CN114435615B - Aircraft lander - Google Patents
Aircraft lander Download PDFInfo
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- CN114435615B CN114435615B CN202210106072.9A CN202210106072A CN114435615B CN 114435615 B CN114435615 B CN 114435615B CN 202210106072 A CN202210106072 A CN 202210106072A CN 114435615 B CN114435615 B CN 114435615B
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- 238000004891 communication Methods 0.000 claims abstract description 69
- 239000007853 buffer solution Substances 0.000 claims abstract description 12
- 230000000903 blocking effect Effects 0.000 claims description 37
- 238000005516 engineering process Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 9
- 230000003993 interaction Effects 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 230000033001 locomotion Effects 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 claims description 4
- 230000002441 reversible effect Effects 0.000 claims description 2
- 238000013016 damping Methods 0.000 abstract description 6
- 239000000872 buffer Substances 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 8
- 230000003139 buffering effect Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
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- 206010000369 Accident Diseases 0.000 description 1
- 239000006173 Good's buffer Substances 0.000 description 1
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Classifications
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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
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
- B64F1/025—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using decelerating or arresting beds
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Abstract
The invention relates to the technical field of landers, in particular to an aircraft lander. The aircraft lander comprises a plurality of modularized units, and the modularized units can be mutually spliced; the spliced module unit comprises a vehicle body frame, an aircraft landing plate arranged on the vehicle body frame, a receiving and fixing device, a central control system, a braking system, a buffer system, a communication system, a power system and a wheel set; when the aircraft faces the landing problem, the aircraft can directly fall on a landing platform which keeps relative moving speed with the aircraft, the tire type structure and the damping buffer device adopted by the landing platform have the characteristic of high bearing capacity, the hard impact during landing can be effectively reduced, the safety of the aircraft is protected, and the receiving and fixing device on the landing plate of the aircraft can be locked and fixed with the aircraft to prevent the aircraft from unbalance, friction fire or rushing out of a runway. The invention improves the safety of the aircraft when the aircraft encounters landing problems, and greatly ensures the life safety of personnel in the aircraft.
Description
Technical Field
The invention relates to the technical field of landers, in particular to an aircraft lander.
Background
Aircraft crashes continue to be a significant problem for the aviation industry, with many types of civil and military aircraft accidents occurring each year. For civil aircraft, the accident rate encountered during landing of the civil aircraft can reach 40% in all flight phases, the take-off phase is 16%, the 8 minutes during the landing phase and the 3 minutes during the take-off phase are also called as dangerous 11 minutes by the civil aircraft industry, the landing phase is the most dangerous, and according to relevant statistics, major flight accidents 621 occur in the world in the transportation and flight from the beginning of the 80 th to the middle of the 90 th of the last century, wherein the accident occurring in the major approach landing phase is 287 and accounts for 46%. In the latest commercial aviation accident statistical analysis of 2019, the accident rate in landing in the last 20 years still stays high, the proportion still accounts for more than 45%, landing becomes the most frequent stage of serious accidents, and most of the visible air accidents occur in the landing stage. For military aircraft, the accident causes are more complex, the flight risk of the military aircraft is much larger than that of the civil aircraft, and the accident causes cannot be tracked. It follows that the risk of sailing of military aircraft is very high. The military aircraft can also face landing problems such as landing gear faults, icing of the tail wing, braking failure and the like when landing, and the safety of pilots is seriously influenced.
At present, no method and device for well solving the landing accident of the aircraft exist, but the invention can effectively solve the risks of landing gear faults, brake failure, engine faults and the like of the aircraft when landing and the landing is required to be hard or impossible.
Disclosure of Invention
The invention aims to provide an aircraft lander which can solve the problems that in the prior art, an aircraft encounters landing gear faults, brake failure, engine faults and the like when landing is needed or cannot be landed;
the invention provides an aircraft lander, which comprises a plurality of modularized units, wherein the modularized units can be mutually spliced;
the spliced module unit comprises a vehicle body frame, an aircraft landing plate arranged on the vehicle body frame, a receiving and fixing device, a central control system, a braking system, a buffer system, a communication system, a power system and a wheel set;
the communication system is in communication connection with the aircraft and the airport control console, and when the lander operates, the central control system adjusts and controls the output of the power system according to the collected signals received by the communication system, so that the spliced module units have the same horizontal speed as the aircraft when the aircraft descends;
when the aircraft lands, the power output of the power system is controlled, so that the spliced module units accelerate to track the aircraft, the communication system carries out speed tracking and position tracking on the aircraft, and when the communication of the aircraft fails, the device carries out active speed tracking and position tracking on the aircraft.
After the aircraft falls onto the platform, the buffer system can start to work, the impact force of the aircraft is absorbed, and then the brake system can brake to finish the final receiving work.
Preferably, the power system comprises a linear motor employing a long primary linear motor having a primary width greater than a secondary width mounted on the platform.
Preferably, the central control system is used for carrying out finishing analysis and instruction grading processing on all data of the lander;
estimating the weight of the aircraft according to the established basic parameter database of the landing model when the lander works, and estimating the impact force of the landing moment of the aircraft and analyzing the braking force required in the platform braking process based on the weight of the aircraft;
the central control system establishes three-dimensional space coordinates of an airport and an aircraft dynamics model by receiving data of the communication system, predicts the motion trail of the aircraft in real time, and adjusts the thrust of a linear motor of the power system;
the central control system tracks the parameter changes of all the systems, coordinates the work of all the systems and realizes the safe receiving of the aircraft.
Preferably, the communication system adopts an airport primary radar aircraft capturing technology to measure the speed scalar and estimate the initial position of the aircraft, and the laser radar is used for accurately positioning and measuring the speed of the aircraft, so that the immediate detection of the position vector of the aircraft is realized;
aiming at the problem of aircraft positioning, interaction and interaction are needed to be formed with an aircraft, and in the aspect of accurate positioning, the two are combined together to realize accurate positioning;
the communication system can be connected into the existing communication system of the aircraft and the control console for multiparty communication, and the communication system can realize two-party and multiparty communication, uninterrupted data transmission and management party communication control authority access by utilizing the existing very high frequency data link communication technology.
Preferably, the power system comprises linear motors arranged at two sides of the lander;
at the moment that the aircraft falls onto the lander, the impact resistance control of the linear motor is realized through speed-free, sensor-free control and traction anti-lateral deviation control;
the power system can be powered by wireless charging, a storage battery or a traction network.
Preferably, the wheel set is mounted on the underside of the body frame by a cushioning device.
Preferably, each module unit is provided with a brake system;
after the aircraft is received and fixed, the lander starts to decelerate, the lander decelerates by virtue of the braking system of each modularized unit, the linear motor of the power system regenerates the brake when the device brakes, and if the aircraft has a reverse thrust braking mechanism of an engine, the lander and the aircraft mutually cooperate to jointly decelerate.
Preferably, the receiving and fixing device comprises a front blocking baffle, a middle blocking baffle, a left blocking baffle, a right blocking baffle and a rear blocking baffle;
the blocking plate is preset on the landing plate of the aircraft according to the model of the aircraft.
Preferably, the receiving fixture is adjustable in position relative to the aircraft landing plate;
when receiving fixed aircraft, receive fixing device in lifting shrink, fixed aircraft, fixed accepting device has the redundant space of setting.
Preferably, the modular units are rigidly connected.
The beneficial effects are that:
the invention can effectively solve the risks caused by hard landing or incapability of landing when an aircraft encounters landing gear faults, brake failure, engine faults and the like during landing. When the aircraft faces the landing problem, the aircraft can directly fall on a landing platform which keeps relative moving speed with the aircraft, the tire type structure and the damping buffer device adopted by the landing platform have the characteristic of high bearing capacity, the hard impact during landing can be effectively reduced, the safety of the aircraft is protected, and the receiving and fixing device on the landing plate of the aircraft can be locked and fixed with the aircraft to prevent the aircraft from unbalance, friction fire or rushing out of a runway. The tire type structural technology applied by the invention has the advantages of mature technology, high load capacity, good buffering effect, strong adaptability, low field requirement and good braking effect, improves the safety of an aircraft when the aircraft encounters landing problems, and greatly ensures the life safety of internal personnel.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a side view of an aircraft landing gear configured using three modules according to an embodiment of the present invention when receiving a landing aircraft.
Fig. 2 is a side view of an aircraft landing gear using three sets of modules in accordance with an embodiment of the present invention.
Fig. 3 is a top view of an aircraft landing gear using three sets of modules according to an embodiment of the present invention.
Fig. 4 is a schematic view of the bottom of an aircraft landing gear using three modules in accordance with an embodiment of the present invention.
Fig. 5 is a front view of an aircraft landing gear using three sets of modules according to an embodiment of the present invention.
FIG. 6 is a top view of an aircraft landing gear floor made up of three modules with a receiving fixture according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of a modular unit according to an embodiment of the present invention.
Reference numerals illustrate:
1-a front blocking baffle; 2-an intermediate blocking baffle; 3-a rear blocking baffle; 4-aircraft landing boards; 5-a body frame; 6-wheel group; 7-a linear motor; 8-right side blocking baffle; 9-left side blocking baffle; 10-an electromagnetic damping device; 11-a communication system; 12-a braking system; 13-power system.
Detailed Description
The technical solutions of the present invention will be clearly and completely described in connection with the embodiments, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. Furthermore, the terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1 to 7, the present embodiment provides an aircraft landing system including a plurality of modular units, and the modular units can be spliced with each other.
After selecting a suitable number of modular units to form a complete set of landing receivers, the landing receivers comprise the following structure: the aircraft landing plate 4, the receiving fixtures on the aircraft landing plate, the central control system, the braking system 12, the cushioning system, the power system 13, the communication system 11, and the underlying wheel set 6 are secured to the body frame 5.
When the device is operated, the communication system 11 and the aircraft can communicate with each other, the communication system 11 and the airport control console can communicate with each other, the central control unit can adjust the output of the power of the control subsystem 13 according to the collected signals received by the communication system 11, so that the whole device has the same horizontal speed as the aircraft when the aircraft lands, and the aircraft is kept horizontally and relatively static with the device when the aircraft lands on the landing board 4 of the aircraft.
When the aircraft lands, the power system 13 drives the linear motor 7 in advance, so that the device accelerates and tracks the aircraft, the linear motor adopts a long primary linear motor, the primary width of the motor is larger than the secondary width of the motor arranged on the platform, and the linear motor can work normally when the platform is greatly fluctuated up and down; the communication system 11 will track the speed and position of the aircraft and the device will actively track the speed and position of the aircraft in the event of a failure of the aircraft communication, so that the whole device will have the same horizontal speed as the aircraft when receiving the aircraft, keeping the aircraft horizontally relatively stationary with the platform when landing on the platform.
After the aircraft has landed on the platform, the cushioning system will begin to operate, absorbing the impact of the aircraft, and the braking system 12 will then brake to complete the final receiving operation.
Central control system
Firstly, the central control system is used for realizing the arrangement analysis and the instruction grading processing of all data of the platform, and realizing the weight estimation of the aircraft according to the established landing model basic parameter database when the platform works, thereby realizing the estimation of the landing instant impact force of the aircraft and the analysis of the braking force required by the platform braking process; by receiving the data of the communication system 11, establishing an airport three-dimensional space coordinate and an aircraft dynamics model, predicting the aircraft motion trail in real time, and adjusting the thrust of a linear motor 7 of the power system; and finally, the central control system tracks the parameter changes of all the systems, coordinates the work of all the systems and realizes the safe receiving of the aircraft.
Communication system
The communication system 11 adopts the airport primary radar aircraft capturing technology to realize the speed scalar measurement and initial position estimation of the aircraft, and realizes the accurate positioning and speed measurement of the aircraft through a laser radar to realize the instant detection of the aircraft position vector, and besides the laser radar, the mode is not limited to a high-speed camera, a GPS, beidou and the like; aiming at the problem of aircraft positioning, interaction and interaction are also formed with the aircraft, and in the aspect of accurate positioning, the two are combined together to realize accurate positioning.
The communication system 11 of the device can be connected to the existing communication systems of the aircrafts and the control console for multiparty communication, and the communication system can realize two-party and multiparty communication, uninterrupted data transmission and management party communication control authority access by utilizing the existing very high frequency data link (VDL) communication technology.
Power system
The power system 13 drives the landing receiving device through the linear motors 7 arranged on two sides of the platform, and impact resistance control of the linear motors 7 is realized through speed-free, sensor-free control and traction anti-lateral deviation control at the moment that the aircraft lands on the platform; the linear motor adopts a long primary linear motor, the primary width of the motor is larger than the secondary width of the motor arranged on the platform, and the linear motor can normally work when the platform is greatly fluctuated up and down; the power system 13 may be powered by wireless charging, a battery, or a traction grid.
Wheel set
The wheel type design adopted in the embodiment has good buffering effect, and the used tire is combined with other buffering devices such as a hydraulic buffering device, a pneumatic buffering device and the like in the wheel set 6 structure and the electromagnetic damping device 10 arranged on the platform to form a buffering system together, so that potential energy of an aircraft during landing can be fully absorbed.
Braking system
After the aircraft is received and fixed, the platform starts to decelerate, the platform mainly depends on the braking system 12 of each modularized unit to decelerate, the linear motor 7 of the power system 13 can also perform regenerative braking during device braking, and when the aircraft has other deceleration mechanisms such as the back-thrust braking of an engine, the platform can mutually cooperate with the aircraft to jointly decelerate so as to achieve better braking effect.
Receiving fixing device
The receiving and fixing device on the landing plate 4 of the aircraft comprises a front blocking baffle 1, a middle blocking baffle 2, a left blocking baffle 9, a right blocking baffle 8 and a rear blocking baffle 3, which jointly play a role in receiving and fixing, and an auxiliary landing device is also arranged on the landing plate, so that the landing gear of the aircraft can not be opened, and the aircraft is assisted to land.
The receiving and fixing device can be placed and stored on the landing plate 4 of the aircraft, so that the visual field of the landing plate is flat and wide when the aircraft lands; when receiving fixed aircraft, receive fixing device in lifting shrink, fixed aircraft, fixed accepting device need exist certain redundant space, when guaranteeing that the aircraft descends and have certain error, also can be accurate fixed aircraft.
In the use process of the aircraft lander, a proper number of modularized units are required to be freely spliced and combined to form a whole set of linear motor driving wheel type landing device, and all modules are rigidly connected to ensure that the modules are combined to form a stable whole.
According to the technical scheme provided by the embodiment, the power system in the linear motor driven aircraft wheel type landing receiving device provides power for the device, so that the device is accelerated to a proper speed; the buffer system enables the mechanical stress to be small when the aircraft lands and is recovered, and the aircraft can be safely, reliably and stably received when a landing accident occurs, so that the damage probability of the aircraft is reduced; the braking system can enable the aircraft to be orderly decelerated and braked after landing on the device; the communication system enables communication between the device and the aircraft, and between the device and the airport control console, so as to ensure that the whole device has the same speed as the aircraft when the aircraft lands, and the aircraft is kept horizontally and relatively static with the device when the aircraft lands on the landing board of the aircraft. The central control system realizes the arrangement analysis and the instruction grading processing of all the data of the platform and coordinates the work of each system. The front blocking baffle and the middle blocking baffle provide deceleration thrust for the aircraft; the left and right side blocking baffles provide good balance capacity and contact friction force for the aircraft, and meanwhile, excellent damping effect can be achieved, so that the aircraft can be stably landed and decelerated; the rear blocking baffle plays a role in preventing the aircraft from slipping.
For further explanation of the aircraft landing device, the embodiment uses three modular units for detailed explanation, but in practical application, the number of the modular units should not be limited to this number, and a suitable number of the modular units should be selected for combination according to a specific aircraft model, for example, the width of the device can be increased by arranging multiple groups of connecting devices and modular units side by side, or the length of the device can be increased by connecting more modular units, and the combination should be reasonably arranged according to the model of the aircraft.
Each module bottom formed by three modularized units comprises a wheel set 6, a power system 13, a communication system 11, a braking system 12, a buffer system, a central control system and a linear motor 7, wherein a front blocking baffle 1, a middle blocking baffle 2, a left blocking baffle 9, a right blocking baffle 8 and a rear blocking baffle 3 are fixed on an upper aircraft landing plate 4, and the structures are arranged on a vehicle body frame 5.
The power system 13 is driven by linear motors 7 arranged on two sides of the platform, and the power system 13 can supply energy to the platform and can be powered by wireless charging, a storage battery or a traction network.
The communication system 11 and the aircraft can communicate with each other, the communication system 11 can transmit the signals collected by receiving to the central control system, so as to adjust the output of the power of the control subsystem 13, thereby ensuring that the whole device has the same speed as the aircraft when the aircraft lands, and ensuring that the aircraft lands on the landing board 4 and keeps horizontal relative rest with the device when the aircraft lands on the landing board 4.
When the landing receiving work of the aircraft begins, the communication system 11 firstly receives signals, the communication system 11 adopts the airport primary radar aircraft capturing technology to realize the speed scalar measurement and the initial position estimation of the aircraft, and the laser radar is used for accurately positioning and measuring the speed of the aircraft to realize the instant detection of the position vector of the aircraft. The communication system 11 also needs to be connected to the existing communication systems of the aircrafts and consoles for multiparty communication, and utilizes the existing very high frequency data link (VDL) communication technology to realize two-party and multiparty communication, uninterrupted data transmission and management party communication control authority access.
The communication system 11 transmits data to the central control system, the central control system establishes three-dimensional space coordinates of an airport and an aircraft dynamics model according to corresponding data after receiving the data from the communication system 11, predicts the motion track of the aircraft in real time, and adjusts the motor thrust of the power system 13 so as to ensure that the receiving device can keep corresponding horizontal speed with the aircraft when the aircraft falls on the receiving landing device.
The central control system also realizes the weight estimation of the aircraft according to the established landing model basic parameter database, further realizes the estimation of the impact force of the landing moment of the aircraft and the analysis of the braking force required by the platform braking process, and adjusts the output of the buffer system according to the corresponding data; the central control unit is used for realizing the arrangement analysis and the instruction grading processing of all the data of each system of the platform, and finally the central control system is used for tracking the parameter change of each system, coordinating the work of each system and realizing the safe receiving of the aircraft.
The power system 13 provides power for the device, and after the power system 13 receives data from the communication system 11 and the central control system, the receiving device is driven to accelerate and track the aircraft in advance before the aircraft lands. The power system 13 drives the receiving device through the linear motors 7 arranged on two sides of the platform, in the process that the power system drives the platform to accelerate, the communication system 11 can continuously track the speed and track the position of the aircraft, and when the communication of the aircraft fails, the communication system can actively track the speed and track the position of the aircraft, so that each module can have the same horizontal speed as the aircraft when receiving the aircraft, and the aircraft can keep horizontal relative static with the platform when landing on the platform.
After the aircraft falls on the device, the buffer system can slow down the impact and vibration of the aircraft during landing, the wheel type design adopted by the invention has good buffer effect on the used tire, and the buffer system is formed by combining hydraulic buffer, pneumatic buffer and the electromagnetic damping device 10 arranged on the upper part of the platform together, so that the potential energy of the aircraft during landing is fully absorbed, and the landing receiving safety can be well ensured.
The left side blocking baffle plate 9, the right side blocking baffle plate 8, the front blocking baffle plate 1, the middle blocking baffle plate 2 and the rear blocking baffle plate 3 on the landing plate of the aircraft start to operate and are quickly folded, the effect of fixing the aircraft is achieved through combined action, good balance capacity and contact friction force are provided while the fixing effect is met, meanwhile, an excellent shock absorption effect can be achieved, and the aircraft can be ensured to land and decelerate stably. The landing gear mounted on the landing plate 4 can be lifted to a proper height to support the aircraft when the landing gear of the aircraft cannot be opened, and the landing gear can assist the aircraft in landing.
The receiving and fixing device on the landing plate 4 of the aircraft can be placed and stored on the landing plate 4 of the aircraft at ordinary times, as shown in fig. 7, so that the visual field of the landing plate is ensured to be flat and wide when the aircraft lands. When receiving and fixing the aircraft, the receiving and fixing device is lifted and contracted to fix the aircraft.
The braking system 12 is activated after the aircraft is received and secured by the device, so that the landing gear and the aircraft start to brake by decelerating, and the platform and the aircraft can cooperate to decelerate together to achieve a better braking effect when the aircraft has other deceleration mechanisms, such as the thrust reverser brake of the engine. The linear motor 7 adopted by the power system 13 is driven, and the regenerative braking of the linear motor 7 can also participate in the deceleration braking of the device.
After the final landing receiving platform and the horizontal speed of the aircraft are zero, the landing receiving work is completed once.
In summary, the power system in the linear motor driving wheel type landing receiving device of the aircraft provides power for the device, the communication system realizes communication between the device and the aircraft and between the device and the airport control console, the braking system provides deceleration braking for the device, the blocking baffle fixes the aircraft after the aircraft falls, the buffer system reduces impact and vibration of the aircraft after falling, the aircraft can be safely, reliably and stably received when falling accidents happen, the damage probability of the aircraft is reduced, and the life and property safety of personnel in the aircraft is ensured; when the aircraft is forced to land, the platform can keep relative static at the same speed, and after the aircraft lands and is locked by the platform, the platform starts to decelerate, so that the problems that the aircraft collides with the ground, rubs, deviates from a runway, cannot land and the like after landing faults are effectively prevented.
The device for receiving the landing of the linear motor driving wheel of the aircraft can effectively eliminate the risks caused by hard landing or incapability of landing when the aircraft encounters landing gear faults, brake failure, engine faults and the like during landing. When the aircraft faces the landing problem, the aircraft can directly fall on a landing device which keeps relative movement with the aircraft, a buffer system is arranged on the landing device, the adopted wheel type design has the characteristic of high bearing capacity, the hard impact during landing can be effectively reduced, and the device can be locked and fixed with the aircraft after landing of the aircraft, so that the aircraft is prevented from unbalance, and the aircraft is prevented from rubbing on fire or rushing out of a runway. The wheel type design applied by the device has the advantages of mature technology, strong shock resistance, no need of paving a track and strong economical efficiency, and can well realize speed tracking and position tracking when the aircraft lands.
Those of ordinary skill in the art will appreciate that: the drawing is a schematic diagram of one embodiment and the modules or flows in the drawing are not necessarily required to practice the invention.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment mainly describes differences from other embodiments. In particular, for apparatus or system embodiments, since they are substantially similar to method embodiments, the description is relatively simple, with reference to the description of method embodiments in part. The apparatus and system embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (7)
1. An aircraft landing gear is characterized by comprising a plurality of modularized units, wherein the modularized units can be spliced with each other;
the spliced module unit comprises a vehicle body frame, an aircraft landing plate arranged on the vehicle body frame, a receiving and fixing device, a central control system, a braking system, a buffer system, a communication system, a power system and a wheel set;
the communication system is in communication connection with the aircraft and the airport control console, and when the lander operates, the central control system adjusts and controls the output of the power system according to the collected signals received by the communication system, so that the spliced module units have the same horizontal speed as the aircraft when the aircraft descends;
when the aircraft lands, controlling the power output of the power system, enabling the spliced module units to accelerate and track the aircraft, enabling the communication system to track the speed and the position of the aircraft, and enabling the device to actively track the speed and the position of the aircraft when the communication of the aircraft fails;
after the aircraft falls onto the platform, the buffer system can start to work to slow down the impact force of the aircraft, and then the brake system can brake to finish the final receiving work;
the central control system is used for carrying out arrangement analysis and instruction grading processing on all data of the lander;
estimating the weight of the aircraft according to the established basic parameter database of the landing model when the lander works, and estimating the impact force of the landing moment of the aircraft and analyzing the braking force required in the platform braking process based on the weight of the aircraft;
the central control system establishes three-dimensional space coordinates of an airport and an aircraft dynamics model by receiving data of the communication system, predicts the motion trail of the aircraft in real time, and adjusts the thrust of a linear motor of the power system;
the central control system tracks the parameter changes of all the systems, coordinates the work of all the systems and realizes the safe receiving of the aircraft;
the communication system (11) adopts an airport primary radar aircraft capturing technology to measure the speed scalar of the aircraft and estimate the initial position, and carries out accurate positioning and speed measurement of the aircraft through a laser radar to realize the instant detection of the position vector of the aircraft;
aiming at the problem of aircraft positioning, interaction and interaction are needed to be formed with an aircraft, and in the aspect of accurate positioning, the two are combined together to realize accurate positioning;
the communication system (11) can be connected into the existing communication systems of the aircraft and the control console for multiparty communication, and the communication control authority access of the management party is realized by utilizing the existing very high frequency data link communication technology and realizing the two-party and multiparty communication without intermittent data transmission;
the power system comprises linear motors arranged at two sides of the lander;
at the moment that the aircraft falls onto the lander, the impact resistance control of the linear motor is realized through speed-free, sensor-free control and traction anti-lateral deviation control;
the power system can be powered by wireless charging, a storage battery or a traction network.
2. The aircraft landing gear of claim 1, wherein the power system includes a linear motor employing a long primary linear motor having a primary width greater than a secondary width mounted on the platform.
3. An aircraft landing gear according to claim 1, wherein the wheel sets are mounted on the underside of the body frame by cushioning means.
4. An aircraft landing gear according to claim 1, wherein a braking system is provided on each modular unit;
after the aircraft is received and fixed, the lander starts to decelerate, the lander decelerates by virtue of the braking system of each modularized unit, the linear motor of the power system regenerates the brake when the device brakes, and if the aircraft has a reverse thrust braking mechanism of an engine, the lander and the aircraft mutually cooperate to jointly decelerate.
5. The aircraft landing gear of claim 1, wherein the receiving fixture includes a front blocking baffle, a middle blocking baffle, a left blocking baffle, a right blocking baffle, and a rear blocking baffle;
the blocking plate is preset on the landing plate of the aircraft according to the model of the aircraft.
6. The aircraft landing gear of claim 5, wherein the receiving fixture is adjustable in position relative to an aircraft landing plate;
when receiving fixed aircraft, receive fixing device in lifting shrink, fixed aircraft, fixed accepting device has the redundant space of setting.
7. The aircraft landing gear of claim 1, wherein rigid connection is employed between the modular units.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210106072.9A CN114435615B (en) | 2022-01-28 | 2022-01-28 | Aircraft lander |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210106072.9A CN114435615B (en) | 2022-01-28 | 2022-01-28 | Aircraft lander |
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| Publication Number | Publication Date |
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| CN114435615A CN114435615A (en) | 2022-05-06 |
| CN114435615B true CN114435615B (en) | 2024-01-19 |
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| CN202210106072.9A Active CN114435615B (en) | 2022-01-28 | 2022-01-28 | Aircraft lander |
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| CN111498132A (en) * | 2020-04-27 | 2020-08-07 | 南京工程学院 | Servo tracking robot for intelligent safe landing of aircraft landing gear fault |
| CN113247286A (en) * | 2021-03-04 | 2021-08-13 | 北京交通大学 | Aircraft magnetic suspension landing receiving device |
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| FR2936079B1 (en) * | 2008-09-16 | 2010-09-17 | Thales Sa | METHOD FOR MONITORING THE LANDING PHASE OF AN AIRCRAFT |
| US9296488B2 (en) * | 2013-03-06 | 2016-03-29 | 3Rd Millennium Solutions, Inc. | Aircraft braking early warning system |
| US10059465B2 (en) * | 2014-11-19 | 2018-08-28 | The Boeing Company | System to accelerate and decelerate aircraft for take-off and landing |
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|---|---|---|---|---|
| CN1305925A (en) * | 2000-10-13 | 2001-08-01 | 王丽莉 | Carriage for forced landing of aircraft with landing chassis |
| CN101837838A (en) * | 2010-05-07 | 2010-09-22 | 霍方华 | Security landing-assistant rescuing system for breakdown plane |
| CN111356633A (en) * | 2017-09-14 | 2020-06-30 | 伊利亚·罗森伯格 | Electric train system and method for autonomous takeoff and landing of aircraft |
| CN111498132A (en) * | 2020-04-27 | 2020-08-07 | 南京工程学院 | Servo tracking robot for intelligent safe landing of aircraft landing gear fault |
| CN113247286A (en) * | 2021-03-04 | 2021-08-13 | 北京交通大学 | Aircraft magnetic suspension landing receiving device |
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| Publication number | Publication date |
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| CN114435615A (en) | 2022-05-06 |
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