CN102826232B - Airplane short-distance sliding take-off and landing system based on RFID (Radio Frequency Identification) technology - Google Patents
Airplane short-distance sliding take-off and landing system based on RFID (Radio Frequency Identification) technology Download PDFInfo
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- CN102826232B CN102826232B CN201110163972.9A CN201110163972A CN102826232B CN 102826232 B CN102826232 B CN 102826232B CN 201110163972 A CN201110163972 A CN 201110163972A CN 102826232 B CN102826232 B CN 102826232B
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Abstract
The invention provides an airplane short-distance sliding take-off and landing system based on an RFID (Radio Frequency Identification) technology, which comprises a short-distance runway airplane take-off and landing devices and a control system based on the RFID technology; each short-distance runway airplane take-off and landing device comprises a first power track, a second power track, a third power track and a mechanical device for automatically closing the tracks; the control system based on the RFID technology comprises a background control device, card readers and a radio-frequency card; at least one of the card readers is arranged on each short-distance runway airplane take-off and landing device; the card readers are fixed at both sides of each short-distance runway airplane take-off and landing device or inside each short-distance runway airplane take-off and landing device so as to read a speed control command from the radio-frequency card, and the rotation directions and rotation speeds of the first power track, the second power track and the third power track of each short-distance runway airplane take-off and landing device are controlled according to the speed control command. The system shortens the runway length necessary for airplane sliding take-off and landing.
Description
Technical field
The present invention relates to a kind of aircraft short distance and slide landing system, particularly relate to a kind of aircraft short distance based on RFID technique and slide landing system.
Background technology
At present, the runway that takeoff and landing use is linear, and runway is long, and area occupied is large, will set up traditional plane track more difficult for takeoff and landing on the island of limited area; Equally, will slide landing aircraft on aircraft carrier, its landing airdrome length determines its huge volume (particularly length), and be easy to be attacked, its cost, upkeep cost are also considerable.Therefore, the tradition of aircraft slides landing runway and governs aircraft carrier and island airport construction to a great extent.
Summary of the invention
Fundamental purpose of the present invention is to provide a kind of aircraft short distance based on RFID technique to slide landing system, significantly shortens the necessary landing airdrome length of aircraft taxi landing, effectively to utilize the area of aircraft carrier and island.
In order to achieve the above object, the invention provides a kind of aircraft short distance based on RFID technique and slide landing system, comprise short distance runway takeoff and landing device and the control system based on RFID technique;
Described short distance runway takeoff and landing device comprises the mechanical hook-up of the first power rail, the second power rail, the 3rd power rail and automatic closed orbit;
Described first power rail, described second power rail and described 3rd power rail are parallel to each other, and are the track of drive device;
Described first power rail and described 3rd power rail are positioned at described second power rail both sides;
Described first power rail, parallel distance between described 3rd power rail and described second power rail are equal with on undercarriage two horizontal range between trailing wheel with front-wheel;
Described first power rail and described 3rd power rail, be respectively used to two trailing wheels of carrying undercarriage and provide power;
The power synchronous that the propulsion system of described first power rail and the propulsion system of described 3rd power rail provide, and the frictional power provided of described first power rail and described 3rd power rail is equal;
The front-wheel of described second power rail carrying undercarriage;
The mechanical hook-up of described automatic closed orbit is equipped with propulsion system, and during takeoff and landing, the mechanical hook-up of described automatic closed orbit is opened, to open described first power rail, described second power rail and described 3rd power rail, for aircraft provides power;
The described control system based on RFID technique comprises Background control device, card reader and radio-frequency card;
Described radio-frequency card is fixed on the front-wheel of undercarriage;
Described background control system, for described radio-frequency card transmission speed steering order;
Each described short distance runway takeoff and landing device is at least provided with a card reader;
Described card reader is fixed on described short distance runway takeoff and landing device both sides or described short distance runway takeoff and landing device is inner, to read from the rate control instruction of described radio-frequency card, and control direction that the first power rail of short distance runway takeoff and landing device, the second power rail and the 3rd power rail rotate and rotating speed according to this rate control instruction.
During enforcement, when taking off, described background control system to described radio-frequency card send take off time rotating speed steering order, the speed that when this takes off, rotating speed steering order controls power rail is increased to maximum from zeroth order ladder type successively; Described card reader to receive when this takes off after rotating speed steering order, open the mechanical hook-up of automatic closed orbit, control described first power rail, described second power rail and described 3rd power rail to rotate forward, and the rotating speed controlling described first power rail, described second power rail and described 3rd power rail is increased to maximum (top) speed from zeroth order ladder type successively.
During enforcement, when described card reader does not read the radio-frequency information that described radio-frequency card sends within a schedule time, control the mechanical hook-up of closing described automatic closed orbit.
During enforcement, when aircraft landing, rotating speed control command when described background control system sends landing to described radio-frequency card, after described card reader receives landing hourly velocity control command, open the mechanical hook-up of described automatic closed orbit, control described first power rail, described second power rail and described 3rd power rail rotate forward, and control described first power rail, the speed when rotating speed of described second power rail and described 3rd power rail lands from aircraft landing, decelerate to zero, control described first power rail again, described second power rail and described 3rd power rail rotate backward, until aircraft stops.
During enforcement, the mechanical hook-up of described automatic closed orbit, comprises the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid and propulsion system;
The length of the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid is equal with described short distance runway takeoff and landing device length;
The width of described second slip lid and described 3rd slip lid is equal, and the width of described second slip lid and described 3rd slip lid is equal to or less than the horizontal range between former and later two wheel neighboring edges of undercarriage respectively;
The width of described first slip lid and described 4th slip lid is equal;
The width of described first slip lid equals the horizontal range at described first power rail outer ledge and described second power rail center, with the difference of the width of described second slip lid;
The width of described 4th slip lid equals the horizontal range at described 3rd power rail outer ledge and described second power rail center, and between the width of described 3rd slip lid difference;
These propulsion system are connected with the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid respectively, for the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid provide level or level power to the right left.
Compared with prior art, technical characterstic of the present invention and effect as follows:
1, the present invention provides extra power or resistance for takeoff and landing, effectively can shorten the coasting distance of takeoff and landing;
2, the present invention adopts rail mounted runway, can prevent the unexpected sideslip of aircraft;
3, rail mounted runway of the present invention can open and close automatically, opens track when takeoff and landing, for aircraft provides power; Can close at ordinary times, protection track and airport is smooth, can be used as traditional airport.Therefore Novel track type airport, on the basis not affecting conventional airplane landing, can increase many runways, effectively improves airport utilization factor;
4, the present invention is simply easy to carry out, and only need slightly reequip the undercarriage of existing aircraft, and can realize on traditional runway and Novel running track of the present invention can landing;
5, the present invention is a kind of backup system of aircraft taxi landing, with the servicing unit of other landings and use, as ejector, slope, can block rope etc.
Accompanying drawing explanation
Fig. 1 is the structural representation that landing system is slided in the aircraft short distance based on RFID technique of the present invention;
Fig. 2 A is power rail that landing system is slided in the aircraft short distance based on RFID technique of the present invention schematic diagram when closing;
Fig. 2 B is power rail that landing system is slided in the aircraft short distance based on RFID technique of the present invention schematic diagram when opening.
Embodiment
As shown in Figure 1, the invention provides a kind of aircraft short distance based on RFID technique and slide landing system, comprise short distance runway takeoff and landing device 1 and the control system 2 based on RFID technique.
Described short distance runway takeoff and landing device 1 comprises the mechanical hook-up 14 of power rail 11, power rail 12, power rail 13 and automatic closed orbit;
Described power rail 11, described power rail 12 and described power rail 13 are parallel to each other, and are the track of drive device.
Described power rail 11 and described power rail 13 are in described power rail 12 both sides;
Described power rail 11, parallel distance between described power rail 13 and described power rail 12 are equal with on undercarriage two horizontal range between trailing wheel with front-wheel.
Described power rail 11 and described power rail 13 are made up of parallel arranged before and after rotating wheel, rotating bearing or crawler belt equal power device.The power synchronous that the propulsion system of described power rail 11 and described power rail 13 provide, its objective is that the object that can contact with power rail for vertical direction provides frictional power forward or backward, and the frictional power provided of described power rail 11 and described power rail 13 is equal.
Described power rail 12 carries the front-wheel of undercarriage, and power can be provided also can not to provide power.
The mechanical hook-up 14 of described automatic closed orbit is equipped with propulsion system, and during takeoff and landing, the mechanical hook-up 14 of automatic closed orbit is opened, to open described power rail 11, described power rail 12 and described power rail 13, for aircraft provides power.The mechanical hook-up 14 of described automatic closed orbit cuts out at ordinary times; to close described power rail 11, described power rail 12 and described power rail 13; protect described power rail 11, described power rail 12 and described power rail 13 and airport is smooth, can be used as traditional airport.
According to a kind of embodiment, as shown in Fig. 2 A, Fig. 2 B, the mechanical hook-up 14 of described automatic closed orbit, comprises slip lid 141, slip lid 142, slip lid 143, slip lid 144 and propulsion system (not shown).The length of slip lid 141, slip lid 142, slip lid 143 and slip lid 144 is equal with short distance runway takeoff and landing device 1 length; The width of slip lid 142 and slip lid 143 is equal, and the width of slip lid 142 and slip lid 143 is equal to or less than the horizontal range between former and later two wheel neighboring edges of undercarriage respectively; The width of slip lid 141 equals the horizontal range at power rail 11 outer ledge and power rail 12 center, with the difference of the width of slip lid 142, the width of slip lid 144 equals the horizontal range at power rail 13 outer ledge and power rail 12 center, and between the width of slip lid 143 difference.Its objective is, when slip lid closes, slip lid 141 and slip lid 142 level are slided to the right, and slip lid 143 and slip lid 144 level are slided left, and make slip lid cover whole track, airport is smooth; When slip lid is opened, slip lid 141 and slip lid 142 level are slided left, and slip lid 143 and slip lid 144 level are slided to the right, and make outside track is exposed to completely, undercarriage can carry in orbit completely.These propulsion system are connected with slip lid 141, slip lid 142, slip lid 143, slip lid 144, for slip lid 141, slip lid 142, slip lid 143 and slip lid 144 provide level or level power to the right left.Its objective is, when taking off or land, when power rail needs to open, for slip lid provides the power opened; After taking off or landing, when power rail needs closed, for slip lid provides closed power.
The described control system 2 based on RFID technique comprises Background control device 21, card reader 22 and radio-frequency card 23.
Described radio-frequency card 23 is fixed on the front-wheel of undercarriage;
Described background control system 21 is integrated on the control desk of aircraft handling room, radio frequency card 23 can carry out read-write operation, for described radio-frequency card 23 transmission speed steering order; .
Each short distance runway takeoff and landing device 1 is at least provided with a card reader 22; Described card reader 22 is fixed on short distance runway takeoff and landing device 1 both sides or short distance runway takeoff and landing device 1 is inner, to read the rate control instruction from described radio-frequency card 23, and control the power rail 11 of short distance runway takeoff and landing device 1, power rail 12 and power rail 13 according to this rate control instruction and rotate forward or rotate backward, and the rotating speed of described power rail 11, described power rail 12 and described power rail 13 can be controlled.
When taking off, be integrated in background control system 21 on the control desk of aircraft handling room to radio-frequency card 23 send take off instruction and take off time rotating speed control command, the speed of power rail is increased to maximum (taking off speed when leaving ground) from zeroth order ladder type successively; The card reader 22 be contained on short distance runway takeoff and landing device 1 receive take off instruction and take off time rotating speed control command after, open the mechanical hook-up 14 of automatic closed orbit, control power rail 11, power rail 12 and power rail 13 to rotate forward with corresponding speed, for aircraft provides the acceleration slided forward, aircraft starting engine accelerated slip forward simultaneously.Runway run out of by aircraft, and card reader 22 is not when a period of time detects the radio-frequency information that radio-frequency card 23 sends, and the mechanical hook-up 14 of automatic closed orbit cuts out automatically, and card reader 22 enters the state of wait-receiving mode radio-frequency card 23, and system completes a takeoff operational.
When aircraft landing, the rotating speed control command of power rail when the background control system 21 be integrated on the control desk of aircraft handling room sends landing instruction and landing to radio-frequency card 23, the speed of power rail is from maximal rate (speed when aircraft landing lands) forwards, ensure aircraft and track crawler occlusion, decelerate to zero rapidly, reverse with suitable speed again, until aircraft stops.After the card reader 22 be arranged on short distance runway takeoff and landing device 1 receives landing instruction and landing hourly velocity control command, open the mechanical hook-up 14 of automatic closed orbit, control power rail 11, power rail 12 and power rail 13 to rotate with corresponding speed, for aircraft provides resistance backward, aircraft starts brake system simultaneously, and aircraft is stopped fast.Aircraft stops and after de-orbiting, card reader 22 is not when a period of time detects the effective radio-frequency information from radio-frequency card 23, the mechanical hook-up 14 of automatic closed orbit cuts out automatically, card reader 22 enters the state of wait-receiving mode from the radio-frequency information of radio-frequency card 23, and system completes a landing operation.
General aircraft landing speed is 260km/h, if the power rail of card reader and control thereof responds in 1s, plane distance card reader 72m can identify, the decipherment distance of 2.45Ghz active RF card, generally at 3-80m, can meet the demands.In practice, card reader can be placed on the track entrance of aircraft landing or rear number formulary rice, can identify in advance, for the startup of the power rail of card reader and control thereof provides grace time.
In like manner, the decipherment distance of 5.8Ghz active RF card at 1-30km, the aircraft of identifiable design more speed.Also can, by the remote recognition technology such as radar, infrared acquisition, realize identifying and automatically controlling.
The whole runway A of aircraft is tiled by several short distance runway takeoff and landing devices 1 and forms, and the track of runway A porch adopts many rails to converge mode B, to guarantee that aircraft landing is slightly offset, also can normally enter the orbit.
As shown in Figure 1, many rails converge mode B, refer to that horizontal range equals power rail 11, horizontal range between power rail 12 and power rail 13, and parallel many groups track, as (but being not limited to) track B11, track B21, track B31, with track B13, track B23, track B33, converge to another group horizontal range gradually and equal power rail 11, the horizontal range of power rail 12 and power rail 13, and on parallel track, as track B12, track B22 and track B32, and, final respectively with power rail 11, power rail 12, power rail 13 connects.Its objective is, ensure that aircraft is in the process of landing, when departing from main orbit a little, as power rail 11, power rail 12 and power rail 13, still can sail main orbit into.
For making aircraft can landing on railway tracks and normal runway, the wheel of the present invention to existing undercarriage be slightly transformed.In the present invention, each load-bearing wheel of undercarriage is made up of two wheels, and increase between two wheels that diameter is less than the diameter of described two wheels, width is equal to or slightly greater than track width and can and the wheel C of crawler belt occlusion.
More than illustrate just illustrative for the purpose of the present invention; and nonrestrictive, those of ordinary skill in the art understand, when not departing from the spirit and scope that following claims limit; many amendments, change or equivalence can be made, but all will fall within the scope of protection of the present invention.
Claims (5)
1. a landing system is slided in the aircraft short distance based on RFID technique, it is characterized in that, comprises short distance runway takeoff and landing device and the control system based on RFID technique;
Described short distance runway takeoff and landing device comprises the mechanical hook-up of the first power rail, the second power rail, the 3rd power rail and automatic closed orbit;
Described first power rail, described second power rail and described 3rd power rail are parallel to each other, and are the track of drive device;
Described first power rail and described 3rd power rail are positioned at described second power rail both sides;
Described first power rail, parallel distance between described 3rd power rail and described second power rail are equal with on undercarriage two horizontal range between trailing wheel with front-wheel;
Described first power rail and described 3rd power rail, be respectively used to two trailing wheels of carrying undercarriage and provide power;
The power synchronous that the propulsion system of described first power rail and the propulsion system of described 3rd power rail provide, and the frictional power provided of described first power rail and described 3rd power rail is equal;
The front-wheel of described second power rail carrying undercarriage;
The mechanical hook-up of described automatic closed orbit is equipped with propulsion system, and during takeoff and landing, the mechanical hook-up of described automatic closed orbit is opened, to open described first power rail, described second power rail and described 3rd power rail, for aircraft provides power;
The described control system based on RFID technique comprises Background control device, card reader and radio-frequency card;
Described radio-frequency card is fixed on the front-wheel of undercarriage;
Described Background control device, for described radio-frequency card transmission speed steering order;
Each described short distance runway takeoff and landing device is at least provided with a card reader;
Described card reader is fixed on described short distance runway takeoff and landing device both sides or described short distance runway takeoff and landing device is inner, to read from the rate control instruction of described radio-frequency card, and control direction that the first power rail of short distance runway takeoff and landing device, the second power rail and the 3rd power rail rotate and rotating speed according to this rate control instruction.
2. slide landing system based on the aircraft short distance of RFID technique as claimed in claim 1, it is characterized in that, when taking off, described Background control device to described radio-frequency card send take off time rotating speed steering order, the speed that when this takes off, rotating speed steering order controls power rail is increased to maximum from zeroth order ladder type successively; Described card reader to receive when this takes off after rotating speed steering order, open the mechanical hook-up of described automatic closed orbit, control described first power rail, described second power rail and described 3rd power rail to rotate forward, and the rotating speed controlling described first power rail, described second power rail and described 3rd power rail is increased to maximum (top) speed from zeroth order ladder type successively.
3. slide landing system based on the aircraft short distance of RFID technique as claimed in claim 2, it is characterized in that, when described card reader does not read the radio-frequency information that described radio-frequency card sends within a schedule time, control the mechanical hook-up of closing described automatic closed orbit.
4. slide landing system based on the aircraft short distance of RFID technique as claimed in claim 2 or claim 3, it is characterized in that, when aircraft landing, rotating speed control command when described Background control device sends landing to described radio-frequency card, after described card reader receives landing hourly velocity control command, open the mechanical hook-up of described automatic closed orbit, control described first power rail, described second power rail and described 3rd power rail rotate forward, and control described first power rail, the speed when rotating speed of described second power rail and described 3rd power rail lands from aircraft landing, decelerate to zero, control described first power rail again, described second power rail and described 3rd power rail rotate backward, until aircraft stops.
5. slide landing system based on the aircraft short distance of RFID technique as claimed in claim 1, it is characterized in that, the mechanical hook-up of described automatic closed orbit, comprise the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid and propulsion system;
The length of the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid is equal with described short distance runway takeoff and landing device length;
The width of described second slip lid and described 3rd slip lid is equal, and the width of described second slip lid and described 3rd slip lid is equal to or less than the horizontal range between former and later two wheel neighboring edges of undercarriage respectively;
The width of described first slip lid and described 4th slip lid is equal;
The width of described first slip lid equals the horizontal range at described first power rail outer ledge and described second power rail center, with the difference of the width of described second slip lid;
The width of described 4th slip lid equals the horizontal range at described 3rd power rail outer ledge and described second power rail center, and between the width of described 3rd slip lid difference;
These propulsion system are connected with the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid respectively, for the first slip lid, the second slip lid, the 3rd slip lid, the 4th slip lid provide level or level power to the right left.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110163972.9A CN102826232B (en) | 2011-06-17 | 2011-06-17 | Airplane short-distance sliding take-off and landing system based on RFID (Radio Frequency Identification) technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110163972.9A CN102826232B (en) | 2011-06-17 | 2011-06-17 | Airplane short-distance sliding take-off and landing system based on RFID (Radio Frequency Identification) technology |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102826232A CN102826232A (en) | 2012-12-19 |
| CN102826232B true CN102826232B (en) | 2015-04-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110163972.9A Active CN102826232B (en) | 2011-06-17 | 2011-06-17 | Airplane short-distance sliding take-off and landing system based on RFID (Radio Frequency Identification) technology |
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Citations (3)
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|---|---|---|---|---|
| US4901949A (en) * | 1988-03-11 | 1990-02-20 | Orbital Sciences Corporation Ii | Rocket-powered, air-deployed, lift-assisted booster vehicle for orbital, supraorbital and suborbital flight |
| CN101519124A (en) * | 2009-03-31 | 2009-09-02 | 王力丰 | Takeoff device and method of carrier-borne aircraft of aircraft carrier |
| CN201712792U (en) * | 2009-10-19 | 2011-01-19 | 刘克良 | Airplane taking-off and landing platform |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070029442A1 (en) * | 2003-06-06 | 2007-02-08 | Klaus Wolter | Method for supporting a propelled flying object during take-off and/or landing |
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2011
- 2011-06-17 CN CN201110163972.9A patent/CN102826232B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4901949A (en) * | 1988-03-11 | 1990-02-20 | Orbital Sciences Corporation Ii | Rocket-powered, air-deployed, lift-assisted booster vehicle for orbital, supraorbital and suborbital flight |
| CN101519124A (en) * | 2009-03-31 | 2009-09-02 | 王力丰 | Takeoff device and method of carrier-borne aircraft of aircraft carrier |
| CN201712792U (en) * | 2009-10-19 | 2011-01-19 | 刘克良 | Airplane taking-off and landing platform |
Non-Patent Citations (1)
| Title |
|---|
| 多跑道降落飞机协同调度优化;张洪海,胡明华;《交通运输工程学报》;20090630;第9卷(第3期);86-91 * |
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| CN102826232A (en) | 2012-12-19 |
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