CN103434661B - Automatic injecting interface - Google Patents
Automatic injecting interface Download PDFInfo
- Publication number
- CN103434661B CN103434661B CN201310390862.5A CN201310390862A CN103434661B CN 103434661 B CN103434661 B CN 103434661B CN 201310390862 A CN201310390862 A CN 201310390862A CN 103434661 B CN103434661 B CN 103434661B
- Authority
- CN
- China
- Prior art keywords
- interface
- receiving
- output
- output interface
- filling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The invention provides an automatic injecting interface. A receiving interface is connected with a receiving platform; an output interface is connected with an output platform; one end of a tapered butt joint of the receiving interface is provided with an opened tapered outward-flared part, and the other end of the tapered butt joint is provided with a guide pipe; the guide pipe is connected with an injection storage device; a receiving interface controller is in communication with a receiving platform computer and controls a sealing switch to drive a seal for sealing the guide pipe so as to seal injection; auxiliary butting devices of the output interface are arranged at the two sides of the head of an output pipe; the head of the output pipe is subjected to spherical treatment and is internally provided with a pressure sensing device; when both the two sides of the head of the output pipe are pressed, accurate butting is achieved, and then an inner layer sleeve driver drives a hollow cylindrical inner layer sleeve inside the output pipe to extend into the receiving interface so as to form stable connection. The automatic injecting interface is simple in information interaction mode, the control accuracy requirement during butting can be lowered, and meanwhile, the automatic injecting interface has a disturbance resisting capability and is capable of automatically injecting fluids between platforms.
Description
Technical field
The present invention relates to a kind of filling interface.
Background technology
Along with the development of various new and high technology and the successful development of new installation, be proposed new requirement for various types of carrying platform autonomous operation ability, wherein most is representational is unmanned plane and the autonomy-oriented of spacecraft supply in-orbit.Unmanned plane makes that aircraft cruise duration is short, flight range is limited due to load limit.The appearance of loading technique makes this intrinsic weakness obtain larger improvement, by supply fuel oil, the remote maneuverability of unmanned plane can be made to obtain larger raising, greatly increase its flying radius and airborne period.The autonomous filling realizing unmanned plane is significant for the flight performance improving unmanned plane.And spacecraft is serious by the restriction of consumable substance carrying capacity in orbit, wherein flowing material comprises propellant, refrigerant, power supply medium, raw guarantor's gas etc.And the spacecraft lead time is long costly, how to realize the recycling of resource exhaustion spacecraft, the effective rate of utilization improving spacecraft is significant.Simultaneously due to the particularity of space environment, spacecraft is long-range operates poor real in-orbit, and information has delay, so the autonomy-oriented realizing operation is very necessary.
Existing dosing method is mainly annotate in people's aerial filling in the loop and ground, and filling process is monitored in real time by people and carried out intelligent decision.Filling interface is that simple machine connects, and interface does not possess information and generates and recuperability, is not communicated with, can not realizes autonomy-oriented with control center information.Be connected to form without stable when interface connects, connective stability is low, and antijamming capability is weak.For people's aerial filling in the loop, people's information circuits when ground is long, and information safety not easily ensures.Have requirement of real-time owing to artificially monitoring, be not suitable for remote control, loading system application is limited simultaneously.
Summary of the invention
In order to overcome the deficiencies in the prior art, the invention provides a kind of filling interface, information interaction approach is simple, can reduce control accuracy requirement in docking operation, have Ability of Resisting Disturbance simultaneously, can independently annotate by the fluid between implementation platform.
The technical solution adopted for the present invention to solve the technical problems is: comprise receiving interface and output interface; Receiving interface is connected with receiving platform, and output interface is connected with output stage;
Described receiving interface comprises taper butt junction, receiving interface controller, sealing and sealing switch, and taper butt junction one end is the taper expanding part of opening, and the other end is conduit; Conduit with add injecting memory storage and be connected, receiving interface controller and receiving platform compunication also control seal switch, and closes ducts is sealed in driving, seals up for safekeeping and adds injecting;
Described output interface comprises butt joint auxiliary device, Output Interface Control device, internal layer cover and internal layer cover actuator, butt joint auxiliary device is installed on delivery pipe head both sides, head is through sphere process, built-in pressure sensitive device, pressurized situation is converted into signal and sends to Output Interface Control device, accurate docking is shown when the equal pressurized in delivery pipe head both sides, now, Output Interface Control device sends signal, the internal layer cover being positioned at the hollow cylindrical of delivery pipe by internal layer cover driver drives stretches into receiving interface, forms stable connection.
The invention has the beneficial effects as follows: this filling interface can be applicable to unmanned plane air refuelling, in the autonomous filling of the spacecraft fluid medium such as fluid consumable substance filling in-orbit.Information interaction approach of the present invention is simple, can reduce control accuracy requirement in docking operation, have Ability of Resisting Disturbance simultaneously, can independently annotate by the fluid between implementation platform.
Accompanying drawing explanation
Fig. 1 is interface connection diagram;
Fig. 2 is that spacecraft propulsion agent is independently annotated information flow diagram;
Fig. 3 is that spacecraft propulsion agent is independently annotated interfaces flow process.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described, the present invention includes but be not limited only to following embodiment.
The present invention relates generally to one and independently to annotate interface, goal of the invention has certain independence by a kind of, and information interaction approach is simple, can reduce control accuracy requirement in docking operation, there is the filling interface of stronger Ability of Resisting Disturbance, independently annotate with the fluid between implementation platform.Cardinal principle utilizes tapered receiver mouth to expand the detection of a target, reduces control overflow, utilizes the profile of two interfaces to fasten realization preliminary fixing.By being built-in with pressure sensitive recognizer, the butt joint auxiliary device induction pressure situation of port sphere process also generates corresponding signal.Make take-off lever in the effect lower slider along bar direction force and cone-shaped interface inwall during non-precision docking, formed and accurately dock, internal layer cover stretches into receiving interface and realizes stable connection.Spaceborne computer and IO interface controller is utilized to realize information interaction.
The present invention includes receiving interface and output interface two parts, receiving interface is connected with receiving platform, and output interface is connected with output stage.
Receiving interface is made up of taper butt junction, receiving interface controller, sealing and sealing switch, is communicated with receiving platform computerized information.Taper butt junction is made up of taper expanding part and the conduit be attached thereto.Taper extends out design, and make the detection of a target in preliminary aligning become large, reduce control overflow, inner wall smooth process reduces friction.Inwall is by during along power in conical centre's alignment, this power can be analyzed to points to the power at center and the power perpendicular to inner wall surface along tapered receiver mouth inwall, the heavy straight antagonistic force balance provided by inwall in the power of inwall, the power along inwall can make object move to conical centre.Receiving interface controller and sealing and switch thereof, be positioned at catheter tail, and adds injecting memory storage and be connected.Receiving interface controller and receiving platform computing machine and Output Interface Control device information communication.The filling that receiving interface controller identifiable design is sent by Output Interface Control device is ready to complete signal, filling termination is ready to complete signal and filling termination signal, the filling termination signal sent by receiving platform computing machine also controls sealing switch, can send filling to o controller is ready to complete signal simultaneously, filling termination signal, adds injecting sealing closing signal.Seal to be used for sealing up for safekeeping and add injecting, by sealing switch control rule.
Output interface is by butt joint auxiliary device, and Output Interface Control device, internal layer cover and internal layer cover drive composition, and output interface is connected with telescopic stiff rod delivery pipe, is communicated with output stage computing machine and receiving interface controller information.Butt joint auxiliary device is installed on delivery pipe head.Delivery pipe can carry out small-angle movement.Butt joint auxiliary device is by the butt junction through sphere process, and pressure sensitive device, signal generates and forms with pio chip.Pressurized situation is converted into signal and sends to Output Interface Control device by butt joint auxiliary device.With two interface physical be connected and line of centers overlap for accurately to dock standard.Can be obtained by two interface geometric designs, when butt joint auxiliary device is positioned at cone-shaped interface, but do not formed when accurately docking, butt joint auxiliary device single-point pressurized, multiple spot pressurized when only having two line of centerss to overlap, geometric shape fastens, and accurately docks, and connects temporary stabilization.When connecing accurate, internal layer cover stretches into receiving interface, forms stable connection.Output Interface Control device and output stage computing machine, butt joint auxiliary device and receiving interface controller are connected.What Output Interface Control device identifiable design was sent by butt joint auxiliary device is pressure condition signal, judge whether accurate docking, and send signal when non-precision is docked to output stage computing machine, accurately control internal layer cover during docking and stretch out, send filling and be ready to complete signal to Output Interface Control device; The filling sent by receiving interface controller is ready to complete signal, and controls to open after verification to add injecting injection cock; The filling termination signal sent by receiving interface controller, and closedown adds injecting injection cock after verification, sends filling termination and is ready to complete signal; The sealing closing signal sent by receiving interface controller, and regain internal layer cover after verification, send to output stage computing machine and receiving interface controller termination signal of annotating.
Filling desired signal is sent by platform computing machine.Dead work is carried out by platform computer controlled before interface effect.Be confirmed whether by platform machine borne computer needs of annotating, and controlled two platforms or single platform is motor-driven, made two platforms close.Add injecting reserves control monitor unit to be connected with platform computing machine, receive and add injecting reserves shortage signal, generating filling needs signal.Confirm two platform spacings guaranteeing under safe prerequisite close to the length of take-off lever and two interfaces and, stable physical connection can be formed, then represent to enter and allow filling distance.Enter and allow distance afterwards, adjustment platform stance makes receiving port and delivery port just right.Utilize platform machine set detection to equip Guidance control platform motor-driven, make butt joint auxiliary device be positioned at tapered receiver mouth inner, formed and tentatively connect, confirmed by platform computing machine.Wake the output in two platforms and reception control center after confirmation up, and stop the direct information between two platforms to exchange, to carry out next step operation.Platform is made to keep attitude and position stability by two platform computer controlled platforms in filling process.Export during non-filling state and be in dormant state to save the energy with reception control center.Filling settling signal is sent by platform computing machine.Rear platform computer controlled two controller of having annotated enters dormancy, controls two platforms simultaneously and is separated, enter normal operation.
This filling interface can be applicable to unmanned plane air refuelling, in the autonomous filling of the spacecraft fluid medium such as fluid consumable substance filling in-orbit.Independently annotate for spacecraft collaborative propellant in-orbit and be described, output stage and receiving platform are spacecraft in-orbit, and maneuverability is more or less the same.Delivery pipe is telescoping stiff rod, can carry out low-angle deformation and motor-driven.
Fig. 1 is interface connection diagram.Interface forms primarily of two large divisions, is respectively receiving interface and output interface.Receiving interface comprises receiving interface controller, adds the sealing of injecting memory storage and switch and cone-shaped interface.Open sealing after filling is ready to complete, after completing filling, seal closedown.Output interface is by Output Interface Control device, and butt joint auxiliary device, internal layer cover overlaps actuating device with internal layer and forms.Butt joint auxiliary device is installed on delivery pipe head.Add injecting jetting system and be positioned at delivery pipe end, its switch is by output controller controls.After forming preliminary accurately connection, internal layer stretches out under being enclosed within the promotion of actuating device.
Fig. 2 is the flow of information in interface docking operation.After completing preliminary docking, two platform spaceborne computers carry out information interaction by controller.Receive spacecraft spaceborne computer to be connected with orbits controlling thruster, propellant reserves control monitor unit and receiving interface controller with spacecraft attitude.When propellant is not enough or adding amount reaches storage requirement, control monitor unit sends signal to spaceborne calculator, determined whether to need filling, or whether filling can stop by spaceborne calculator.Spaceborne computer controls spacecraft attitude makes two spacecrafts realize when there being filling to need initially docking with orbits controlling thruster, and after filling completes, make two spacecrafts be separated.Spaceborne computer can carry out information interaction with receiving interface controller.Receiving interface controller seals switch with Output Interface Control device and propellant storage box and is connected.Two controllers can realize simple information intercommunication.The spaceborne computer exported in spacecraft is connected with orbits controlling thruster and telescopic stiff rod delivery pipe with Output Interface Control device, spacecraft attitude.Spaceborne computer can control spacecraft attitude and orbits controlling thruster makes two spacecrafts close and keeps certain relative position, sets up communication link, controls delivery pipe and stretches out, and after filling completes, make delivery pipe retract.Output Interface Control device and spaceborne computer can carry out information interaction, and the spacecraft maneuver that platform computer controlled is completed by tentatively aiming to when accurately aiming at slip operates, and realizes accurately docking, and one-tenth filling makes two platforms separation after stopping.Output Interface Control device opens propellant eductor switch after filling prepares all to complete, ejection propellant, and closes propellant jet switch after receiving the filling termination signal sent by reception control center, stops propellant exporting.Butt joint auxiliary device and output control center diconnected, connect the pressure sensitive device generation signal of auxiliary device to portion and import o controller into, be confirmed whether accurate docking by o controller, non-precision is docked, and signal imports spaceborne computer into and carries out corresponding operating.Accurately docking then sends docking by o controller and is ready to complete signal to receiving interface controller, controls internal layer cover simultaneously stretch out by Output Interface Control device.
Fig. 3 is that spacecraft propulsion agent is independently annotated interfaces flow process, is mainly divided into three parts: start section, filling section, termination section.Specific works flow process is as follows:
Autonomous filling starts section:
(1) information is passed to and is received spacecraft spaceborne computer by propellant reserves monitoring device detection propellant reserves, defines without filling needs, and thinking when reserves are not enough has filling needs.
(2) communication link between filling both sides spacecraft is set up, receiving spacecraft spaceborne computer control orbit maneuver thruster makes reception spacecraft make two spacecrafts close to exporting spacecraft and adjusting attitude, guarantee that two spacecrafts can keep attitude stabilization in further operating process, spaceborne computer no longer carries out direct information simultaneously
Exchange.
(3) export spacecraft and stretch out telescopic stiff rod delivery pipe.Exporting the butt joint auxiliary device being made take-off lever front end under the control of spacecraft spaceborne computer by detector guiding, be in and receive spacecraft cone-shaped interface inside.
(4) butt joint auxiliary device internal pressure inductor generates signal, pass to o controller, and then import output spacecraft spaceborne computer into, make that receiving interface is slipped into output interface by spaceborne computer control spacecraft maneuver and form accurate docking, control internal layer cover by output control center and stretch into receiving interface.Signal is sent to and receives control center.
(5) receive control center's identification signal, confirm that exporting spacecraft is ready to complete, and opens the sealing of propellant memory storage, is issued by signal and export control center.
(6) export control center's identification signal, confirm to receive spacecraft ready, open and advance jetting system switch, start filling.
Autonomous filling section: limited by physical connection by the propellant jet device flow controlled when annotating simultaneously and add the injecting flow direction, monitor propellant reserves by the propellant reserves monitoring device on receiver.
Autonomous filling stops section:
(1) information is passed to and is received spacecraft spaceborne computer by propellant reserves monitoring device detection propellant reserves, determines whether to stop filling, constantly thinks that reserves up to standard when reserves reach to be worth, stop filling.
(2) receive spacecraft, by receiving interface controller and Output Interface Control device, signal is passed to output spacecraft, controlled to close propelling jetting system switch by output spacecraft Output Interface Control device, generate signal and pass to receiver.
(3) receiving interface controller identification signal, confirms that exporting spacecraft has done filling termination preparation, closes the sealing of propellant memory storage, and to output spacecraft transmission signal.
(4) Output Interface Control device identification signal, regain internal layer cover and telescopic take-off lever, signal is sent to reception spacecraft, control to export spacecraft lifting force device by output spacecraft spaceborne computer makes two spacecrafts be separated simultaneously, adjustment Space Vehicle position and attitude, make output spacecraft normally run by original track.
(5) receive spacecraft identification signal, by spaceborne calculating control thruster adjustment reception Space Vehicle position and attitude, spacecraft is normally run.
Claims (1)
1. independently annotate an interface, comprise receiving interface and output interface, it is characterized in that: receiving interface is connected with receiving platform, output interface is connected with output stage; Described receiving interface comprises taper butt junction, receiving interface controller, sealing and sealing switch, and taper butt junction one end is the taper expanding part of opening, and the other end is conduit; Conduit with add injecting memory storage and be connected, receiving interface controller and receiving platform compunication also control seal switch, and closes ducts is sealed in driving, seals up for safekeeping and adds injecting; Described output interface comprises butt joint auxiliary device, Output Interface Control device, internal layer cover and internal layer cover actuator, butt joint auxiliary device is installed on delivery pipe head both sides, head is through sphere process, built-in pressure sensitive device, pressurized situation is converted into signal and sends to Output Interface Control device, accurate docking is shown when the equal pressurized in delivery pipe head both sides, now, Output Interface Control device sends signal, the internal layer cover being positioned at the hollow cylindrical of delivery pipe by internal layer cover driver drives stretches into receiving interface, forms stable connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310390862.5A CN103434661B (en) | 2013-08-31 | 2013-08-31 | Automatic injecting interface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310390862.5A CN103434661B (en) | 2013-08-31 | 2013-08-31 | Automatic injecting interface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103434661A CN103434661A (en) | 2013-12-11 |
| CN103434661B true CN103434661B (en) | 2015-07-08 |
Family
ID=49688415
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310390862.5A Expired - Fee Related CN103434661B (en) | 2013-08-31 | 2013-08-31 | Automatic injecting interface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103434661B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2558002C1 (en) | 2014-02-03 | 2015-07-27 | Общество с ограниченной ответственностью "Лаборатория будущего" | Device for diagnostics of overhead power transmission lines and its component |
| CN104058109B (en) * | 2014-05-30 | 2015-11-04 | 北京控制工程研究所 | A kind of satellite is independently annotated in-orbit and is used fluid transport interface |
| CN107284699B (en) * | 2017-06-19 | 2019-12-20 | 北京航天发射技术研究所 | Automatic butt joint control system for carrier rocket add-and-drain connector |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2803473A (en) * | 1951-07-16 | 1957-08-20 | Bernhard A Hohmann | Valved pipe joint equipment for refuelling an aircraft in flight |
| US6752357B2 (en) * | 2002-05-10 | 2004-06-22 | The Boeing Company | Distance measuring using passive visual means |
| US8074935B2 (en) * | 2007-03-09 | 2011-12-13 | Macdonald Dettwiler & Associates Inc. | Satellite refuelling system and method |
| US8381779B1 (en) * | 2011-10-11 | 2013-02-26 | General Electric Company | System for wireless refueling of an aircraft |
| CN203111518U (en) * | 2012-12-27 | 2013-08-07 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Locking structure for butt joint and disjoint in air refueling |
-
2013
- 2013-08-31 CN CN201310390862.5A patent/CN103434661B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN103434661A (en) | 2013-12-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103434661B (en) | Automatic injecting interface | |
| CN102360216B (en) | Two-engine carrier-based aircraft with one engine off safety carrier landing control method | |
| CN112416012B (en) | Active section guidance control method for rocket power plane symmetric carrier | |
| CN102298389A (en) | System fully controlled and taken over by ground station during takeoff and landing stages of unmanned plane | |
| CN104155990A (en) | Hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint | |
| US20160229558A1 (en) | System to accelerate and decelerate aircraft for take-off and landing | |
| CN103171756B (en) | Wing rib-free rapid water injection and drainage wing suitable for sea and air across amphibious unmanned aerial vehicle | |
| CN106292687A (en) | A kind of agricultural unmanned vehicle sprayer apparatus and spraying method thereof | |
| CN109703768A (en) | It is a kind of based on the soft air refuelling interconnection method of posture/track complex controll | |
| CN111470032A (en) | Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof | |
| CN107792404B (en) | The safety belt that section is drawn close in a kind of translation of spacecrafts rendezvous determines method | |
| CN107618661B (en) | Short-distance vertical take-off and landing aircraft based on throat offset type pneumatic vectoring nozzle | |
| CN111309041A (en) | Catapult takeoff pull-up control method | |
| CN103523223A (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN103253382B (en) | High-precision joint orbital transfer method for engines | |
| CN204184579U (en) | The electromagnetism carrier landing system of aircraft carrier | |
| CN204184572U (en) | Water kinetic energy aircraft | |
| CN105865742A (en) | Wind tunnel test aero-engine thrust vector jet pipe steering system | |
| CN210083558U (en) | Anti-vibration agricultural unmanned aerial vehicle medical kit | |
| US20230150654A1 (en) | Novel jet-propelled lift-increasing and stability-increasing amphibious aircraft and application method thereof | |
| CN212473831U (en) | Multifunctional aquaculture unmanned ship | |
| CN114228931A (en) | Unmanned aerial vehicle auxiliary platform on water | |
| CN212637890U (en) | Novel jet-propelled amphibious aircraft that increases lift and increases steady | |
| WO2018032430A1 (en) | Intelligent unmanned aerial vehicle system | |
| CN113071681A (en) | Intelligent unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150708 Termination date: 20210831 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |