CN203453160U - Pneumatic-hydraulic system of low-impact UAV ejector - Google Patents
Pneumatic-hydraulic system of low-impact UAV ejector Download PDFInfo
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- CN203453160U CN203453160U CN201320247045.XU CN201320247045U CN203453160U CN 203453160 U CN203453160 U CN 203453160U CN 201320247045 U CN201320247045 U CN 201320247045U CN 203453160 U CN203453160 U CN 203453160U
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Abstract
The utility model relates to a pneumatic-hydraulic system of a low-impact UAV ejector. The system is composed of a main oil pump electromagnetic unloading overflow valve, a main oil pump, a main oil pump motor, a slippage pump electromagnetic unloading overflow valve, a slippage pump, a slippage pump motor, a cartridge valve, a first non-return valve, a safety valve, a motor, an electro-hydraulic proportional cartridge valve, a second non-return valve, a safety and stop valve block, a third non-return valve, an accumulator, a pressure-reducing valve, a speed control valve, an electromagnetic reversing valve, a proportional overflow valve, a deceleration hydraulic cylinder, an oil tank, and oil hoses connecting all the parts. By using the hydraulic motor to drive a reel mechanism, the system overcomes the disadvantages that a conventional pneumatic-hydraulic system is complex in technique and difficult to machine due to the usage of a high-speed hydraulic cylinder. The system utilizes the proportional valve to control the hydraulic motor and to perform closed loop control of the rotational speed of the hydraulic motor, so that high-reliability low-impact ejection is achieved during the starting stage, and the system overcomes the defects that a conventional pneumatic-hydraulic system has large impact and poor reliability.
Description
Technical field
The present invention relates to a kind of unmanned aerial vehicle ejecting device, particularly the low impact catapult-launching gear of a kind of unmanned plane gas-liquid pressing system.
Background technique
Ejection mechanism is applied very extensive in military field, for example transmitting of guided missile and rocket, the transmitting of ship-board aircraft, the launching of unmanned plane, the launching of Lifesaving chair, and from space station, space shuttle or other aircraft launch and launch an artificial satellite etc.
The radiation pattern of unmanned plane is numerous, as hand throwing, airborne input, vehicle transmitting, launch, rocket assist etc.Conventional unmanned aerial vehicle ejecting mode has elastic force to launch, combustion gas is launched, the gentle hydraulic catapult of electromagnetic launch.Elastic force launches the elastic force of the elastic element (as elastic cord, spring) that utilizes stretchability very strong and does power, and the required acceleration that takes off is provided, and is applicable to light (little) type unmanned plane; Combustion gas is launched and is referred to and directly utilize powder gases to launch unmanned plane, conventionally by active service cannon, realizes general transmitting, consider anti-overloading performance, and the compatibility of general structure size and weapon; Electromagnetic launch is to utilize electromagnetic force to promote object, make object in short distance, accelerate to the device of launching after certain speed, because linear dc motion actuator has good controllability, can facilitate and accurately the size by regulation output electric current change launch can size, make Electromagnetical ejector there is the ability of accurately launching unmanned plane from light-duty to heavy.But electromagnetic launch is poor in middle-size and small-size unmanned plane field Economy, be therefore only adapted to large-scale unmanned plane and carrier-borne aircraft, gas hydraulic catapult is to utilize hydraulic actuator (oil hydraulic cylinder) and accumulator to be used in conjunction with, pressurized gas in accumulator is instantaneous to be pressed into hydraulic oil in oil hydraulic cylinder and to realize, compare with conventional rato mode, it is good that it has property safe and out of sight, good economy performance, the advantages such as adaptability is good, can not produce light, sound, heat, the signals such as smog, there is not the storage of fire control equipment, the advantages such as transportation and problem of management, and the expense that while carrying out unmanned plane transmitting, consumable supplies and support ensure is at every turn lower, in addition within the specific limits by regulating charging pressure of accumulator and charge pressure just can meet the usage requirement of different unmanned planes to take off weight and taking off speed, compare with the wheeled mode of taking off, the former takes off without airfield runway, has good maneuverability, can carry out continuously unmanned aerial vehicle ejecting and take off, easy to use, vehicle-mounted, carrier-borne all very applicable.
But traditional unmanned plane gas-liquid is pressed still Shortcomings part of catapult technique, the start up period of being first, impact greatlyr, be difficult to realize stepless speed regulation; Secondly, the high speed hydraulic cylinders that adopt in accelerating process more, difficulty of processing is large, complex process.
Summary of the invention
For the defect existing in above-mentioned prior art, technical problem to be solved by this invention is to provide the low impact catapult-launching gear of a kind of unmanned plane gas-liquid pressing system, this system possesses traditional unmanned plane gas-liquid and presses the advantages such as catapult technique good concealment, good economy performance, adaptability are good, has avoided that its breakout pressure impacts greatly, high speed hydraulic cylinder is difficult to the shortcomings such as processing simultaneously.
For achieving the above object, the present invention is achieved in that
The low impact catapult-launching gear of a kind of unmanned plane gas-liquid pressing system, it is by main oil pump electromagnetism unloading overflow valve 1, main oil pump 2, main oil pump motor 3, slippage pump electromagnetism unloading overflow valve 4, slippage pump 5, slippage pump motor 6, cartridge valve 7, the first one-way valve 8 and safety valve 9 thereof, oil hydraulic motor 10, electro-hydraulic proportion cartridge valve 11, the second one-way valve 12, safety and stop valve piece 13, the 3rd one-way valve 14, accumulator 15, reduction valve 16, series flow control valve 17, solenoid directional control valve 18, proportional pressure control valve 19, deceleration oil hydraulic cylinder 20, fuel tank 21 and the oil pipe being communicated between each original paper form, main oil pump motor 3 drives main oil pump 2, main oil pump 2 inlet ports are connected with fuel tank 21, main oil pump 2 force feed mouths are connected accumulator 15 with safety with stop valve piece 13 by the second one-way valve 12, and main oil pump electromagnetism unloading overflow valve 1 is connected across between the force feed mouth and fuel tank 21 of main oil pump 2, accumulator 15 is by electro-hydraulic proportion cartridge valve 11 connecting fluid pressure motor 10 filler openings, and oil hydraulic motor 10 return openings are connected with fuel tank 21 by cartridge valve 7, safety and stop valve piece 13 is connected with the 3rd one-way valve 14 simultaneously, and the reduction valve 16 that is linked in sequence, series flow control valve 17, solenoid directional control valve 18, solenoid directional control valve 18 filler openings connect deceleration oil hydraulic cylinder 20, and its return opening connects fuel tank 21, and proportional pressure control valve 19 is connected across between deceleration oil hydraulic cylinder 20 rod chambers and rodless cavity, slippage pump motor 6 drives slippage pump 5, and slippage pump 5 inlet ports are connected with fuel tank 21, and slippage pump 5 force feed mouths are connected with oil hydraulic motor 10 filler openings by the first one-way valve 8, and slippage pump electromagnetism unloading overflow valve 4 is connected across between the force feed mouth and fuel tank 21 of slippage pump 5.
The hardware of the low impact catapult-launching gear of unmanned plane gas-liquid pressing system comprises speed control system, movable pulley system, slide trolley system; Speed control system carries out speed control by movable pulley system by slide trolley system, and slide trolley carrying unmanned plane, finally realizes the low impact of unmanned plane and launch.
Described speed control system, main implementation method is: in electro-hydraulic proportion cartridge valve 11, by displacement transducer feedback signal, realize the closed loop control to spool travel; The speed feedback of oil hydraulic motor drum mechanism built and given signal compare, and realize the closed loop of unmanned plane speed or open loop are controlled, and then realize quick acceleration and the low impulsive control of unmanned plane.
Further, described movable pulley system, comprises movable pulley speed regulating structure and static pulley changement; Movable pulley speed regulating structure, for accelerating unmanned plane to taking off speed, and the retarding braking of slide trolley; Static pulley changement, transmits power to slide rail below for take commutation to process by flexible rope.
Further, described slide trolley system, as the carrier that launches of unmanned plane, accelerates to unmanned plane safe take-off speed on launching cradle together with unmanned plane, guarantees that unmanned plane boost phase is reliable.
Owing to adopting technique scheme, a kind of low impact unmanned aerial vehicle ejecting device gas-liquid pressing system provided by the invention, compared with prior art has such beneficial effect:
1) adopt fluid motor-driven drum mechanism built, overcome transmission gas-liquid pressing system and adopted high speed hydraulic cylinder, complex process, the shortcoming that difficulty of processing is large;
2) adoption rate valve control oil hydraulic motor, carries out closed loop control to motor rotary speed, and the highly reliable low impact start up period of can realizing is launched, and has overcome traditional gas Impact in Hydraulic System large, the shortcoming of poor reliability.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the low impact catapult-launching gear of unmanned plane of the present invention gas-liquid pressing system;
Fig. 2 is that the hardware each several part of the low impact catapult-launching gear of unmanned plane of the present invention gas-liquid pressing system is related to block diagram;
Fig. 3 is the low impact catapult-launching gear of unmanned plane of the present invention workflow diagram;
Fig. 4 is the mechanical structure schematic diagram of the low impact catapult-launching gear of unmanned plane of the present invention gas-liquid pressing system;
Fig. 5 is the low impact catapult-launching gear of unmanned plane of the present invention speed Control loop block diagram.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail:
The low impact catapult-launching gear of a kind of unmanned plane gas-liquid pressing system, as shown in Figure 1, it is by main oil pump electromagnetism unloading overflow valve 1, main oil pump 2, main oil pump motor 3, slippage pump electromagnetism unloading overflow valve 4, slippage pump 5, slippage pump motor 6, cartridge valve 7, the first one-way valve 8 and safety valve 9 thereof, oil hydraulic motor 10, electro-hydraulic proportion cartridge valve 11, the second one-way valve 12, safety and stop valve piece 13, the 3rd one-way valve 14, accumulator 15, reduction valve 16, series flow control valve 17, solenoid directional control valve 18, proportional pressure control valve 19, deceleration oil hydraulic cylinder 20, fuel tank 21 and the oil pipe being communicated between each original paper form, main oil pump motor 3 drives main oil pump 2, main oil pump 2 inlet ports are connected with fuel tank 21, main oil pump 2 force feed mouths are connected accumulator 15 with safety with stop valve piece 13 by the second one-way valve 12, and main oil pump electromagnetism unloading overflow valve 1 is connected across between the force feed mouth and fuel tank 21 of main oil pump 2, accumulator 15 is by electro-hydraulic proportion cartridge valve 11 connecting fluid pressure motor 10 filler openings, and oil hydraulic motor 10 return openings are connected with fuel tank 21 by cartridge valve 7, safety and stop valve piece 13 is connected with the 3rd one-way valve 14 simultaneously, and the reduction valve 16 that is linked in sequence, series flow control valve 17, solenoid directional control valve 18, solenoid directional control valve 18 filler openings connect deceleration oil hydraulic cylinder 20, and its return opening connects fuel tank 21, and proportional pressure control valve 19 is connected across between deceleration oil hydraulic cylinder 20 rod chambers and rodless cavity.Slippage pump motor 6 drives slippage pump 5, and slippage pump 5 inlet ports are connected with fuel tank 21, and slippage pump 5 force feed mouths are connected with oil hydraulic motor 10 filler openings by the first one-way valve 8, and slippage pump electromagnetism unloading overflow valve 4 is connected across between the force feed mouth and fuel tank 21 of slippage pump 5.
Its controlling method is: rope pretension first, make slide trolley with and rope in preparing acceleration mode; Then unmanned plane accelerates, and reaches unmanned aerial vehicle ejecting speed; Then slide trolley slows down, and makes unmanned plane separated with slide trolley; Finally complete after transmitting work, slide trolley starts backhaul.
As shown in Figure 2, the hardware of the low shock machine catapult-launching gear of a kind of novel unmanned plane gas-liquid pressing system comprises:
Speed control system, for quick acceleration and the low impulsive control of unmanned plane;
Movable pulley system, for the retarding braking of unmanned plane acceleration and slide trolley;
Slide trolley system, as unmanned aerial vehicle ejecting carrier, guarantees that unmanned plane boost phase is reliable.
Figure 3 shows that the low impact catapult-launching gear of unmanned plane workflow diagram, first Accumulator on Hydraulic System group accumulation of energy, movable pulley system rope pretension, then slide trolley drags unmanned plane acceleration, accelerate to after taking off speed, slide trolley slows down under buffer stopper effect, and unmanned plane departs from slide trolley and takes off, last slide trolley relies on Action of Gravity Field backhaul, enters next work cycle.
The specific works process of the embodiment of the present invention is as follows:
1) rope pretension process
Main oil pump motor 3 task driven main oil pumps 2, high pressure oil enters into accumulator 15 by the second one-way valve 12, when pressure reaches the pressure of setting (different setting values can complete launching of different type of machines), 1 automatic deloading of main oil pump electromagnetism unloading overflow valve, main oil pump motor 3 power-off simultaneously, main oil pump 2 stalls, stop to accumulator 15 fuel feeding.Meanwhile, the fluid of accumulator 15 acts on oil hydraulic motor 10 through electro-hydraulic proportion cartridge valve 11, makes reel that oil hydraulic motor 10 is connected by rope pretension, makes slide trolley and rope all be in the state of preparing acceleration.
2) unmanned plane accelerating process
Boost phase main oil pump 2 is in vehicle stop state.High pressure oil in accumulator 15 enters into oil hydraulic motor 10 by electro-hydraulic proportion cartridge valve 11, simultaneously, cartridge valve 7 is opened, the fluid that adds speed hydraulic motor 10 inside is got back to fuel tank fast through cartridge valve 7, and in fast rotational process, slippage pump motor 6 drive slippage pumps 5 through one-way valve 8 to oil hydraulic motor 10 low-pressure cavity repairings.Wherein, electro-hydraulic proportion cartridge valve 11 passing ratios regulate the control that can realize oil hydraulic motor 10 rotating speeds.
3) slide trolley moderating process
In the rope pretension stage, the electromagnet 2DT of solenoid directional control valve 18 obtains electric, and fluid is the rod chamber fuel feeding to deceleration oil hydraulic cylinder 20 through the 3rd one-way valve 14, reduction valve 16, series flow control valve 17, and the hydraulic cylinder bar that makes to slow down is regained, and carries out slide trolley and slows down and prepare.
When slide trolley moves to buffer stopper position, the piston rod of deceleration oil hydraulic cylinder is drawn out, and the acceleration that 19 pairs of dollies of hydraulic oil passing ratio relief valve of rod chamber slow down is controlled, and rodless cavity is carried out to repairing simultaneously.
4) slide trolley backhaul process
Complete after the transmitting work of unmanned plane, slide trolley is by Action of Gravity Field backhaul.
The mechanical structure of the low impact catapult-launching gear of unmanned plane of the present invention gas-liquid pressing system, as shown in Figure 4, is now described in detail as follows:
1) oil hydraulic motor reel structure
The hydraulic actuator of unmanned aerial vehicle ejecting device uses oil hydraulic motor, and two oil hydraulic motors and a rope drum are connected, and by the rotation of oil hydraulic motor, band movable reel retraction cables, accelerates slide trolley and unmanned plane.
2) movable pulley speedup structure
The effect of movable pulley acceleration system is to make unmanned plane with slide trolley, on the launching cradle of finite length, accelerate to safe take-off speed.The movement velocity of movable pulley acceleration system own is oil hydraulic motor and rotates speed, restriction due to the conditions such as properity of oil hydraulic motor self, make the rotating speed of oil hydraulic motor output and the condition that moment of torsion does not possess large-scale unmanned plane transmitting, therefore, must increase a set of acceleration system.The characteristic having due to running block meets the requirement of this acceleration system completely, and simple in structure, therefore adopt running block as speeder.
3) static pulley commutating structure
Between the oil hydraulic motor of unmanned aerial vehicle ejecting device and slide trolley, be to be connected by flexible rope, and because oil hydraulic motor is positioned at the below of slide rail, make power transmission just must take commutation to process to rope to slide trolley.
4) slide trolley structure
Slide trolley system, as the carrier that launches of unmanned plane, accelerates to unmanned plane safe take-off speed on launching cradle together with unmanned plane.The overall process of whole high-speed motion (comprising accelerating sections and the braking section) time is very short, first by the static unmanned plane taking off speed that accelerates to, is then decelerated to static.Therefore at the design aspect of slide trolley self, must consider stress complicated in acceleration and moderating process.
Coordinate design must be carried out with unmanned plane exactly in another important aspect of slide trolley structural design, need carry out according to the distribution form of unmanned plane the technical research of slide trolley and the coordinated movement of various economic factors of unmanned plane overall process.
5) slowing-down structure
Unmanned plane gas-liquid presses its function of deceleration system in ejection system to be: when unmanned plane accelerates to safe take-off speed, the kinetic energy of slide trolley is absorbed by deceleration system, and unmanned plane is separated with slide trolley and take off.Deceleration system has been the principal organ of slide trolley deceleration work after each transmitting, mainly oil hydraulic cylinder, running block, static pulley group, buffer stopper etc., consists of.
Figure 5 shows that the low impact catapult-launching gear of unmanned plane speed Control loop block diagram, electro-hydraulic proportion cartridge valve is by internal displacement sensor feedback signal, make comparisons with the given signal of spool travel, and through amplifier, signal is amplified, through controller, export corresponding control signal again, the proportion electro-magnet that arrives Proportional valve by current delivery promotes spool generation displacement, controls the rotation of oil hydraulic motor; In whole speed control system, motor drum mechanism built, by speed probe, compares by speed feedback and with given signal, then by electro-hydraulic proportion cartridge valve, unmanned plane speed is realized to closed loop control, and then realizes the quick and low impact acceleration control of unmanned plane.
Protection scope of the present invention is defined by the claims.Those skilled in the art can make various modifications or be equal to replacement the present invention in essence of the present invention and protection domain, this modification or be equal to replacement and also should be considered as dropping in protection scope of the present invention.
Claims (1)
1. the low impact catapult-launching gear of a unmanned plane gas-liquid pressing system, it is characterized in that: it is by main oil pump electromagnetism unloading overflow valve (1), main oil pump (2), main oil pump motor (3), slippage pump electromagnetism unloading overflow valve (4), slippage pump (5), slippage pump motor (6), cartridge valve (7), the first one-way valve (8) and safety valve (9) thereof, oil hydraulic motor (10), electro-hydraulic proportion cartridge valve (11), the second one-way valve (12), safety and stop valve piece (13), the 3rd one-way valve (14), accumulator (15), reduction valve (16), series flow control valve (17), solenoid directional control valve (18), proportional pressure control valve (19), deceleration oil hydraulic cylinder (20), fuel tank (21) and the oil pipe being communicated between each element form, main oil pump motor (3) drives main oil pump (2), main oil pump (2) inlet port is connected with fuel tank (21), main oil pump (2) force feed mouth is connected accumulator (15) with safety with stop valve piece (13) by the second one-way valve (12), and main oil pump electromagnetism unloading overflow valve (1) is connected across between the force feed mouth and fuel tank (21) of main oil pump (2), accumulator (15) is by electro-hydraulic proportion cartridge valve (11) connecting fluid pressure motor (10) filler opening, and oil hydraulic motor (10) return opening is connected with fuel tank (21) by cartridge valve (7), safety and stop valve piece (13) are connected with the 3rd one-way valve (14) simultaneously, and the reduction valve that is linked in sequence (16), series flow control valve (17), solenoid directional control valve (18), solenoid directional control valve (18) filler opening connects deceleration oil hydraulic cylinder (20), and its return opening connects fuel tank (21), and proportional pressure control valve (19) is connected across between deceleration oil hydraulic cylinder (20) rod chamber and rodless cavity, slippage pump motor (6) drives slippage pump (5), slippage pump (5) inlet port is connected with fuel tank (21), slippage pump (5) force feed mouth is connected with oil hydraulic motor (10) filler opening by the first one-way valve (8), and slippage pump electromagnetism unloading overflow valve (4) is connected across between the force feed mouth and fuel tank (21) of slippage pump (5).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320247045.XU CN203453160U (en) | 2013-05-08 | 2013-05-08 | Pneumatic-hydraulic system of low-impact UAV ejector |
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| CN201320247045.XU CN203453160U (en) | 2013-05-08 | 2013-05-08 | Pneumatic-hydraulic system of low-impact UAV ejector |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103277353A (en) * | 2013-05-08 | 2013-09-04 | 燕山大学 | Unmanned aerial vehicle low impact catapult pneumatic and hydraulic system |
| CN108482700A (en) * | 2018-03-07 | 2018-09-04 | 燕山大学 | A kind of pneumatic ejection system of unmanned plane |
| CN112943717A (en) * | 2021-01-28 | 2021-06-11 | 华电通用轻型燃机设备有限公司 | Hydraulic starting system for aeroderivative gas turbine generator set |
-
2013
- 2013-05-08 CN CN201320247045.XU patent/CN203453160U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103277353A (en) * | 2013-05-08 | 2013-09-04 | 燕山大学 | Unmanned aerial vehicle low impact catapult pneumatic and hydraulic system |
| CN103277353B (en) * | 2013-05-08 | 2015-06-10 | 燕山大学 | Unmanned aerial vehicle low impact catapult pneumatic and hydraulic system |
| CN108482700A (en) * | 2018-03-07 | 2018-09-04 | 燕山大学 | A kind of pneumatic ejection system of unmanned plane |
| CN112943717A (en) * | 2021-01-28 | 2021-06-11 | 华电通用轻型燃机设备有限公司 | Hydraulic starting system for aeroderivative gas turbine generator set |
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