CN109229412A - A kind of ejector - Google Patents
A kind of ejector Download PDFInfo
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- CN109229412A CN109229412A CN201810241500.2A CN201810241500A CN109229412A CN 109229412 A CN109229412 A CN 109229412A CN 201810241500 A CN201810241500 A CN 201810241500A CN 109229412 A CN109229412 A CN 109229412A
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- trolley
- ejector
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Classifications
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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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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
A kind of ejector of the present invention, for the catapult-assisted take-off of aircraft carrier and the pop-up of carrier rocket and the vertical launch system of various guided missiles.Then the mechanical energy that the present invention first issues prime mover realizes ejection by the varying pitch screw driving trailer wagon of quasi- constant speed rotary again by flywheel energy storage.After the starting vessel of the sliding block insertion varying pitch screw on trailer wagon, varying pitch screw just by the helical flute of helix angle eustasy and can terminate slot precisely movement is accomplished without any letup by the ejection of constant acceleration and Brake stop this whole set of；The hydraulic producing balanced forces mechanism of multi-slide can use multiple sliding blocks simultaneously in a varying pitch helical flute, solve the problems, such as that single sliding block can not provide enough thrust.Original machine power of the present invention is small, and system weight is light, high-efficient, and ejection acceleration is steady, ejection frequency is high, manufacturing process is simple, low in cost, and anti-electromagnetism striking capabilities are strong, and maintenance is simple, maintenance personal is few, and comprehensive performance is better than steam catapult and Electromagnetical 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 the ejector adopts a prime mover with lower power as power, accumulates energy through a flywheel, directly converts the rotary motion of a variable-pitch screw into the linear motion of a traction trolley through the combined action of the variable-pitch screw linked with the flywheel and a telescopic slide block on the traction trolley which can only do linear motion along a track, accelerates a carrier-borne aircraft to a specified take-off speed at a stable acceleration by virtue of the change of a spiral lifting angle β of a spiral groove of the variable-pitch screw, then rapidly decelerates the traction trolley and separates the carrier-borne aircraft, the telescopic slide block separates from the variable-pitch screw after the traction trolley stops, a resetting device on the traction trolley can drive the traction trolley to automatically move backwards and return to the initial position before ejection to prepare for next ejection.
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 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 rising angle β gradually increases from zero degree, the spiral rising angle is gradually reduced to zero after the spiral groove reaches the highest speed point, and the starting groove and the ending groove are in smooth transition with the variable-pitch;
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 sectionAt the end of the acceleration section, s1＝L1Helix angle β1To a maximum of βM，The speed of the tractor reaches a maximum value VT，VTN · pi · D · tg β M, lead angle of the deceleration sectionAt the end of the acceleration section s2＝L1+L2Helix angle β2At 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 β of the spiral.
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 figures 1 to 15, the ejector 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 towing trolley 11 and a track 17, wherein 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 except that a towing hook 20 at the top of the towing trolley 11 extends out of an aircraft carrier removable deck 12 from a slit 50, the rest is arranged in a catapult ground groove 48 below the aircraft carrier removable deck 12 of a take-off runway, 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 for take-off, the variable pitch screw 7 is arranged in parallel to the lower part of the slit 50 of the aircraft carrier removable deck 12 of the runway, both ends of the variable pitch screw 7 are provided with a first bearing 10 and a second bearing 15, at least one of which is a thrust bearing, a screw β of the variable pitch screw 7 is arranged on the surface of the towing trolley 7, the track 11 is arranged in parallel to the axis of the towing hook 8, the track 11 or the track 11, the track 11 is arranged on the track, the track 11 is arranged in parallel to control track, the track 11, or the track, the track 11 is arranged in contact with the track, the track.
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 spiral 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 starting groove 32 with a zero pitch, the starting groove 32 is an incomplete circular groove, the length is less than one circle, the groove width is obviously larger than the width of the spiral groove 8, the length of an acceleration section AB of the variable-pitch screw 7 is longer, the spiral angle β of the spiral groove 8 is gradually increased from zero degree and reaches the maximum value at a point B, the acceleration section AB enters a deceleration section BC after the acceleration section AB is finished, the length of the deceleration section BC is shorter, the spiral angle β of the spiral groove 8 of the deceleration section BC is gradually reduced, the change rate value of the spiral angle β is larger than that of the acceleration section AB, the spiral groove 8 of the deceleration section BC enters an ending groove 33 with a zero spiral angle β after the end, the ending groove 33 is a complete circular groove, and a section of an opening 49 is formed at the joint of the ending groove 33 and.
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 relationship between the helix angle β of the helical groove and the trolley displacement s should basically follow 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 L2The acceleration of the acceleration section is a1Acceleration of the deceleration section is a2Then the helix angle of the acceleration sectionAt the end of the acceleration section, s1＝L1Helix angle β1To a maximum of βM，The speed of the tractor also reaches a maximum value VT，VTN · pi · D · tg β m. lead angle of the deceleration sectionAt the end of the acceleration section s2＝L1+L2Helix angle β2When the angle is 0 DEG, the speed of the traction trolley is reduced to zero, and the forward movement is stopped.
In order to maintain stable acceleration, the spiral lift angle β of the spiral groove can be properly corrected according to the change of the rotating speed of the variable pitch screw in 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 AB spiral groove 8 of the acceleration section, the spiral angle β of the spiral 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 the point B with the maximum helix angle β, the traction trolley 11 reaches the highest speed, and then enters the 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 helix angle β of the variable-pitch screw 7 is reduced and the towing trolley 11 starts to decelerate, the ejection rod 47 of the carrier-based aircraft 46 automatically disengages from the towing 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 the embodiment is a mechanical catapult driven by a flywheel energy storage and variable-pitch screw, see figure 1. the catapult mainly comprises a prime mover 1, a hydraulic torque converter 2, a speed changer 3, a flywheel 4, a variable-pitch screw 7, a telescopic slide block 6, a towing trolley 11 and a track 17, wherein the towing hook 20 at the top of the towing trolley 11 extends out of an aircraft carrier opening deck 12, the rest of the catapult is arranged in a catapult ground groove 48 below an aircraft carrier opening deck 12 of a take-off runway, the prime mover 1 drives the flywheel 4 and the variable-pitch screw 7 to accelerate 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 the aircraft carrier opening 12, a first bearing 10 and a second bearing 15 are arranged at two ends of the variable-pitch screw 7, a spiral groove 8 with a spiral lifting angle β is arranged on the outer cylindrical surface of the variable-pitch screw 7, the telescopic slide block 6 is a part of the towing trolley and can be inserted into or separated from the spiral groove 8 of the variable-pitch screw 7 under the control command under the action of the telescopic cylinder 35, the control command, the towing trolley 11 is arranged above the track 11 and the towing trolley 11 is arranged on the two sides of the towing trolley 11.
At least one of a first bearing 10 and a second bearing 15 arranged at two ends of a variable pitch screw 7 is a thrust bearing, a thread groove 8 is processed on the outer surface of the variable pitch screw 7, see fig. 2, a starting groove 32 with a helix angle β less than one circle is zero at an outgoing end A of the variable pitch screw 11, the tail end of the starting groove 32 is connected with a thread groove 8 of an acceleration section AB, the groove width of the starting groove 32 is larger, see fig. 9, the length of an acceleration section AB of the thread groove 8 is longer, the helix angle β of the thread groove 8 is gradually increased from zero until a point B is reached, the helix angle β of the thread groove 8 reaches a maximum value, the thread groove 8 enters a deceleration section BC from the point B, the length of the deceleration section BC is shorter, the helix angle β of the thread groove 8 is gradually reduced, the change rate of the helix angle β is larger than that of the acceleration section AB, the thread groove 8 enters an ending groove 9 with a helix angle β of zero after the deceleration section BC is ended, the ending groove 9 is a complete ring groove 33, and is connected with the thread groove 8, an opening is provided with a slider at a position which is slightly larger than the acceleration section BC and the slider at any acceleration section BC and the acceleration section BC at any acceleration section BC which is manufactured when the acceleration section BC and.
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 catapult comprises the steps of firstly starting a prime mover 1, driving a flywheel 4 by the prime mover 1 through a hydraulic torque converter 2 and a speed changer 3, driving a variable-pitch screw 7 to rotate in an accelerated manner after deceleration through a small gear 5 and a large gear 14, accumulating mechanical kinetic energy emitted by the prime mover 1 in the flywheel 4 and the variable-pitch screw 7, enabling the catapult to be carried out after the rotating speed of the variable-pitch screw 7 reaches a set value, placing a traction trolley 11 at the initial end of the variable-pitch screw 7 in advance before catapulting, enabling a telescopic sliding block 6 on the traction trolley 11 to be located beside a starting groove 32, hanging an ejection rod 47 on a front undercarriage of a carrier-based aircraft 46 into a semicircular groove of a traction hook 20 on the upper portion of the traction trolley 11, starting a telescopic cylinder 35 to quickly push the telescopic sliding block 6 into the starting groove 32 of the variable-pitch screw 7 after the rotating speed of the variable-pitch screw 7 reaches a set value, enabling the telescopic sliding block 6 to enter an accelerating section AB screw groove 8 with a spiral lifting angle β gradually increased along with the rotation of the variable-pitch screw 7, enabling the telescopic sliding block 6 to drive the traction trolley 46 to advance along a track 17, enabling the telescopic sliding block 6 to enter a telescopic lifting angle B of the telescopic screw 7 to be dragged to be gradually increased to reach a point B of the initial accelerating groove 17 after the telescopic screw 7, and then to be pulled out from the tail end of the telescopic screw, and the telescopic screw 11, and the telescopic trolley 11, and the telescopic screw to be pulled to be gradually after the tail end of the telescopic trolley 11, and the telescopic screw 7, and the telescopic trolley 11 to be pulled to be.
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 acceleration section is about 59m in length, the deceleration section is about 10 m in length, the maximum spiral angle β at the end of the acceleration section reaches 45 degrees, and the variable-pitch screw 7 is large in rotation inertia and can serve as a flywheel.
The 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 variable pitch screw 7 has kinetic energy which is about 10 times of the kinetic energy required by ejecting a 30t heavy carrier aircraft, when the ejected carrier aircraft finishes 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, the fastest sliding speed of a sliding block in a thread groove is 99m/S, the maximum sliding speed of the ejected carrier aircraft is 70m/S due to a maximum spiral lifting angle β being 45 degrees, the maximum speed of the ejected carrier aircraft is also 70m/S, then a sliding block 6 of the ejection trolley 11 enters the variable pitch screw 7, the maximum sliding speed of the sliding block in the thread groove is 99m/S, the maximum spiral lifting angle β is 45 degrees, the maximum speed of the ejection trolley is also 70m/S, and the speed of the sliding block is reduced to the maximum acceleration of the speed of the ejection trolley 14, and the speed of the ejection trolley is reduced to the maximum acceleration of the speed of the ejection trolley 14, and the acceleration of the ejection trolley is also reduced along with the acceleration of the acceleration section of the acceleration of the ejection trolley 14, if the acceleration of the ejection trolley is equal to the acceleration of the ejection trolley 14, the acceleration of the ejection trolley is increased rapidly.
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 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, wherein each group of buffer hydraulic cylinders comprises a group of independent one-way piston hydraulic cylinders 51, a piston 40 and a push rod 39, hydraulic pipelines 41 of all the one-way piston hydraulic cylinders 51 are communicated, and the air bag type energy accumulator 45 provides high-pressure hydraulic oil 42, and the hydraulic cylinders communicated with the hydraulic circuits automatically adjust the position of the telescopic sliding block 6 in the advancing direction relative to a traction trolley so as to adapt to the change of a spiral lifting angle β of a spiral groove 8 and balance acting forces borne by the telescopic cylinders 35 of different telescopic sliding blocks 6.
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 (10)
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 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 β gradually increases from zero degree, the spiral rising angle 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;
the traction trolley is characterized in that a traction hook (20) is arranged above the traction trolley (11), at least one telescopic cylinder (35) is arranged below the traction trolley, 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), one end of each telescopic sliding block (6), which extends 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).
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 according to claim 1, wherein the spiral groove (8) is divided into an acceleration section and a deceleration section, the rotation speed of the variable pitch screw (7) during the ejection is set to n, the diameter of the variable pitch screw (7) is set to D, and the length of the acceleration section is set to 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 sectionAt the end of the acceleration section, s1＝L1Helix angle β1To a maximum of βM，The speed of the traction carriage (11) reaches a maximum value VT，VTN · pi · D · tg β M, lead angle of the deceleration sectionAt the end of the acceleration section s2＝L1+L2Helix angle β2At 0 deg., the speed of the traction trolley (11) is reduced to zero and the advance is stopped.
5. 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).
6. Ejector according to claim 1 or 5, 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).
7. The ejector according to claim 5, further comprising a multi-slider hydraulic automatic balancing force mechanism disposed below the towing trolley (11), and comprising a set of acceleration buffer hydraulic cylinders (38), a set of deceleration buffer hydraulic cylinders (36) and an air bag type energy accumulator (45), wherein each set of buffer hydraulic cylinders comprises a set of one-way piston hydraulic cylinders (51), pistons (40) disposed in the one-way piston hydraulic cylinders (51), and push rods (39) having one ends connected to the pistons (40) and the other ends extending out of the one-way piston hydraulic cylinders (51), all the acceleration buffer hydraulic cylinders (38) and the deceleration buffer 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 hydraulic cylinder (51) automatically adjusts the position of the retractable slider (6) relative to the towing trolley in the advancing direction to adapt to the change of the spiral lift angle β of the spiral groove (8) and the acting force of each retractable slider (6) is balanced at the same time.
8. The ejector according to claim 7, 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.
9. The ejector according to claim 5, 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 a 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.
10. 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).
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110950273A (en) * | 2019-11-11 | 2020-04-03 | 界首市天瓴建筑工程有限公司 | Lifting device for building |
| CN111854545A (en) * | 2020-06-04 | 2020-10-30 | 中国人民解放军国防科技大学 | Boosting gliding small-sized test rocket system |
| CN114212267A (en) * | 2021-12-27 | 2022-03-22 | 西安现代控制技术研究所 | Single torsional spring energy storage rotating cam type safety switch mechanism of aircraft |
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