CN105480430B - A kind of unmanned plane hydraulic catapult system - Google Patents
A kind of unmanned plane hydraulic catapult system Download PDFInfo
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- CN105480430B CN105480430B CN201510983657.9A CN201510983657A CN105480430B CN 105480430 B CN105480430 B CN 105480430B CN 201510983657 A CN201510983657 A CN 201510983657A CN 105480430 B CN105480430 B CN 105480430B
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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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
Unmanned plane hydraulic catapult system of the present invention includes hydraulic-driven part, hydraulic energy-accumulating part, hydraulic starting part, hydraulic cushion part, hydraulic braking part and hydraulic pressure oil groove and the fluid pressure line for being connected between each several part；Hydraulic-driven part includes motor, variable pump and hydraulic motor and electro-hydraulic reversing valve；Accumulation of energy part includes accumulator, electromagnetic relief valve and pressure gauge；Hydraulic starting part includes starting hydraulic cylinder and electro-hydraulic reversing valve；Hydraulic cushion part includes buffering hydraulic cylinder and electro-hydraulic reversing valve；Hydraulic braking part includes brake fluid cylinder pressure and electro-hydraulic reversing valve；Accumulator is connected with hydraulic motor simultaneously, and control valve group is in series with simultaneously on the fluid pressure line between accumulator and hydraulic motor；Braking valve group and replenishing valve are provided with hydraulic motor simultaneously；Control valve group is connected with braking valve group simultaneously.Driving force of the present invention is strong, and buffer-braking is rapid, and stable performance, reliability are adapted to the use requirement of different unmanned plane take-off weights and takeoff speed.
Description
Technical field
The invention belongs to unmanned plane lift-off technology field, more particularly to a kind of unmanned plane hydraulic catapult system.
Background technology
UAV abbreviation unmanned plane, is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Because it has small volume, low cost, easy to use, low to operational environment requirement, battlefield survival stronger
The advantages of, the favor of all armies in the world is enjoyed, it is widely used in military field.Additionally, countries in the world are all in product at present
The range of application of civilian unmanned plane is expanded in pole, in fields such as electric power, communication, meteorology, agricultural, ocean, explorations using unmanned plane
Technique effect and economic effect are all expected very much.
With extensive use of the unmanned plane in social each field, the emitter for matching therewith has also been obtained sufficiently
Development, in the whole work process of unmanned plane, launching phase is often referred to as one of most difficult, most important stage, mesh
The preceding launch both at home and abroad to unmanned plane has made substantial amounts of research and trial, and has achieved certain achievement.The hair of unmanned plane
Penetrate mode numerous, such as hand throwing, airborne dispensing, vehicle transmitting, ejection, rocket assist transmitting.Equipment is launched in wherein rolling start
Overload that is simple and reliable, accelerating is small, low cost, but, maneuverability harsh to environmental requirement is poor；Electromagnetic launch combustion gas ejection is only
Possessed some special knowledge in a small number of developed countries, the country there is no research；Elastic force ejection is only applicable to small-sized unmanned plane；Rocket assist is launched
Floor space is small, early investment is low, small, adaptability affected by environment preferably, but is related to the storage of priming system, transports and make
With, potential safety hazard is big, range of application is narrow；Gas fluid pressure launch good property safe and out of sight, good economy performance, adaptability it is good, can continuous several times
Use.
Learnt according to related data investigation, rocket assist transmitting is unmanned plane radiation pattern the most frequently used at present, and unmanned plane
The hydraulic catapult mode of taking off is a kind of advanced unmanned plane radiation pattern for occurring in the world in recent years, compared with the former, is had
Property safe and out of sight is good, good economy performance, good adaptability the advantages of, the signals such as light, sound, heat, smog will not be produced, be easy to take-off venue
Hidden, storage in the absence of fire control equipment, transport and problem of management, and carry out every time when unmanned plane is launched consumable supplies and
Support the expense for ensureing relatively low.Hydraulic catapult launching apparatus are mountable on carrier loader, are easy to maneuver warfare and transport to shift, by
This device has good maneuverability again.
By the advantage and disadvantage of each radiation pattern of comprehensive analysis, the state-of-art with reference to current China, research and design one
Kind driving force is strong, buffer-braking is effective, can adapt to the bullet of the use requirement in different unmanned plane take-off weights and takeoff speed
Hydraulic system is penetrated, tool is of great significance.
The content of the invention
The technical problem to be solved in the present invention is exactly to overcome above-mentioned the deficiencies in the prior art, and provide a kind of driving force it is strong,
Buffer-braking effectively, can adapt to the unmanned plane hydraulic catapult of the use requirement in different unmanned plane take-off weights and takeoff speed
System.
In order to solve the above technical problems, the technical scheme is that：
Design a kind of unmanned plane hydraulic catapult system, including hydraulic-driven part, hydraulic energy-accumulating part, hydraulic starting portion
Point, hydraulic cushion part, hydraulic braking part and hydraulic pressure oil groove and the fluid pressure line for being connected between each several part；Wherein,
Hydraulic-driven part includes motor, variable pump and hydraulic motor, is in series with the fluid pressure line between variable pump and hydraulic motor
Electro-hydraulic reversing valve；
Accumulation of energy part includes accumulator, the accumulator and variable series connection of pumps, the hydraulic tube between accumulator and variable pump
Electromagnetic relief valve and pressure gauge are in series with road simultaneously；
Hydraulic starting part includes starting hydraulic cylinder, the startup hydraulic cylinder and variable series connection of pumps, is starting hydraulic cylinder and is becoming
Electro-hydraulic reversing valve is in series with fluid pressure line between amount pump simultaneously；
Hydraulic cushion part includes buffering hydraulic cylinder, the buffering hydraulic cylinder and variable series connection of pumps, in buffering hydraulic cylinder and change
Electro-hydraulic reversing valve is in series with fluid pressure line between amount pump simultaneously；
Hydraulic braking part includes brake fluid cylinder pressure, the brake fluid cylinder pressure and variable series connection of pumps, in brake fluid cylinder pressure and change
Electro-hydraulic reversing valve is in series with fluid pressure line between amount pump simultaneously；
The accumulator is connected with hydraulic motor simultaneously, is gone here and there simultaneously on the fluid pressure line between accumulator and hydraulic motor
It is associated with control valve group；
Braking valve group and replenishing valve are provided with the hydraulic motor simultaneously；Control valve group is connected with braking valve group simultaneously；Fill
The electro-hydraulic reversing valve that liquid valve is connected with control valve group with brake fluid cylinder pressure respectively simultaneously is connected；Contain the time in braking valve group
Relay.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the fluid pressure line includes hydraulic main circuit and hydraulic pressure branch
Pipeline, wherein variable pump are arranged on hydraulic main circuit, hydraulic motor, accumulator, startup hydraulic cylinder, buffering hydraulic cylinder and braking
Hydraulic cylinder is mounted in parallel on hydraulic pressure bye-pass respectively.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the liquid where the oil inlet and oil-out of the variable pump
Filter is respectively equipped with pressure main line.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic pressure branch pipe between accumulator and variable pump
On road simultaneously be in series with check valve, the wherein oil inlet of check valve is connected with the oil-out of variable pump, the oil-out of check valve and
The oil inlet of accumulator is connected.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic pressure branch pipe where the buffering hydraulic cylinder oil inlet
Restriction is provided with simultaneously on road, check valve, the wherein oil inlet of check valve and section are in series between the restriction and hydraulic pressure oil groove
Head piece is connected, and the oil-out of check valve is connected with hydraulic pressure oil groove.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic motor has multiple, and is connected in parallel.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the accumulator has multiple, and is connected in parallel.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the electromagnetic relief valve is pilot operated electromagnetic relief valve.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, pacify on the hydraulic pressure bye-pass where the startup hydraulic cylinder
The electro-hydraulic reversing valve of dress is two-bit triplet electro-hydraulic reversing valve；That is installed on the hydraulic pressure bye-pass where the brake fluid cylinder pressure is electro-hydraulic
Reversal valve is two four-way electro-hydraulic reversing valves.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic pressure where the hydraulic motor and buffering hydraulic cylinder
The electro-hydraulic reversing valve installed on bye-pass is 3-position 4-way electro-hydraulic reversing valve.
Preferably, in above-mentioned unmanned plane hydraulic catapult system, the startup hydraulic cylinder, buffering hydraulic cylinder and brake fluid pressure
Cylinder is respectively high speed hydraulic cylinder.
Operation principle of the invention：
The operation principle of unmanned plane hydraulic catapult system of the present invention is, for unmanned aerial vehicle ejecting provides power, to drive ejection carrier
The unmanned plane of loading carries out accelerating to safe take-off speed on launching cradle, when the speed that ejection carrier is moved together with unmanned plane
When reaching takeoff speed, power source is cut off, ejection carrier is buffered absorption systems to be stopped and be a significant slowdown, and unmanned plane is then used
Property and motor power in the presence of separate and take off from ejection carrier with takeoff speed.
The beneficial effect of technical solution of the present invention is：
Unmanned plane hydraulic catapult system of the present invention can launch as the core of unmanned plane emitter for unmanned plane
Sufficient power is provided；Wherein accumulator can the substantial amounts of hydraulic oil of instantaneous relase, unmanned plane can be made instantaneously to reach larger rising
Rapidly spend.Whole fluid power system is broadly divided into five stages：Accumulator pressurizing, hydraulic oil instantaneous relase start, launch, delay
Punching is moved and piston return.During accumulator pressurizing, electromagnetic relief valve is powered, and variable pump carries out oil-filled to accumulator, treats that it reaches
After the precharge pressure of regulation, electromagnetic relief valve power-off, pump off-load；Hydraulic oil instantaneous relase starts, and starts hydraulic cylinder works；Ejection
When, the fluid in accumulator and variable pump drives hydraulic motor, hydraulic motor to be driven by steel wire rope and drag load dolly and nothing jointly
Man-machine high-speed motion, when drag carry dolly and reach guide rail top when, drag load dolly to reduce speed now buffering, unmanned plane then drag rapidly by disengaging
Dolly is carried to take off；When dragging load dolly to return, motor is rotated backward, and is driven by steel wire rope and is dragged load dolly to return to original place.Entirely
Process drives hydraulic motor jointly using accumulator and variable pump, and driving force is strong；Buffer-braking aspect, except being delayed using hydraulic cylinder
Punching is dynamic outer, while being braked to rope sheave using hydraulic power system and liquid braking device, buffer-braking is rapid；And,
Overall performance stabilization, reliable, pipe-line layout is compact, reasonable, is adapted to different unmanned plane take-off weights and takeoff speed
Use requirement.Thus, it is suitable to promotion and implementation.
Brief description of the drawings
Specific embodiment of the invention is described in further detail below in conjunction with the accompanying drawings, wherein：
Fig. 1 is the schematic diagram of unmanned plane hydraulic catapult system of the present invention；
Fig. 2 is the workflow diagram of unmanned plane hydraulic catapult system of the present invention；
Sequence number in figure：1st, motor, 2, variable pump, 3, pilot operated electromagnetic relief valve, 4, pressure gauge, 5,6,7,18, electro-hydraulic change
To valve, 8, self-control restriction, 9,19, check valve, 10, self-control buffering hydraulic cylinder, 11, self-control start hydraulic cylinder, 12, self-control braking
Hydraulic cylinder, 13, accumulator, 14, control valve group, 15, hydraulic motor, 16, braking valve group, 17, replenishing valve, 20, filter.
Specific embodiment
Below in conjunction with the accompanying drawing in the present invention, clearly complete retouching is carried out to the technical scheme in the embodiment of the present invention
State, it is clear that described embodiment is only schematical part specific embodiment of the invention, is not limited to of the invention
Scope, the equivalent variations that any those skilled in the art is made on the premise of present inventive concept and principle is not departed from repair
Change, the scope of protection of the invention all should be belonged to.
Referring to Fig. 1, in figure, unmanned plane hydraulic catapult system of the present invention, including hydraulic-driven part, hydraulic energy-accumulating part,
Hydraulic starting part, hydraulic cushion part, hydraulic braking part and hydraulic pressure oil groove and the hydraulic pressure for being connected between each several part
Pipeline；Wherein, hydraulic-driven part includes motor 1, variable pump 2 and hydraulic motor 15, the liquid between variable pump and hydraulic motor
Electro-hydraulic reversing valve 18 is in series with pressure pipe road；Accumulation of energy part includes accumulator 13, the accumulator and variable series connection of pumps, in accumulator
Electromagnetic relief valve 3 and pressure gauge 4 are in series with fluid pressure line between variable pump simultaneously；Hydraulic starting part includes starting liquid
Cylinder pressure 11, the startup hydraulic cylinder and variable series connection of pumps, connect simultaneously on the fluid pressure line started between hydraulic cylinder and variable pump
There is electro-hydraulic reversing valve 6；Hydraulic cushion part includes buffering hydraulic cylinder 10, the buffering hydraulic cylinder and variable series connection of pumps, in buffer solution
Electro-hydraulic reversing valve 7 is in series with fluid pressure line between cylinder pressure and variable pump simultaneously；Hydraulic braking part includes brake fluid cylinder pressure
12, the brake fluid cylinder pressure and variable series connection of pumps are in series with electricity simultaneously on the fluid pressure line between brake fluid cylinder pressure and variable pump
Liquid reversal valve 5；The accumulator is connected with hydraulic motor simultaneously, on the fluid pressure line between accumulator and hydraulic motor simultaneously
It is in series with control valve group 14；Braking valve group 16 and replenishing valve 17 are provided with the hydraulic motor simultaneously；Control valve group simultaneously with system
Dynamic valve group connection；The electro-hydraulic reversing valve that replenishing valve is connected with control valve group with brake fluid cylinder pressure respectively simultaneously is connected；Brake valve
Contain the time relay in group.
Referring to Fig. 2, the workflow of whole hydraulic system is broadly divided into five stages：That is accumulator pressurizing, hydraulic oil wink
When release start, ejection, buffer-braking and piston return.During accumulator pressurizing, electromagnetic relief valve 3 is powered, and variable pump 2 is by single
Accumulator 13 is carried out to valve 19 oil-filled, after after its precharge pressure for reaching regulation, electromagnetic relief valve 3 is powered off, pump off-load；High pressure
When oily instantaneous relase starts, electro-hydraulic reversing valve 6 is opened, and self-control starts hydraulic cylinder 11 and works；During ejection, electromagnetic relief valve 3 and electricity
Liquid reversal valve 5,6 is powered, and replenishing valve 17 is reversely opened, and the fluid in accumulator and variable pump drives hydraulic motor 15, hydraulic pressure horse
Load dolly and unmanned plane high-speed motion are dragged up to being driven by steel wire rope, when dragging load dolly to reach guide rail top, stroke is touched
Switch, travel switch work, electro-hydraulic reversing valve 5,6 is powered off, and drags load dolly to reduce speed now buffering, and unmanned plane then departs from and drags load dolly
Take off；When dragging load dolly to return, electromagnetic relief valve 3 is powered, and the right-hand member of electro-hydraulic reversing valve 7 is powered, and motor is rotated backward, by steel wire
Rope band is dynamic to drag load dolly to return to original place.Whole process drives hydraulic motor jointly using accumulator and variable pump, and driving force is strong；
Buffer-braking aspect, in addition to using hydraulic cylinder buffer-braking, while using hydraulic power system and liquid braking device come to rope
Wheel is braked, and buffer-braking is rapid；And, overall performance stabilization, reliability, pipe-line layout are compact, reasonable, are adapted to not
With unmanned plane take-off weight and the use requirement of takeoff speed, it is suitable to promotion and implementation.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the fluid pressure line includes liquid
Pressure main line and hydraulic pressure bye-pass, wherein variable pump be arranged on hydraulic main circuit on, hydraulic motor, accumulator, start hydraulic cylinder,
Buffering hydraulic cylinder and brake fluid cylinder pressure are mounted in parallel on hydraulic pressure bye-pass respectively.The pipeline structure is compact, rationally distributed, saves
Length of pipe.
In a specific embodiment of the invention, referring to Fig. 1, in figure, in above-mentioned unmanned plane hydraulic catapult system, the change
Filter 20 is respectively equipped with hydraulic main circuit where measuring the oil inlet and oil-out of pump.The setting of filter is to entering system
The hydraulic oil of each component is filtered, to improve the service life of each hydraulic component.
In a specific embodiment of the invention, referring to Fig. 1, in figure, in above-mentioned unmanned plane hydraulic catapult system, it is described
Check valve 19, the wherein oil inlet and variable pump of check valve are in series with hydraulic pressure bye-pass between accumulator and variable pump simultaneously
Oil-out be connected, the oil-out of check valve is connected with the oil inlet of accumulator.The setting of the check valve can be prevented because of hydraulic pressure
Oil flows back and the loss of build-up of pressure.
It is described slow in above-mentioned unmanned plane hydraulic catapult system in figure referring to Fig. 1 in a specific embodiment of the invention
While being provided with restriction 8 on hydraulic pressure bye-pass where rushing hydraulic cylinder oil inlet, it is in series between the restriction and hydraulic pressure oil groove
The oil inlet of check valve 9, wherein check valve is connected with restriction, and the oil-out of check valve is connected with hydraulic pressure oil groove.The restriction
And the setting of check valve can prevent the loss of build-up of pressure because of hydraulic oil backflow.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic motor has two,
And be connected in parallel.Two or more hydraulic motors are arranged in parallel, and the driving force of abundance can be provided for unmanned plane transmitting.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the accumulator has two, and
It is connected in parallel.Two or more accumulators are arranged in parallel, and can store more multi-energy, then instantaneous relase so that nobody
Machine instantaneously reaches larger takeoff speed.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the electromagnetic relief valve is for first
Conduction electromagnetic relief valve.Using pilot operated electromagnetic relief valve so that overall structure is simpler, compact, and it is easy to buying, it is raw
Produce use cost also low.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, where the startup hydraulic cylinder
Hydraulic pressure bye-pass on install electro-hydraulic reversing valve be two-bit triplet electro-hydraulic reversing valve；Hydraulic pressure branch where the brake fluid cylinder pressure
The electro-hydraulic reversing valve installed on pipeline is two four-way electro-hydraulic reversing valves.Using two-bit triplet, two four-way electro-hydraulic reversing valves, make
Obtain overall structure simpler, compact, and be easy to buying, production and application cost is also low.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the hydraulic motor and buffering
The electro-hydraulic reversing valve installed on hydraulic pressure bye-pass where hydraulic cylinder is 3-position 4-way electro-hydraulic reversing valve.It is electro-hydraulic using 3-position 4-way
Reversal valve so that overall structure is simpler, compact, and it is easy to buying, production and application cost is also low.
In a specific embodiment of the invention, in above-mentioned unmanned plane hydraulic catapult system, the startup hydraulic cylinder, buffering
Hydraulic cylinder and brake fluid cylinder pressure are respectively high speed hydraulic cylinder.Using high speed hydraulic cylinder, agile, fast response time, conversion is fast,
Fully meet the use requirement that unmanned plane takes off.
Each embodiment is described by the way of progressive in this specification, and what each embodiment was stressed is and it
The difference of its embodiment, identical similar part is cross-referenced between each embodiment.
To the described above of disclosed embodiment, those skilled in the art is realized or use the present invention.To these
The many places modification of embodiment is apparent to those skilled in the art, and generic principles defined herein can be
On the premise of not departing from the spirit or scope of invention, realize in other embodiments.Therefore, the present invention will be not restricted to this paper institutes
These embodiments of display, and it is to fit to the widest range consistent with principles disclosed herein and features of novelty.
Claims (10)
1. a kind of unmanned plane hydraulic catapult system, it is characterized in that：Including hydraulic-driven part, hydraulic energy-accumulating part, hydraulic starting
Partly, hydraulic cushion part, hydraulic braking part and hydraulic pressure oil groove and the fluid pressure line for being connected between each several part；Its
In, hydraulic-driven part includes motor, variable pump and hydraulic motor, is connected on the fluid pressure line between variable pump and hydraulic motor
There is electro-hydraulic reversing valve；
Accumulation of energy part includes accumulator, the accumulator and variable series connection of pumps, on the fluid pressure line between accumulator and variable pump
It is in series with electromagnetic relief valve and pressure gauge simultaneously；
Hydraulic starting part includes starting hydraulic cylinder, the startup hydraulic cylinder and variable series connection of pumps, is starting hydraulic cylinder and variable pump
Between fluid pressure line on simultaneously be in series with electro-hydraulic reversing valve；
Hydraulic cushion part includes buffering hydraulic cylinder, the buffering hydraulic cylinder and variable series connection of pumps, in buffering hydraulic cylinder and variable pump
Between fluid pressure line on simultaneously be in series with electro-hydraulic reversing valve；
Hydraulic braking part includes brake fluid cylinder pressure, the brake fluid cylinder pressure and variable series connection of pumps, in brake fluid cylinder pressure and variable pump
Between fluid pressure line on simultaneously be in series with electro-hydraulic reversing valve；
The accumulator is connected with hydraulic motor simultaneously, is in series with simultaneously on the fluid pressure line between accumulator and hydraulic motor
Control valve group；
Braking valve group and replenishing valve are provided with the hydraulic motor simultaneously；Control valve group is connected with braking valve group simultaneously；Replenishing valve
The electro-hydraulic reversing valve connected with brake fluid cylinder pressure with control valve group respectively simultaneously is connected；Contain time relay in braking valve group
Device.
2. unmanned plane hydraulic catapult system according to claim 1, it is characterized in that：The fluid pressure line includes hydraulic main
Road and hydraulic pressure bye-pass, wherein variable pump are arranged on hydraulic main circuit, hydraulic motor, accumulator, startup hydraulic cylinder, buffer solution
Cylinder pressure and brake fluid cylinder pressure are mounted in parallel on hydraulic pressure bye-pass respectively.
3. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：The oil inlet of the variable pump and fuel-displaced
Filter is respectively equipped with hydraulic main circuit where mouthful.
4. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：It is described between accumulator and variable pump
Hydraulic pressure bye-pass on simultaneously be in series with check valve, the wherein oil inlet of check valve is connected with the oil-out of variable pump, check valve
Oil-out be connected with the oil inlet of accumulator.
5. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：Where the buffering hydraulic cylinder oil inlet
Hydraulic pressure bye-pass on be simultaneously provided with restriction, be in series with check valve between the restriction and hydraulic pressure oil groove, wherein check valve
Oil inlet is connected with restriction, and the oil-out of check valve is connected with hydraulic pressure oil groove.
6. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：The hydraulic motor has multiple, and simultaneously
It is linked togather；The accumulator has multiple, and is connected in parallel.
7. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：The electromagnetic relief valve is pilot-operated type electricity
Magnetic overflow valve.
8. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：Hydraulic pressure where the startup hydraulic cylinder
The electro-hydraulic reversing valve installed on bye-pass is two-bit triplet electro-hydraulic reversing valve；On hydraulic pressure bye-pass where the brake fluid cylinder pressure
The electro-hydraulic reversing valve of installation is two four-way electro-hydraulic reversing valves.
9. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：The hydraulic motor and buffering hydraulic cylinder
The electro-hydraulic reversing valve installed on the hydraulic pressure bye-pass at place is 3-position 4-way electro-hydraulic reversing valve.
10. unmanned plane hydraulic catapult system according to claim 2, it is characterized in that：The startup hydraulic cylinder, buffering hydraulic
Cylinder and brake fluid cylinder pressure are respectively high speed hydraulic cylinder.
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| CN107458585B (en) * | 2017-08-11 | 2020-05-08 | 温州铭泰工业设计有限公司 | Small unmanned aerial vehicle wheel brake mechanism |
| CN108116691B (en) * | 2017-12-29 | 2021-03-19 | 郑州光之源电子科技有限公司 | Hydraulic ejection method of unmanned aerial vehicle |
| CN113357205B (en) * | 2021-06-16 | 2022-11-29 | 浙江大学 | Gas-liquid ejection servo actuating system |
| CN114436164B (en) * | 2021-11-24 | 2023-09-08 | 广西电网有限责任公司北海供电局 | Electric repair tower lifting leveling device and method |
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| DE3314763C2 (en) * | 1983-04-23 | 1986-07-03 | Hydro Gerätebau GmbH & Co KG Hebezeuge, 7616 Biberach | Device for external ventilation, heating, cooling and air conditioning of aircraft on the ground or the like. |
| FR2560569B1 (en) * | 1984-03-05 | 1992-09-04 | Fmc Corp | HYDRAULIC AND ELECTRICAL SYSTEM FOR A BELT LOADER FOR AN AIRCRAFT |
| CN101195414A (en) * | 2006-12-04 | 2008-06-11 | 胡宣哲 | Numerical controlled constant power ejection method and device |
| CN103277353B (en) * | 2013-05-08 | 2015-06-10 | 燕山大学 | Unmanned aerial vehicle low impact catapult pneumatic and hydraulic system |
| CN205366099U (en) * | 2015-12-24 | 2016-07-06 | 郑州彩通科技股份有限公司 | Unmanned aerial vehicle hydraulic pressure system of launching |
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