CN104500459B - Realize the hydraulic pressure weight balancing system of microgravity environment - Google Patents
Realize the hydraulic pressure weight balancing system of microgravity environment Download PDFInfo
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- CN104500459B CN104500459B CN201410753102.0A CN201410753102A CN104500459B CN 104500459 B CN104500459 B CN 104500459B CN 201410753102 A CN201410753102 A CN 201410753102A CN 104500459 B CN104500459 B CN 104500459B
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- Prior art keywords
- hydraulic cylinder
- accumulator
- pressure
- chorista
- hydraulic
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B1/00—Installations or systems with accumulators; Supply reservoir or sump assemblies
- F15B1/02—Installations or systems with accumulators
- F15B1/024—Installations or systems with accumulators used as a supplementary power source, e.g. to store energy in idle periods to balance pump load
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/02—Systems essentially incorporating special features for controlling the speed or actuating force of an output member
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B19/00—Testing; Calibrating; Fault detection or monitoring; Simulation or modelling of fluid-pressure systems or apparatus not otherwise provided for
- F15B19/007—Simulation or modelling
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
Abstract
The invention provides a kind of hydraulic pressure weight balancing system realizing microgravity environment, including: hydraulic cylinder, accumulator package, servo pump station, servo control module；The present invention is connected with aircraft chorista by hydraulic cylinder piston rod, servo-control system is utilized to control servo pump station output pressure, hydraulic cylinder output loads is made to keep consistent with aircraft chorista gravity, when separation test is carried out, separation nut unlocks, chorista separates with by chorista by separation nut spring force, move upward, now, hydraulic cylinder piston rod moves upwardly together therewith, in hydraulic cylinder piston rod motion process, hydraulic cylinder cavity volume increases, accumulator is to hydraulic cylinder fluid infusion, supplementary pressure, hydraulic cylinder output loads is made to keep consistent with aircraft chorista gravity, accumulator ftercompction response time ＜ 5ms, guarantee that separation test is carried out under microgravity environment, ensure that the validity of test, authenticity.
Description
Technical field
The present invention relates to use hanging method to carry out Separation Test Technology field, a kind of microgravity environment that realizes
Hydraulic pressure weight balancing system.
Background technology
At present, each chorista separation can be carried out during the space product flight in-orbit such as aircraft.Set for checking separating mechanism
Meter correctness and reasonability, and separating mechanism normal temperature condition under separation function, its each parts need to be carried out ground
Face separation test.Hanging method exclusion assay is a kind of exclusion assay conventional in surface separation test, for
The working environment that true simulated flight device flies when separating in-orbit and microgravity environment, test generally uses suspension join
The method of weight carrys out equilibrium separation body weight power, to carry out separation test.
Counterweight method is used to carry out separation test, owing to chorista mass property differs more than one times with virtual condition, point
In vitro speed is big with virtual condition difference, and does not adapt to the separate acceleration released state more than acceleration of gravity,
Therefore for guaranteeing that separation test is carried out under chorista real operating environments, hydraulic pressure weight balancing system balance point is used
In vitro gravity, the separation process under true stimulated microgravity.
Summary of the invention
For defect of the prior art, it is an object of the invention to provide a kind of hydraulic pressure gravity realizing microgravity environment
Balance system.
A kind of hydraulic pressure weight balancing system realizing microgravity environment provided according to the present invention, including: hydraulic cylinder, storage
Can device assembly, servo pump station, servo control module；
The joint of hydraulic cylinder piston rod is used for connecting chorista；
Servo control module is before separating experiment is carried out, and control servo pump station, to hydraulic cylinder output pressure, makes hydraulic cylinder
Output loads and the gravity of chorista keep consistent；
Accumulator package in separating experiment is carried out body to be separated with separated by chorista after, to hydraulic cylinder fluid infusion, make
The output loads of hydraulic cylinder keeps consistent with the gravity of chorista, and i.e. at hydraulic cylinder, pressure changes, accumulator
Hydraulic oil is pressed in hydraulic cylinder cavity volume by assembly inner high voltage gas, it is ensured that cylinder pressure is constant；
Servo pump station is accumulator package voltage supply.
Preferably, the cylinder body leading section near hydraulic cylinder is provided with that be evenly distributed and quantity is equal with accumulator package
Multiple screws, the plurality of screw is spirally connected with the stud bottom corresponding accumulator package connection respectively；At the bottom of accumulator package
Fuel feed hole and spill port that portion is arranged are connected with servo pump station respectively, and accumulator package top is provided with punching hole for carrying out
Punching press；
The cylinder body leading section of hydraulic cylinder is provided with hydraulic cylinder stud, and hydraulic cylinder stud is connected with taking out Lou pump by connecting line,
Take out Lou pump and connect servo pump station, take out the hydraulic oil that Lou hydraulic cylinder is spilt by pump and draw back in servo pump station；The cavity volume of hydraulic cylinder
Rear end is provided with buffer structure and buffers to provide to the hydraulic cylinder piston rod retracted, and hydraulic cylinder piston rod is positioned at buffer structure
Front side.
Preferably, accumulator package, particularly as follows:
V: accumulator total measurement (volume)
Δ V: accumulator delivery volume
P0: charging pressure of accumulator.
P1: accumulator minimum operating pressure
P2: accumulator maximum working pressure
K: accumulator adiabatic coefficent
Preferably, servo pump station provides rated pressure 21MPa, the hydraulic load of metered flow 10L/min, and provides
Initial pressure；Accumulator package is bag type accumulator；Hydraulic cylinder completes oil-feed and works with oil return, and hydraulic cylinder exports
After pressure P has set, when hydraulic cylinder piston rod moves, hydraulic cylinder cavity volume V becomes big, now with liquid
The accumulator package that cylinder pressure connects responds to hydraulic cylinder supplementary pressure, makes cylinder device output pressure P constant.
Compared with prior art, the present invention has a following beneficial effect:
The present invention is connected with aircraft chorista by hydraulic cylinder piston rod, utilizes servo-control system to control servopump
Stand output pressure, make hydraulic cylinder output loads keep consistent with aircraft chorista gravity, when separation test is carried out,
Separation nut unlocks, and chorista separates with by chorista by separation nut spring force, moves upward, now, and liquid
Pressure cylinder piston bar moves upwardly together therewith, and in hydraulic cylinder piston rod motion process, hydraulic cylinder cavity volume increases,
Accumulator, to hydraulic cylinder fluid infusion, supplementary pressure, makes hydraulic cylinder output loads keep consistent with aircraft chorista gravity,
Accumulator ftercompction response time ＜ 5ms, it is ensured that separation test is carried out under microgravity environment, it is ensured that test effective
Property, authenticity.
Accompanying drawing explanation
By the detailed description non-limiting example made with reference to the following drawings of reading, the further feature of the present invention,
Purpose and advantage will become more apparent upon:
Fig. 1 is overall structure schematic diagram of the present invention；
Fig. 2 is that the present invention hangs method separation test schematic diagram；
Fig. 3 is present hydraulic cylinder schematic diagram；
Fig. 4 is accumulator package schematic diagram of the present invention；
Fig. 5 be the present invention be accumulator package of the present invention and hydraulic cylinder connection diagram；
In figure: 1 is hydraulic cylinder, 2 is accumulator package, and 3 is connecting line, and 4 is servo control module, and 5 are
Servo pump station, 6 is aircraft chorista, 7 be aircraft by chorista, 31 is hydraulic cylinder mounting flange, and 32 are
Hydraulic cylinder mounting flange installing hole, 33 is buffering structure of hydraulic cylinder, and 34 is hydraulic cylinder piston rod, and 35 is hydraulic cylinder
Screw, 36 is hydraulic cylinder stud, and 41 is accumulator fuel feed hole, and 42 is accumulator spill port, 43 be accumulator with
Hydraulic cylinder connecting stud, 44 is accumulator punching hole.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in those skilled in the art
Member is further appreciated by the present invention, but limits the present invention the most in any form.It should be pointed out that, the common skill to this area
For art personnel, without departing from the inventive concept of the premise, it is also possible to make some deformation and improvement.These broadly fall into
Protection scope of the present invention.
The invention discloses a kind of hydraulic pressure weight balancing system realizing microgravity environment, including hydraulic cylinder, accumulator package,
Servo pump station, servo control module and connecting line.The cylinder body front end of described hydraulic cylinder is provided with and is connected with accumulator package
Joint and with take out Lou pump jointing, be connected with test body at piston rod attachment, export load consistent with test body weight.
In described accumulator package, upper end is gases at high pressure, and lower end is hydraulic oil, and connects with hydraulic cylinder and servo pump station, passes through
Servo pump station is to accumulator package voltage supply, and at hydraulic cylinder, pressure changes, and accumulator package inner high voltage gas is by hydraulic pressure
Oil pressure enters in hydraulic cylinder cavity volume, it is ensured that cylinder pressure is constant.Described servo pump station can provide rated pressure 21MPa, volume
The hydraulic load of constant flow 10L/min, provides initial pressure for whole system.Described servo control module is by electro-hydraulic servo
Valve, controller and control software composition, for control system output pressure.Described connecting line passes through high-pressure oil pipe by liquid
Cylinder pressure, accumulator package and servo pump station connect.The present invention realizes the hydraulic pressure gravitational equilibrium system of microgravity environment by this
The use of system, can export a certain permanent load, and then stimulated microgravity in hydraulic cylinder piston rod motion process,
Meet chorista in separation test in the separation process demand to microgravity environment, effectively improve the test of separation test
Means, it is ensured that the validity of testing program, authenticity.
Specifically, the system provided according to the present invention, including:
Hydraulic cylinder 1, its body format is tubular structure, and described hydraulic cylinder 1 arranges a mounting flange at rear end of the cylinder block,
Fixing for hydraulic cylinder integral installation, piston rod cavity volume rear end arranges buffer structure, and described hydraulic cylinder 1 is near cylinder body front end
Place is provided with four screws being uniformly distributed along the circumference, and described hydraulic cylinder 1 is provided with a stud at cylinder body front end；
Accumulator package 2, its body format is cylindrical, is set to stud bottom described accumulator package 2, can be with liquid
Screw on cylinder pressure cylinder body is spirally connected, the fuel feed hole that bottom is arranged.
Connecting line 3, the most high pressure resistant pipeline, for the connection of other parts of system, make system composition entirety.
Servo control module 4, described servo control module 4 is main by electrohydraulic servo valve, high-precision pressure gauge, controller
And control software composition, for control system output pressure.The control accuracy of servo control module is 0.5%.
Servo pump station 5, described servo pump station 5 can provide rated pressure 21MPa, the hydraulic pressure of metered flow 10L/min carries
Lotus, provides initial pressure for whole system.
As in figure 2 it is shown, described hydraulic cylinder piston rod 34 is connected with aircraft chorista 6, utilize servo control module 4
Control servo pump station 5 output pressure, make hydraulic cylinder 1 output loads keep consistent with aircraft chorista 6 gravity, dividing
When separating test is carried out, separation nut unlocks, and chorista 6 separates with by chorista 7 by separation nut spring force, upwards
Motion, now, hydraulic cylinder piston rod 34 moves upwardly together therewith, in hydraulic cylinder piston rod 34 motion process, liquid
Cylinder pressure 1 cavity volume increase, accumulator package 2 to hydraulic cylinder fluid infusion, supplementary pressure, make hydraulic cylinder 1 output loads with
Aircraft chorista 6 gravity keeps consistent, accumulator package 2 ftercompction response time ＜ 5ms, it is ensured that separation test is micro-
Carry out under gravity environment.
As shown in Fig. 3, Fig. 4 and Fig. 5, arrange at cylinder body front end four of described hydraulic cylinder 1 are uniformly distributed along the circumference
The stud 43 arranged bottom screw 35 and four groups of accumulator package 2 is spirally connected, the fuel feed hole arranged bottom accumulator package 2
41 and spill port 42 be connected with servo pump station 5 by connecting line 3, by punching hole 44, accumulator package 2 is carried out
Punching press.
Accumulator package selection principle is:
V: accumulator total measurement (volume) (L)
Δ V: delivery volume (L)
P0: the blowing pressure (MPa)
P1: minimum operating pressure (MPa)
P2: maximum working pressure (MPa)
K: adiabatic coefficent
The hydraulic pressure weight balancing system provided by means of above-described embodiment is provided below in conjunction with the accompanying drawings, is not affecting separation
On the premise of test experimental enviroment, meet the space product hanging method separation test need to microgravity test environment such as aircraft
Ask.
During installation, as in figure 2 it is shown, first accumulator package 2 to be mounted on test tower frame cross beam upper end, hydraulic cylinder
1 is mounted on test tower frame cross beam lower end by mounting flange 31, and hydraulic cylinder 1 passes through hydraulic cylinder piston rod 34 and flies
Row device chorista 6 connects, and hydraulic cylinder 1 is connected by connecting line 3 with accumulator package 2, entering of accumulator package 2
Oilhole 41 and spill port 42 are connected with servo pump station 5 by connecting line 3, and servo control module 4 is by controlling cable
Being connected with system, hydraulic cylinder 1 is attached with taking out Lou pump by connecting line 3, takes out Lou pump and passes through connecting line 3 and watch
Take pumping plant 5 to connect.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in
Stating particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims,
This has no effect on the flesh and blood of the present invention.
Claims (3)
1. the hydraulic pressure weight balancing system realizing microgravity environment, it is characterised in that including: hydraulic cylinder, accumulation of energy
Device assembly, servo pump station, servo control module；
The joint of hydraulic cylinder piston rod is used for connecting chorista；
Servo control module is before separating experiment is carried out, and control servo pump station, to hydraulic cylinder output pressure, makes hydraulic cylinder
Output loads and the gravity of chorista keep consistent；
Accumulator package in separating experiment is carried out body to be separated with separated by chorista after, to hydraulic cylinder fluid infusion, make
The output loads of hydraulic cylinder keeps consistent with the gravity of chorista；
Servo pump station is accumulator package voltage supply；
The cylinder body leading section of hydraulic cylinder is provided with that be evenly distributed and that quantity is equal with accumulator package multiple spiral shells
Hole, the plurality of screw is spirally connected with the stud bottom corresponding accumulator package connection respectively；Arrange bottom accumulator package
Fuel feed hole and spill port be connected with servo pump station respectively, accumulator package top is provided with punching hole for carrying out punching press；
The cylinder body leading section of hydraulic cylinder is provided with hydraulic cylinder stud, and hydraulic cylinder stud is connected with taking out Lou pump by connecting line,
Take out Lou pump and connect servo pump station, take out the hydraulic oil that Lou hydraulic cylinder is spilt by pump and draw back in servo pump station；The cavity volume of hydraulic cylinder
Rear end is provided with buffer structure, and hydraulic cylinder piston rod is positioned at the front side of buffer structure.
The hydraulic pressure weight balancing system realizing microgravity environment the most according to claim 1, it is characterised in that store
Energy device assembly, particularly as follows:
V: accumulator total measurement (volume)
Δ V: accumulator delivery volume
P0: charging pressure of accumulator
P1: accumulator minimum operating pressure
P2: accumulator maximum working pressure
K: accumulator adiabatic coefficent.
The hydraulic pressure weight balancing system realizing microgravity environment the most according to claim 1, it is characterised in that watch
Take pumping plant and rated pressure 21MPa, the hydraulic load of metered flow 10L/min are provided, and initial pressure is provided；Store
Can device assembly be bag type accumulator；Hydraulic cylinder completes oil-feed and works with oil return, and hydraulic cylinder output pressure P has set
Cheng Hou, when hydraulic cylinder piston rod moves, hydraulic cylinder cavity volume V becomes big, the storage being now connected with hydraulic cylinder
Energy device component responds, to hydraulic cylinder supplementary pressure, makes cylinder device output pressure P constant.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410753102.0A CN104500459B (en) | 2014-12-09 | 2014-12-09 | Realize the hydraulic pressure weight balancing system of microgravity environment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410753102.0A CN104500459B (en) | 2014-12-09 | 2014-12-09 | Realize the hydraulic pressure weight balancing system of microgravity environment |
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| Publication Number | Publication Date |
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| CN104500459A CN104500459A (en) | 2015-04-08 |
| CN104500459B true CN104500459B (en) | 2016-08-17 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105403385B (en) * | 2015-10-27 | 2018-10-23 | 上海航天精密机械研究所 | A kind of experimental rig and its test method of the pneumatic cut spring work of simulation |
| CN106596155A (en) * | 2016-11-18 | 2017-04-26 | 上海宇航系统工程研究所 | Spacecraft separation test system and method |
| CN106568664A (en) * | 2016-11-18 | 2017-04-19 | 上海宇航系统工程研究所 | Spacecraft high/low temperature separation testing system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5379657A (en) * | 1992-06-22 | 1995-01-10 | Timothy K. Hasselman | Microgravity suspension system for simulating a weightless environment |
| CN2514327Y (en) * | 2001-08-22 | 2002-10-02 | 北京机电研究所 | Imitating loader for press |
| CN101245794A (en) * | 2008-03-21 | 2008-08-20 | 太原理工大学 | Redundant electrohydraulic servo-controlling system |
| CN102050230A (en) * | 2010-11-10 | 2011-05-11 | 湖北航天技术研究院总体设计所 | Stage separation test device and method for balancing gravity |
| CN202783802U (en) * | 2012-06-27 | 2013-03-13 | 湖北三江航天红阳机电有限公司 | Aircraft separation test device |
| CN103672126A (en) * | 2013-12-26 | 2014-03-26 | 重庆川仪自动化股份有限公司 | Electro-hydraulic actuator |
-
2014
- 2014-12-09 CN CN201410753102.0A patent/CN104500459B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5379657A (en) * | 1992-06-22 | 1995-01-10 | Timothy K. Hasselman | Microgravity suspension system for simulating a weightless environment |
| CN2514327Y (en) * | 2001-08-22 | 2002-10-02 | 北京机电研究所 | Imitating loader for press |
| CN101245794A (en) * | 2008-03-21 | 2008-08-20 | 太原理工大学 | Redundant electrohydraulic servo-controlling system |
| CN102050230A (en) * | 2010-11-10 | 2011-05-11 | 湖北航天技术研究院总体设计所 | Stage separation test device and method for balancing gravity |
| CN202783802U (en) * | 2012-06-27 | 2013-03-13 | 湖北三江航天红阳机电有限公司 | Aircraft separation test device |
| CN103672126A (en) * | 2013-12-26 | 2014-03-26 | 重庆川仪自动化股份有限公司 | Electro-hydraulic actuator |
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| CN104500459A (en) | 2015-04-08 |
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