CN104477400A - Unmanned aerial vehicle hydraulic catapult launching system - Google Patents
Unmanned aerial vehicle hydraulic catapult launching system Download PDFInfo
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- CN104477400A CN104477400A CN201410708695.9A CN201410708695A CN104477400A CN 104477400 A CN104477400 A CN 104477400A CN 201410708695 A CN201410708695 A CN 201410708695A CN 104477400 A CN104477400 A CN 104477400A
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Abstract
The invention aims to provide an unmanned aerial vehicle hydraulic catapult launching system which is compact in structure and short in response time. A buffer energy-absorption system is integrated in a hydraulic energy system. The technical scheme includes that in the hydraulic energy system, high-pressure hydraulic oil pumped out by a tandem pump group is divided into two paths, one path is connected with an energy accumulator through a hydraulic pipeline, the other path is connected with an oil tank through an electromagnetic overflow valve, the energy accumulator is connected with an oil inlet of a hydraulic motor through the hydraulic pipeline and an inserting valve with an electromagnetic directional valve, a sliding trolley slides in an accelerated manner under the action of power outputted by the hydraulic energy system, an electromagnet 2DT and an electromagnet 3DT are simultaneously powered off after the launching speed of an unmanned aerial vehicle is reached, the inserting valve is closed, the sliding trolley continues to move forwards under the inertia action of the sliding trolley, a traction belt drives the hydraulic motor to rotate reversely, the hydraulic oil is charged to the energy accumulator, kinetic energy of the sliding trolley is consumed, the sliding trolley decelerates to stop, and a buffer energy-absorption function is achieved.
Description
Technical field
The present invention relates to a kind of unmanned plane hydraulic catapult take-off system, particularly a kind of hydraulic energy system being integrated with buffering energy-absorbing system.
Background technology
In recent years, along with development that is scientific and technological and military equipment technology, unmanned plane is becoming weapon indispensable in modern high technology war in military field, equips land, sea, air, the various countries army more and more, for performing the training mission etc. of the combat duty such as attack, scouting and target drone.At civil area, the application of unmanned plane also day by day increases, as: survey of territorial resources, emergency disaster relief, dark woods fireproof monitoring, environmental monitoring etc.
Launch And Recovery System is a critical function system of unmanned plane, be meet UAV Maneuver flexibly, the necessary technology guarantee of the multiple demand such as repeated usage and failure-survival capability.At present, the launch mode of unmanned plane is numerous, as: rocket assist transmitting, catapult-assisted take-off, ground roll-out are taken off.It is be used as power with booster rocket that rocket assist is launched, be widely used in the transmitting of unmanned plane, unmanned plane flies away from feedway under the thrust of 1 or multiple stage (being generally 2) booster rocket, there is lift-off technology maturation, booster rocket thrust range be large, cost is low, the advantage such as seriation and have that property safe and out of sight is poor, consumable supplies and supporting ensures the shortcoming such as costly.Conventional unmanned aerial vehicle ejecting mode has elastic force to launch, Gas fluid pressure launches and launches with combustion gas.It is convert the elastic force of elastic element (as bungee, spring) to mechanical kinetic energy to be used as power that elastic force launches, unmanned plane is provided to take off required acceleration/accel, there is the advantages such as principle is simple, mechanism is light, be only applicable to the transmitting of light (little) type unmanned plane; Combustion gas is launched and is referred to and directly utilize powder gases to launch unmanned plane, usually realizes general transmitting by active service cannon.
Unmanned plane Gas fluid pressure catapult-assisted take-off mode is the guide rail kinetic energy catapult-assisted take-off mode of a kind of advanced person that the nineties in 20th century grows up in the world, and the main Gas fluid pressure energy that adopts is as unmanned aerial vehicle ejecting power.Compared with the rato mode of routine, it has the advantages such as property safe and out of sight is good, good economy performance, comformability are good, the signals such as light, sound, heat, smog can not be produced, there is not the storage of fire control equipment, transport and problem of management, and the expense of carrying out consumable supplies and support guarantee when unmanned plane is launched is lower at every turn, in addition within the specific limits by regulating charging pressure of accumulator and precharge pressure just can meet different unmanned plane to lift-off mass and takeoff speed operating needs; Take off compared with mode with ground roll-out, without the need to airfield runway, there is good maneuverability, unmanned aerial vehicle ejecting can be carried out continuously and take off.At present, a few countries such as the Jin You U.S., Britain and Switzerland is grasped technique and is widely applied and arrived in unmanned plane equipment in the world.
Existing unmanned plane hydraulic catapult take-off system is generally made up of Gas fluid pressure energy resource system 29, speed increaser, crash energy absorption equipment, slide trolley 31, launcher 30, locking releasing mechanism 32, unloading control mechanism, electric control system 33 and carrying platform 34 etc., its principle of work is: the high pressure liquid force feed that energy storage air bag inner high voltage gas expansion is discharged, flow into hydraulic actuating cylinder, drive the piston rod of hydraulic actuating cylinder to do contractile motion, convert hydraulic energy to mechanical kinetic energy; Piston rod is by the haulage cable on speed increaser, and traction slide dolly 31 delivers unmanned plane and runs along the guide rail on launcher 30 is sliding the takeoff speed accelerating to unmanned plane, mechanical kinetic energy conversion is launched the kinetic energy of unmanned plane; After slide trolley 31 reaches takeoff speed, collision buffering energy absorption device block steel rope, crash energy absorption equipment absorbs the kinetic energy of slide trolley 31, makes slide trolley 31 quick deceleration until stop motion; Unmanned plane then, under engine thrust and self inertia combined action, is separated with slide trolley 31, moves forward and take off.Gas fluid pressure energy resource system 29, as one of the core component of unmanned plane hydraulic catapult take-off system, is for hydraulic catapult take-off system provides energy source and power, and the collocation form that its conventional hydraulic energy is converted to mechanical energy is energy storage and high speed hydraulic cylinder.Topping up accumulation of energy process, emission process and unloading process 3 part is mainly comprised by the working process of the Gas fluid pressure energy resource system 29 of this principle design, that is: before unmanned plane is launched, high pressure liquid force feed is filled with to the energy storage being filled with rated pressure nitrogen by Hydraulic Pump, until reach the pressure required for unmanned plane transmitting, complete filling process; During transmitting, the high pressure liquid force feed that energy storage air cavity inner high voltage gas expansion is discharged, flow into hydraulic actuating cylinder, the piston of hydraulic actuating cylinder is driven to do contractile motion, piston rod is by the haulage cable on speed increaser, traction slide dolly 31 delivers unmanned plane and runs along the guide rail on launcher 30 is sliding the takeoff speed accelerating to unmanned plane, completes emission process; When the speed of piston reaches required value (that is: unmanned plane reaches takeoff speed), unloading control institution staff, makes energy storage stop opening the unloader valve oil extraction of hydraulic actuating cylinder while hydraulic actuating cylinder fuel feeding, completes unloading process.When Gas fluid pressure energy resource system 29 converts hydraulic energy to mechanical kinetic energy by high speed hydraulic cylinder, because unmanned plane generally directly can not be accelerated to takeoff speed by the kinematic velocity of high speed hydraulic cylinder piston in the move distance of self, the speed increaser that must pass through a set of high over-speed gear ratio makes slide trolley 31 sliding takeoff speed of running unmanned plane on guide rail.At present, conventional high over-speed gear ratio speed increaser is pulley speed increaser.Crash energy absorption equipment, as another core component of unmanned plane hydraulic catapult take-off system, for absorbing the kinetic energy of slide trolley 31, makes its quick deceleration until stop, to ensure unmanned plane and slide trolley 31 safe separating at short notice.At present, conventional crash energy absorption equipment is hydroturbine energy absorption device.
But, adopt the unmanned plane hydraulic catapult take-off system of above prior art to have the following disadvantages:
1) accelerator many employings high speed hydraulic cylinder, the kinematic velocity of its piston rod needs to reach 5m/s ~ 8m/s, and the flow flowing into cylinder hydraulic oil can reach 1500L/min ~ 3000L/min.Therefore, must according to flowing into the flow design of cylinder body or improving cylinder body inner flow passage, there is the shortcomings such as complex process, difficulty of processing are large;
2) speed increaser many employings pulley speed increaser, there is the shortcomings such as complex structure, hauling rope be easy to wear in it;
3), there is the shortcomings such as design calculation difficulty is large, volume is large in crash energy absorption equipment many employings hydroturbine energy absorption device or oil gas crash energy absorption equipment.
Summary of the invention
The present invention is directed to above-mentioned the deficiencies in the prior art part, provide a kind of form simple, compact conformation, difficulty of processing are little, response time is short, by the unmanned plane hydraulic catapult take-off system of the buffering energy-absorbing system integration in hydraulic energy system.
For achieving the above object, the present invention is achieved in that a kind of unmanned plane hydraulic catapult take-off system, comprise hydraulic energy system 29, buffering energy-absorbing system, launcher 30, slide trolley 31, locking releasing mechanism 32, electric control system 33 and carrying platform 34, it is characterized in that: in hydraulic energy system 29, fuel tank 1 connects the oil suction of twin pump group 2 by hydraulic tubing, two-way is divided into through high-pressure oil outlet check valve 5, hydraulic tubing of leading up to connects the pressure sensor 10 of energy storage 9 and setting energy storage 9 topping up energy-storage pressure, another road then connects fuel tank 1 by the electromagnetic relief valve 6 being connected across the operation pressure setting hydraulic energy system 29 between twin pump group 2 high-pressure oil outlet and fuel tank 1, the shutoff valve 8 be connected across after parallel connection between energy storage 9 with fuel tank 1 is connected fuel tank 1 with the safety valve 7 limiting energy storage 9 topping up energy-storage pressure by hydraulic tubing, energy storage 9 is by hydraulic tubing and the oil inlet of inserted valve 11 connecting fluid pressure motor 15 being installed in parallel solenoid directional control valve 12, HM Hydraulic Motor 15 return opening connects fuel tank 1 by prefill valve 16, the electromagnetic valve change-over valve 13-2 be arranged between energy storage 9 and prefill valve 16 on hydraulic tubing controls the switch of prefill valve 16, under the control of electric control system 33, be arranged on the drum mechanism built 14 between two HM Hydraulic Motor 15 by after fixed pulley 22 guiding of diverse location on traction belt 21, be connected with the slide trolley 31 be arranged on launcher 30 middle guide 24, under the dynamic action that slide trolley 31 years unmanned planes export at hydraulic energy system 29, add ski-running along the guide rail 24 in launcher 30 to run, move to V
0after point reaches the takeoff speed of unmanned plane, electromagnet 2DT, 3DT power-off simultaneously of solenoid directional control valve 12, inserted valve 11 is closed, hydraulic energy system 29 stops Power output, and slide trolley 31 moves forward under self inertia effect, drives HM Hydraulic Motor 15 contrarotation by traction belt 21, to energy storage 9 topping up force feed, consume the kinetic energy of slide trolley 31, make it be decelerated to parking, realize buffering energy-absorbing function.
The present invention has following beneficial effect compared to prior art.
The present invention adopts the array mode of energy storage 9 and HM Hydraulic Motor 15 that hydraulic energy is converted to ejection power, after inserted valve 11 in hydraulic energy system 29 is closed, there is no excess pressure in pipeline between inserted valve 11 to fuel tank 1, decrease hydraulic actuating cylinder unloading mechanism required in traditional Gas fluid pressure energy resource system; Meanwhile, the present invention adopts HM Hydraulic Motor 15 to drive drum mechanism built 14 directly to realize the speedup of slide trolley 31, decreases large over-speed gear ratio pulley speed increaser required in traditional unmanned aerial vehicle ejecting take-off system, reduces the complexity of system composition.
Under the dynamic action that the present invention is exported at hydraulic energy system 29 by slide trolley 31 years unmanned planes, add ski-running race along the guide rail 24 in launcher 30, move to V
0after point reaches the takeoff speed of unmanned plane, inserted valve 11 in hydraulic energy system 29 is closed, hydraulic energy system 29 stops Power output, slide trolley 31 moves forward under self inertia effect, make HM Hydraulic Motor 15 contrarotation to energy storage 9 topping up force feed (that is: HM Hydraulic Motor 15 is converted to pumping function to energy storage 9 topping up force feed by motor function) by traction belt 21, consume the kinetic energy of slide trolley 31, it is made to be decelerated to parking, utilize the energy storage 9 in hydraulic energy system 29 dexterously, inserted valve 11, drum mechanism built 14, HM Hydraulic Motor 15 Hydraulic Elements such as grade and mechanism, composition buffering energy-absorbing system, realize buffering energy-absorbing function.Compared with the employing conventional crash energy absorption equipment such as hydroturbine or oil gas crash energy absorption equipment, there is the advantages such as compact conformation, volume are little.
The present invention adopt HM Hydraulic Motor 15 drive drum mechanism built 14 directly speedup replace traditional Gas fluid pressure energy resource system and adopt high speed hydraulic cylinder and pulley speed increaser speedup, overcome the shortcomings such as high speed hydraulic cylinder and the complex process existing for pulley speed increaser, difficulty of processing are large.
The present invention adopts solenoid directional control valve 12 to control the oil circuit of inserted valve 11 directly between opening and closing energy storage 9 and HM Hydraulic Motor 15, improves the capability of fast response that hydraulic energy system 29 releases energy and stops providing energy, shortens response time.
Accompanying drawing explanation
Fig. 1 is unmanned plane hydraulic catapult take-off system structural principle schematic diagram of the present invention.
Fig. 2 is the hydraulic principle schematic diagram of hydraulic energy system 29 and buffering energy-absorbing system in Fig. 1.
Fig. 3 is the structural representation that in Fig. 1, buffering energy-absorbing system realizes buffering energy-absorbing function by the fixed pulley 22 be arranged on launcher 30.
Fig. 4 is the structural representation of launcher 30 in Fig. 1.
Fig. 5 is the workflow schematic diagram of unmanned plane hydraulic catapult take-off system of the present invention.
In figure: 1 fuel tank, 2 twin pump groups, 3 motors (or automobile power transmission), 4 check valves, 5 check valves, 6 electromagnetic relief valves, 7 safety valves, 8 shutoff valves, 9 energy storages, 10 pressure sensors, 11 inserted valves, 12 electromagnetic valve change-over valves, 13 solenoid directional control valves, 14 drum mechanism built, 15 HM Hydraulic Motor, 16 prefill valves, 17 by pass valves, 18 solenoid directional control valves, 19 hydraulic control one-way valves, 20 one-way throttle valves, 21 traction belts, 22 fixed pulleys, 23 support bodys, 24 guide rails, 25 folding joints, 26 elevation mounts, 27 rear supports, 28 adjustable rear support legs, 29 hydraulic energy systems, 30 launchers, 31 slide trolleys, 32 locking releasing mechanisms, 33 electric control systems, 34 carrying platforms, folded section before 35, 36 canned paragraphs, folded section after 37.
Detailed description of the invention
Below in conjunction with accompanying drawing and detailed description of the invention, the present invention is described in further detail.
Consult Fig. 1.In embodiment described below, unmanned plane hydraulic catapult take-off system, comprise hydraulic energy system 29, launcher 30, slide trolley 31, locking releasing mechanism 32, electric control system 33, carrying platform 34 and buffering energy-absorbing system, wherein, hydraulic energy system 29 adopts the array mode of energy storage 9 and HM Hydraulic Motor 15 hydraulic energy to be converted to the ejection power of unmanned plane, electric control system 33 controls hydraulic cylinder piston rod in elevation mount 26 and locking releasing mechanism 32 by hydraulic energy system 29 and makes fore and aft motion, the angle of divergence realizing launcher 30 respectively regulates and the locking of slide trolley and release.The installation foundation that the instrument that carrying platform 34 transports as the transition of unmanned plane hydraulic catapult take-off system is hydraulic energy system 29, launcher 30, electric control system 33 wait until subsystem.Slide trolley 31 is as carrier during unmanned aerial vehicle ejecting, be arranged on the guide rail 24 of launcher 30, undertaken up and down by the mating surfaces of wheel and guide rail 24, side-to-side movement direction is spacing, make slide trolley 31 add along the guide rail 24 in launcher 30 can not getaway in ski-running race process.Locking releasing mechanism 32 is primarily of compositions such as mount pad, lock dog, connecting rod, locking cylinder, unblock oil cylinders, be arranged on the afterbody of launcher 30, its effect is: before unmanned plane hydraulic catapult take-off system launches unmanned plane, slide trolley 31 (containing unmanned plane) is reliably locked on the guide rail 24 of launcher 30, after the power of hydraulic energy system 29 output reaches maxim, release slide trolley 31, makes it obtain maximum acceleration/accel and adds ski-running along the guide rail 24 of launcher 30 and run; Electric control system 33 is made up of electric power system and control system, be arranged on carrying platform 34, the angle of divergence for system power supply, launcher 30 regulate, the locking of slide trolley 31 and release control, hydraulic energy system 29 topping up accumulation of energy control and hydraulic energy source release control etc.
Consult Fig. 2.Hydraulic energy system 29 is primarily of fuel tank 1, twin pump group 2, motor or automobile power transmission 3, check valve 5, electromagnetic relief valve 6, safety valve 7, shutoff valve 8, energy storage 9, pressure sensor 10, inserted valve 11, electromagnetic valve change-over valve 12, solenoid directional control valve 13, drum mechanism built 14, HM Hydraulic Motor 15, prefill valve 16 be connected each interelement hydraulic tubing and form, wherein: motor (or automobile power transmission) 3 drives twin pump group 2 by coupler, the oil suction of twin pump group 2 is connected with fuel tank 1 by hydraulic tubing, the high-pressure oil outlet of twin pump group 2 is connected energy storage 9 by check valve 5 with hydraulic tubing, electromagnetic relief valve 6 is connected across between the high-pressure oil outlet of twin pump group 2 and fuel tank 1, for setting the operation pressure of hydraulic energy system 29, pressure sensor 10 is connected on the pipeline between check valve 5 and energy storage 9, for setting the topping up energy-storage pressure of energy storage 9, shutoff valve 8 and safety valve 7 are connected across between energy storage 9 and fuel tank 1 side by side, safety valve 7 is for limiting the highest topping up pressure energy-storage pressure of energy storage 9, guarantee the safety of energy storage 9, shutoff valve 8 launches the hydraulic oil of rear excess pressure for operating personal manual releasing energy storage 9, energy storage 9 is connected with the oil inlet of hydraulic tubing with HM Hydraulic Motor 15 by inserted valve 11, and the return opening of HM Hydraulic Motor 15 is connected with fuel tank 1 with hydraulic tubing by prefill valve 16, and the drain tap of HM Hydraulic Motor 15 is directly connected with fuel tank 1 by hydraulic tubing, solenoid directional control valve 12 is arranged on inserted valve 11, for controlling the opening and closing of inserted valve 11, electromagnetic valve change-over valve 13-2 is arranged on the hydraulic tubing between energy storage 9 and prefill valve 16, for controlling the opening and closing of prefill valve 16, traction belt 21 in drum mechanism built 14 is connected with slide trolley 31 after being led by the fixed pulley 22 being arranged on diverse location on launcher 30.Buffering energy-absorbing system is made up of the energy storage 9 in hydraulic energy system 29, inserted valve 11, drum mechanism built 14, HM Hydraulic Motor 15, prefill valve 16, the fixed pulley 22 that connects each interelement hydraulic tubing and be arranged on diverse location on launcher 30, wherein: energy storage 9 is connected with the oil inlet of hydraulic tubing with HM Hydraulic Motor 15 by inserted valve 11, and the return opening of HM Hydraulic Motor 15 is connected with fuel tank 1 with hydraulic tubing by prefill valve 16; Traction belt 21 in drum mechanism built 14 is connected with slide trolley 31 after being led by the fixed pulley 22 being arranged on diverse location on launcher 30.
Further, the working process of hydraulic energy system 29 mainly comprises topping up accumulation of energy process and hydraulic energy source dispose procedure 2 part, that is:, before unmanned plane is launched, electric control system 33 is powered to electromagnet 1DT and made electromagnetic relief valve 6 stop overflow off-load.Be arranged on motor in carrying platform 34 or automobile power transmission 3 drives twin pump group 2 to work by coupler, the high pressure liquid force feed that twin pump group 2 pumps is through check valve 5, enter and be filled with in the energy storage 9 of rated pressure nitrogen in air bag, by the nitrogen accumulation of energy in compress energy storage device 9 air bag.After pressure sensor 10 detects that the supercharging pressure of energy storage 9 reaches setting value, electric control system 33 stops powering to electromagnet 1DT making electromagnetic relief valve 6 overflow off-load, completes topping up accumulation of energy process; During hydraulic energy source release (that is: during transmitting), first electric control system 33 is powered to electromagnet 4DT, 5DT and is made solenoid directional control valve 13-1,13-2 commutation work, prefill valve 16 opened by hydraulic oil in energy storage 9, connects return opening and the fuel tank 1 of HM Hydraulic Motor 15.Then, electric control system 33 is powered to electromagnet 2DT, 3DT and is made solenoid directional control valve 12-1,12-2 commutation open inserted valve 11, the high pressure liquid force feed that high pressure gas expansion in energy storage 9 air bag is discharged, the oil inlet of HM Hydraulic Motor 15 is entered through inserted valve 11, get back to fuel tank 1 through prefill valve 16 after the return opening of HM Hydraulic Motor 15 is discharged, HM Hydraulic Motor 15 drives drum mechanism built 14 High Rotation Speed to reclaim traction belt 21, traction belt 21 traction slide dolly 31 delivers unmanned plane and runs along the guide rail 24 on launcher 30 is sliding the takeoff speed accelerating to unmanned plane, completes emission process.
Consult Fig. 3.Buffering energy-absorbing system comprises: be connected on safety valve 7, energy storage 9 between shutoff valve 8 and inserted valve 11 on hydraulic tubing, be connected on the inserted valve 11-1 between energy storage 9 and HM Hydraulic Motor 15-2 on hydraulic tubing, be connected on the inserted valve 11-2 between energy storage 9 and HM Hydraulic Motor 15-1 on hydraulic tubing, be connected on the HM Hydraulic Motor 15-1 on hydraulic tubing between inserted valve 11-2 and topping up pressure valve 16, be connected on the HM Hydraulic Motor 15-2 on hydraulic tubing between inserted valve 11-1 and topping up pressure valve 16, be connected on HM Hydraulic Motor 15-1, drum mechanism built 14 between HM Hydraulic Motor 15-2, and be connected to HM Hydraulic Motor 15-1, HM Hydraulic Motor 15-2 prefill valve on point of attachment pipeline 16 and be arranged on diverse location on launcher 30, by fixed pulley 22 lead traction slide dolly 31 move traction belt 21, wherein: energy storage 9 passes through the oil inlet of inserted valve 11 and hydraulic tubing connecting fluid pressure motor 15, HM Hydraulic Motor 15 return opening connects prefill valve 16, and connect fuel tank 1 by hydraulic tubing.Traction belt 21 in drum mechanism built 14 is connected with slide trolley 31 after being led by the fixed pulley 22 being arranged on diverse location on launcher 30.
The method that buffering energy-absorbing system realizes buffering energy-absorbing is: under the dynamic action that slide trolley 31 years unmanned planes export at hydraulic energy system 29, add ski-running and run, move to V along the guide rail 24 in launcher 30
0after point reaches the takeoff speed of unmanned plane, electromagnet 2DT, 3DT power-off simultaneously of solenoid directional control valve 12 in hydraulic energy system 29, inserted valve 11 is closed, hydraulic energy system 29 stops Power output, slide trolley 31 moves forward under self inertia effect, make HM Hydraulic Motor 15 contrarotation to energy storage 9 topping up force feed (that is: HM Hydraulic Motor 15 is converted to pumping function to energy storage 9 topping up force feed by motor function) by traction belt 21, consume the kinetic energy of slide trolley 31, make it be decelerated to parking, realize buffering energy-absorbing function.
Consult Fig. 4.Launcher 30 mainly comprises support body 23, guide rail 24, folding joint 25, elevation mount 26, rear support 27 and adjustable rear support leg 28, wherein, be arranged on carrying platform 34 as the sliding race of slide trolley 31 provides the launcher 30 of track to be divided into front folded section 35, canned paragraph 36 and rear folded section 37, front folded section 35 and rear folded section 37, respectively by folding joint 25 section of being connected and fixed 36, can be launched along left side or right side or fold respectively in the horizontal plane; The guide rail 24 be arranged on support body 23 adds the track of ski-running race as slide trolley 31, slide trolley 31 operates on the guide rail 24 of support body 23; Elevation mount 26 is movably connected in the front portion of canned paragraph 36, for regulating the angle of divergence of unmanned plane; Rear support 27 is movably connected in the afterbody of canned paragraph 36, as the turning point of unmanned plane angle of divergence adjustment; Adjustable rear support leg 28 is movably connected in the afterbody of rear folded section 37, for supporting the afterbody of launcher 30.
Consult Fig. 5.The specific works process of the embodiment of the present invention is as follows:
A) angle of divergence control process
Adopt electric control system 33 by controlling the method for solenoid directional control valve electromagnet energising commutation, the power utilizing hydraulic efficiency pressure system to provide changes the extension elongation of hydraulic cylinder piston rod in elevation mount 26, make the axis of rotation of canned paragraph 36 in rear support 27 of launcher 30, realize the adjustment of angle of divergence.
B) expansion of launcher 30, folding process
Adopt electric control system 33 by controlling the method for solenoid directional control valve electromagnet energising commutation, utilize the power that swing hydraulic pressure cylinder exports, drive folding joint 25 to rotate and change the front folded section 35 of support body 23 and the position of rear folded section 37, realize expansion and the folding process of launcher 30.
C) the transmitting locking process of slide trolley 31
Adopting electric control system 33 by controlling the method for solenoid directional control valve electromagnet energising commutation, utilizing the power that hydraulic efficiency pressure system provides, the piston rod of locked hydraulic cylinder in locking releasing mechanism 32 being completed and stretches out, slide trolley 31 is locked in the end of launcher 30.
D) the pre-tensioner process of traction belt 21
The motor (or automobile power transmission) 3 be arranged on carrying platform 34 drives twin pump group 2 to work by coupler, electric control system 33 is energized to the electromagnet 4DT of solenoid directional control valve 13-1 and the electromagnet 6DT of solenoid directional control valve 18 simultaneously, the low pressure oil that twin pump group 2 pumps enters the oil inlet of HM Hydraulic Motor 15 through check valve 4, solenoid directional control valve 18, hydraulic control one-way valve 19, one-way throttle valve 20, and the traction belt 21 making HM Hydraulic Motor 15 drive drum mechanism built 14 to rotate forward being connected with slide trolley 31 is pre-tensioner.
E) energy storage 9 topping up accumulation of energy process
Before unmanned plane is launched, electric control system 33 is powered to electromagnet 1DT and is made electromagnetic relief valve 6 stop overflow off-load, the motor (or automobile power transmission) 3 be arranged in carrying platform 34 drives twin pump group 2 to work by coupler, the high pressure liquid force feed that twin pump group 2 pumps is through check valve 5, enter and be filled with in the energy storage 9 of rated pressure nitrogen in air bag, by the nitrogen accumulation of energy in compress energy storage device 9 air bag, when pressure sensor 10 detects (different setting values can be launching of different type of machines and provides power) after the supercharging pressure of energy storage 9 reaches setting value, electric control system 33 stops powering to electromagnet 1DT making electromagnetic relief valve 6 overflow off-load, the high pressure liquid force feed that twin pump group 2 pumps gets back to fuel tank 1 through electromagnetic relief valve 6, complete energy storage 9 and complete topping up accumulation of energy process.
F) unmanned plane emission process
During transmitting, first electric control system 33 is powered to electromagnet 4DT, 5DT is simultaneously made solenoid directional control valve 13-1,13-2 commutation work, and prefill valve 16 opened by the hydraulic oil in energy storage 9, connects return opening and the fuel tank 1 of HM Hydraulic Motor 15; Then, electric control system 33 is powered to electromagnet 2DT, 3DT simultaneously and solenoid directional control valve 12-1,12-2 is commutated, hydraulic oil in energy storage 9 enters through hydraulic tubing and opens inserted valve 11, the high pressure liquid force feed that high pressure gas expansion in energy storage 9 air bag is discharged, the oil inlet of HM Hydraulic Motor 15 is entered through inserted valve 11, get back to fuel tank 1 through prefill valve 16 after the return opening of HM Hydraulic Motor 15 is discharged, HM Hydraulic Motor 15 drives drum mechanism built 14 tensioning traction belt 21, makes slide trolley 31 be in preacceleration state; Finally, electric control system 33 controls locking releasing mechanism 32 and discharges slide trolley 31, the high pressure liquid force feed of discharging in energy storage 9 is got back in fuel tank 1 through inserted valve 11, HM Hydraulic Motor 15 and prefill valve 16 fast, the HM Hydraulic Motor 15 of High Rotation Speed drives drum mechanism built 14 to rotate forward and is wound around traction belt 21 fast, traction slide dolly 31 delivers unmanned plane and runs along the guide rail 24 on launcher 30 is sliding the takeoff speed accelerating to unmanned plane, completes emission process.
F) slide trolley 31 buffer deceleration process
Under the dynamic action that slide trolley 31 years unmanned planes export at hydraulic energy system 29, add ski-running along the guide rail 24 in launcher 30 and run, move to V
0after point reaches the takeoff speed of unmanned plane, electric control system 33 stops the electromagnet 2DT of solenoid directional control valve 12 in hydraulic energy system 29 simultaneously, 3DT powers, inserted valve 11 is closed, hydraulic energy system 29 stops Power output, slide trolley 31 moves forward under self inertia effect, HM Hydraulic Motor 15 contrarotation is made by traction belt 21, by the hydraulic tubing between connection energy storage 9 and HM Hydraulic Motor 15 to energy storage 9 topping up force feed (that is: HM Hydraulic Motor 15 is converted to pumping function to energy storage 9 topping up force feed by motor function), consume the kinetic energy of slide trolley 31, it is made to be decelerated to parking, realize buffering energy-absorbing function.
G) slide trolley 31 return stroke
The motor (or automobile power transmission) 3 be arranged on carrying platform 34 drives twin pump group 2 to work by coupler, electrical control control system is powered to electromagnet 4DT and electromagnet 7DT simultaneously, make solenoid directional control valve 13-1 and solenoid directional control valve 18 commutation work, the low pressure oil that twin pump group 2 is discharged is through check valve 4, solenoid directional control valve 18, hydraulic control one-way valve 19, one-way throttle valve 20 enters the oil inlet of HM Hydraulic Motor 15, drum mechanism built 14 contrarotation is driven by HM Hydraulic Motor 15, the traction belt 21 be wrapped in drum mechanism built 14 is released, slide trolley 31 gets back to launcher 30 end along launcher 30 middle guide 24 under self gravitation effect, prepare to launch next time.
Above-mentioned embodiment of the present invention can not think the restriction done the claims in the present invention; if those skilled in the art does not need performing creative labour to make various amendment or equivalent replacement to the present invention by inspiration of the present invention, the protection domain of the claims in the present invention all should be fallen into.
Claims (10)
1. a unmanned plane hydraulic catapult take-off system, comprise hydraulic energy system, buffering energy-absorbing system, slide trolley, launcher, locking releasing mechanism, electric control system and carrying platform, it is characterized in that: in hydraulic energy system (29), fuel tank (1) connects the oil suction of twin pump group (2) by hydraulic tubing, two-way is divided into through high-pressure oil outlet check valve (5), hydraulic tubing of leading up to connects the pressure sensor (10) of energy storage (9) and setting energy storage (9) topping up energy-storage pressure, another road then connects fuel tank (1) by the electromagnetic relief valve (6) being connected across the operation pressure setting hydraulic energy system (29) between twin pump group (2) high-pressure oil outlet and fuel tank (1), the safety valve (7) being connected across the shutoff valve (8) between energy storage (9) with fuel tank (1) after parallel connection and limiting energy storage (9) topping up energy-storage pressure is connected fuel tank (1) by hydraulic tubing, energy storage (9) is by hydraulic tubing and the oil inlet of inserted valve (11) connecting fluid pressure motor (15) being installed in parallel solenoid directional control valve (12), HM Hydraulic Motor (15) return opening connects fuel tank (1) by prefill valve (16), the electromagnetic valve change-over valve 13-2 be arranged between energy storage (9) and prefill valve (16) on hydraulic tubing controls the switch of prefill valve (16), under the control of electric control system (33), after the drum mechanism built (14) be arranged between two HM Hydraulic Motor (15) is led by the fixed pulley (22) of the upper diverse location of traction belt (21), be connected with the slide trolley (31) be arranged on launcher (30) middle guide (24), under slide trolley (31) carries the dynamic action that unmanned plane exports at hydraulic energy system (29), add ski-running along the guide rail (24) in launcher (30) to run, move to V
0after point reaches the takeoff speed of unmanned plane, electromagnet 2DT, 3DT power-off simultaneously of solenoid directional control valve (12), inserted valve (11) is closed, hydraulic energy system (29) stops Power output, slide trolley (31) moves forward under self inertia effect, HM Hydraulic Motor (15) contrarotation is driven by traction belt (21), to energy storage (9) topping up force feed, consume the kinetic energy of slide trolley (31), make it be decelerated to parking, realize buffering energy-absorbing function.
2. unmanned plane hydraulic catapult take-off system as claimed in claim 1, is characterized in that: before unmanned plane is launched, and electric control system (33) is powered to electromagnet 1DT and made electromagnetic relief valve (6) stop overflow off-load.
3. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: be arranged on motor in carrying platform (34) or automobile power transmission (3) drives twin pump group (2) work by coupler, the high pressure liquid force feed that twin pump group (2) pumps is through check valve (5), enter in the energy storage (9) being filled with rated pressure nitrogen in air bag, by the nitrogen accumulation of energy in compress energy storage device air bag.
4. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: after pressure sensor (10) detects that the supercharging pressure of energy storage (9) reaches setting value, electric control system (33) stops powering to electromagnet 1DT making electromagnetic relief valve (6) overflow off-load, completes topping up accumulation of energy process.
5. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: during hydraulic energy source release, electric control system (33) is first powered to electromagnet 4DT, 5DT, make solenoid directional control valve 13-1, solenoid directional control valve 3-21 commutation work, prefill valve (16) opened by hydraulic oil in energy storage (9), connects return opening and the fuel tank (1) of HM Hydraulic Motor (15).
6. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: electric control system (33) is to electromagnet 2DT, electromagnet 3DT powers simultaneously and makes solenoid directional control valve 12-1, inserted valve (11) is opened in solenoid directional control valve 12-2 commutation, the high pressure liquid force feed that high pressure gas expansion in energy storage (9) air bag is discharged, the oil inlet of HM Hydraulic Motor (15) is entered through inserted valve (11), get back to fuel tank (1) through prefill valve (16) after the return opening of HM Hydraulic Motor (15) is discharged, HM Hydraulic Motor (15) drives drum mechanism built (14) High Rotation Speed to reclaim traction belt (21), traction belt (21) traction slide dolly (31) delivery unmanned plane runs along the guide rail (24) on launcher (30) is sliding the takeoff speed accelerating to unmanned plane, complete emission process.
7. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: buffering energy-absorbing system comprises: be connected on safety valve (7), energy storage (9) between shutoff valve (8) and inserted valve (11) on hydraulic tubing, be connected on the inserted valve 11-1 on hydraulic tubing between energy storage (9) and HM Hydraulic Motor 15-2, be connected on the inserted valve 11-2 on hydraulic tubing between energy storage (9) and HM Hydraulic Motor 15-1, be connected on the HM Hydraulic Motor 15-1 on hydraulic tubing between inserted valve 11-2 and topping up pressure valve (16), be connected on the HM Hydraulic Motor 15-2 on hydraulic tubing between inserted valve 11-1 and topping up pressure valve (16), be connected on HM Hydraulic Motor 15-1, drum mechanism built (14) between HM Hydraulic Motor 15-2, and be connected to HM Hydraulic Motor 15-1, HM Hydraulic Motor 15-2 prefill valve (16) on point of attachment pipeline and be arranged on the upper diverse location of launcher (30), by the traction belt (21) that fixed pulley (22) guiding traction slide dolly (31) moves.
8. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: launcher (30) mainly comprises support body (23), guide rail (24), folding joint (25), elevation mount (26), rear support (27) and adjustable rear support leg (28), wherein, being arranged on upper the race for slide trolley (31) is sliding of carrying platform (34) provides the launcher of track (30) to be divided into front folded section (35), canned paragraph (36) and rear folded section (37), front folded section (35) and rear folded section (37) are respectively by folding joint (25) section of being connected and fixed (36), can launch along left side or right side or fold respectively in the horizontal plane, the guide rail (24) be arranged on support body (23) adds the track of ski-running race as slide trolley (31), slide trolley (31) operates on the guide rail (24) of support body (23), elevation mount (26) is movably connected in the front portion of canned paragraph (36), for regulating the angle of divergence of unmanned plane, rear support (27) is movably connected in the afterbody of canned paragraph (36), as the turning point of unmanned plane angle of divergence adjustment, adjustable rear support leg (28) is movably connected in the afterbody of rear folded section (37), for supporting the afterbody of launcher (30).
9. unmanned plane hydraulic catapult take-off system as claimed in claim 8, it is characterized in that: electric control system (33) is by controlling solenoid directional control valve electromagnet energising commutation, the power utilizing hydraulic efficiency pressure system to provide changes the extension elongation of hydraulic cylinder piston rod in elevation mount (26), make the axis of rotation of canned paragraph (36) in rear support (27) of launcher (30), realize the adjustment of angle of divergence.
10. unmanned plane hydraulic catapult take-off system as claimed in claim 1, it is characterized in that: motor (or automobile power transmission) (3) be arranged on carrying platform drive twin pump group (2) work by coupler, electric control system (33) is energized to the electromagnet 4DT of solenoid directional control valve 13-1 and the electromagnet 6DT of solenoid directional control valve (18) simultaneously, the low pressure oil that twin pump group (2) pumps is through check valve (4), solenoid directional control valve (18), hydraulic control one-way valve (19), one-way throttle valve (20) enters the oil inlet of HM Hydraulic Motor (15), the traction belt (21) that HM Hydraulic Motor (15) drives drum mechanism built (14) to rotate forward being connected with slide trolley (31) is pre-tensioner.
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