives the variable pitch screw (7) to rotate through a quasi-planetary gear consisting of a sun gear small gear (5), a planetary gear large gear (14) and the inner gear ring (53).
3. Ejector according to claim 2, characterised in that the output of the variator (3) is also provided with a flywheel (4) to make up for the lack of energy storage by the variable pitch screw (7).
4. The ejector of claim 1, wherein when the ejector is used as an aircraft carrier ejector, the ejector is arranged in an ejector ground groove (48) below a deck (19), an aircraft carrier detachable deck (12) is arranged above the ejector ground groove (48), a slit (50) is formed in the aircraft carrier detachable deck (12), rails (17) are formed in two sides of the ejector ground groove (48), wheels (18) below a towing trolley (11) are arranged in the rails (17), a towing hook (20) extends out of the slit (50) in the aircraft carrier detachable deck (12) to be above the deck (19) and is used for being connected with an ejection rod (47) of a carrier (46), and auxiliary support wheels (13) are arranged on two sides of a variable-pitch screw (7).
5. Ejector according to claim 1 or 4, wherein the traction carriage (11) is provided with a lubricating oil injection device for injecting lubricating oil to the thread groove (8) and the telescopic slider (6) during the advance of the traction carriage (11).
6. The ejector according to claim 4, further comprising a multi-slider hydraulic automatic balancing force mechanism disposed under the towing vehicle (11), and comprising a set of accelerating and buffering hydraulic cylinders (38), a set of decelerating and buffering hydraulic cylinders (36) and an air bag type energy accumulator (45), wherein each set of buffering hydraulic cylinders comprises a set of one-way piston cylinders (51), a piston (40) disposed in the one-way piston cylinders (51), and a push rod (39) having one end connected to the piston (40) and the other end extending out of the one-way piston cylinders (51), all of the accelerating and buffering hydraulic cylinders (38) and the decelerating and buffering hydraulic cylinders (36) are communicated with the air bag type energy accumulator (45) through hydraulic pipelines (41), the air bag type energy accumulator (45) provides high-pressure hydraulic oil (42), and each one-way piston cylinder (51) automatically adjusts the position of the telescopic slider (6) in the advancing direction relative to the towing vehicle through the push rod (39) So as to adapt to the change of the helix angle beta of the helical groove (8) and balance the acting force born by each telescopic sliding block (6).
7. The ejector according to claim 6, wherein the thread grooves (8) on the variable pitch screw (7) are multi-thread threads which are uniformly distributed, and the traction trolley (11) is provided with a plurality of groups of telescopic sliding blocks (6) so as to improve the stress condition of the variable pitch screw (7); each screw groove (8) in the multi-start thread is connected with one end of an independent initial groove (32), the initial grooves (32) are not communicated with each other, but the axial positions of the variable-pitch screws (7) are the same, the lifting rule of the helix angle of each screw groove (8) is the same, the screw grooves finally enter the same ending groove (33), and the ending groove (33) and each screw groove (8) are provided with an independent opening (49) at the joint.
8. The ejector according to claim 4, further comprising a reset device disposed under the towing trolley (11) and including a power source, a controller, a reset motor (56), a gear (58) and a rack (59), wherein the guide slot (37) of the towing trolley (11) is clamped between the rails (17) on both sides of the slot (48) of the ejector, a gap is left between the guide slot (37) and the rails (17), and the towing trolley (11) can move back and forth along the rails (17); the rack (59) is arranged in parallel with the track (17) and is arranged on two sides of the ejector ground groove (48); a gear (58) is mounted on an output shaft (55) of the reset motor (56); when the driving trolley (11) moves forward, the controller does not excite the reset motor (56), the gear (58) can freely rotate along with the output shaft (55) of the reset motor (56), and after one ejection is completed, the controller of the reset device excites the reset motor (56) and drives the gear (58) to reversely rotate through the output shaft (55), so that the traction trolley (11) automatically returns to the starting position.
9. The ejector according to claim 1, wherein the front and back surfaces of the telescopic sliding block (6) contacting the spiral groove (8) are cambered surfaces, and the bending radius of the cambered surfaces is as close as possible to but not larger than the minimum bending radius of the two contact surfaces of the spiral groove (8); the telescopic sliding block (6) can rotate the telescopic cylinder (35) at a limited rotation angle along the axis of the telescopic sliding block, the limited rotation angle starts from zero degree, and the maximum rotation angle is larger than the maximum helix angle of the thread groove (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810241500.2A CN109229412B (en) | 2018-03-22 | 2018-03-22 | Ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810241500.2A CN109229412B (en) | 2018-03-22 | 2018-03-22 | Ejector |
Publications (2)
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| CN110950273B (en) * | 2019-11-11 | 2021-08-24 | 井洪涛 | Lifting device for building |
| CN111854545B (en) * | 2020-06-04 | 2022-09-30 | 中国人民解放军国防科技大学 | Boosting gliding small-sized test rocket system |
| CN114212267B (en) * | 2021-12-27 | 2023-10-31 | 西安现代控制技术研究所 | Single torsion spring energy storage rotary cam type safety switch mechanism of aircraft |
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| US2756950A (en) * | 1954-10-07 | 1956-07-31 | Cleveland Pneumatic Tool Co | Aircraft launching device, including a rocket propelled ball screw and nut |
| CN101954974A (en) * | 2009-07-13 | 2011-01-26 | 栾远刚 | Repeating aircraft catapult |
| CN102767299A (en) * | 2011-05-04 | 2012-11-07 | 张愈浓 | Full-automatic stereoscopic parking garage |
| CN202679204U (en) * | 2012-05-25 | 2013-01-16 | 福建尤迪电机制造有限公司 | Novel high power permanent magnetism brushless motor |
| CN203186580U (en) * | 2013-03-26 | 2013-09-11 | 孟金来 | Linear accelerating device |
| CN103183133B (en) * | 2013-03-26 | 2015-07-15 | 张本胜 | Ejector of aircraft carrier shipboard aircraft |
| FR3006990B1 (en) * | 2013-06-14 | 2015-07-17 | Eads Europ Aeronautic Defence | DEVICE FOR THE FLOOR MOVEMENT OF AIRCRAFT |
| CN204161627U (en) * | 2014-09-04 | 2015-02-18 | 张涛 | Spiral aircraft carrier takes off catapult-launching gear |
| US10059465B2 (en) * | 2014-11-19 | 2018-08-28 | The Boeing Company | System to accelerate and decelerate aircraft for take-off and landing |
| WO2016205415A1 (en) * | 2015-06-15 | 2016-12-22 | ImageKeeper LLC | Unmanned aerial vehicle management |
| CN105035343B (en) * | 2015-08-13 | 2018-01-16 | 济南环太机电技术有限公司 | A kind of jetting type ejector of aircraft carrier shipboard aircraft |
| CN205096917U (en) * | 2015-11-20 | 2016-03-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Dual -purpose quick change frock of burner inner liner turnning and milling |
| CN205469870U (en) * | 2016-04-06 | 2016-08-17 | 杨广祥 | Adopt engine / motor to be power hydraulic mechanical transmission's carrier -borne aircraft catapult |
| CN206373952U (en) * | 2016-04-12 | 2017-08-04 | 文登蓝岛建筑工程有限公司 | A kind of automatic cut-off knife mechanism |
| CN106344355B (en) * | 2016-10-28 | 2017-07-18 | 广州初曲科技有限公司 | A kind of lower limb secondary row movement machine bone with center of gravity self-adjusting balance function |
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