JP2015016847A - Improvement of operation stability achieved by effect of rotation drive of aircraft tire wheel due to airflow velocity and profit-and-loss effect due to tire damage safety - Google Patents

Abstract

PROBLEM TO BE SOLVED: To realize operation stability, stability of the attitude of an airframe on landing, an economic effect of reducing exhaustion of consumable members and prevention of damage to airframe members by debris produced on rupture breaking by an effect of rotating the tire wheel of a landing gear of an air craft.SOLUTION: A knife cut groove A-A' is provided in a circumferential-part surface (tread part) of a ground surface of a tire, and a convex part B-B' is provided in the side-surface part. A tire wheel is rotated at a high speed by utilizing resistance energy of air flow. Securing stability of the attitude on landing, a profit-and-loss effect of the drive force produced by rotation force of the tire wheel on the runway surface, elimination of harmful factors in a state where bouncing occurs at an early stage and reduction of tire wear and damage are realized by securing rotation energy, with inertial energy of the rotation and a gyro effect by the rotation force combined, and releasing and discharging the rotation energy again.

Description

  This is a method technique for generating and generating a rotational drive of a tire wheel in the air space of a landing stroke with respect to an aircraft by the shape imparting function of the present invention. Rotation is the flywheel effect generated by the moment, and the gyro effect generated by the high-speed rotation is the effect of generating stable landing posture. The effect of reducing the factor of the bounce occurrence by the bodily effect and the inertial drive energy of the rotational force by preventing the occurrence of dangerous aircraft bounce during landing. In particular, high-speed friction slip at the time of grounding (touchdown) generates tire smoke, and the thermal divergence generates a flat spot in the toret and damages the tire. The driving energy effect by rotation reduces the damage to the maximum. The source of driving energy for rotating the tire wheel is the airflow velocity in the air space, and no other power source expenditure is required. It relates to aeronautical technology that produces this beneficial effect.

  In a conventional aircraft, the aircraft cannot be navigated unless it takes a take-off and landing process from a two-dimensional surface on the ground surface to a three-dimensional aerial space and the reverse process at a moderate angle and an optimal speed. Current operations are implementing them. In the case of takeoff of a piece or rocket, a safe flight path is not possible without a thrust that burns fuel explosively about 1.3 times its own weight at the minimum, and in the extreme, thrust that supports its own weight Only the amount of fuel consumed is wasted. The achievement of the flight is directly related to the acceleration dynamics theory of gravity. On the other hand, the current aircraft takes the form of flight that equally divides the influence of gravity for economic efficiency and safe operation, and the cost-effectiveness of its operating mechanism exhibits excellent and beneficial physical effects. Therefore, in the case of a rocket, it becomes a so-called one-way disposable aircraft that does not have the ground-sliding device that is the subject of the present invention. In the case of a result rocket flight, the subject of the present invention is out of the question. This is a general description of flying objects.

  In the case of aircraft Unlike the case of the above-mentioned rockets, the invention of the aircraft, in particular, is required for long-term use for long-term operation, and safe operation is maintained for a long time by repeated take-off and landing on the ground and in the air. Is the most important landing device, and without this device, flight will not be possible. Landing devices are broadly divided into shock absorbers that relieve the impact of the entire weight of the aircraft during landing and tire wheels that rotate in direct contact with the ground. The tire wheel is constituted by a pressure pneumatic tire mainly composed of a metallic wheel portion and rubber fitted on the outer peripheral portion thereof.

  The aircraft tires are required to have maximum performance. Taking the case of a jumbo jet as an example, the grounding speed requires a maximum speed of 360m / s, including the maximum permissible level, and at the same time, a load of about 20t or more, which is shared as one aircraft weight at the time of landing. Has been. A total body weight of 350t is supported by a total of 18 totals, including two nose wheels, 8 main wing wheel left and right totals, and 8 fuselage wheel left and right totals, one of which is the total weight of a large 10 ton truck on land. It is an amazing function and performance that can be fully supported by one. Aircraft tires are expensive and most important mechanical parts because they have special high performance.

  Since the first flight of the Wright brothers motorized aircraft, the current state of the tire wheel, which is the current aircraft and landing gear, should have been exposed to the airflow only when landing. It is the only cause of air resistance. In some small aircraft that do not have a retractable leg function, some aircraft have a streamlined cover attached to the tire as a countermeasure against air resistance, but this has the function of rotating the tire part which is the subject of the present invention It's not something The idea of the landing gear part is one of the few undeveloped fields to improve even though it is almost completed in aircraft engineering.

"How does Sanuki Yasuko Jumbo Jet fly" Kodansha "Jiro Kondo, why planes fly" Kodansha "Science of tires Naomi Obori" Kodansha

  It is indispensable for an aircraft to repeatedly use takeoff and landing operations. Here, when considering only the landing gear, which is the proposition of the present invention, the shock absorber that constitutes the majority of the present invention is configured with a shock absorbing function by the function of an air oleo system using high pressure compressed gas and buffer oil. . In the medium to short term, this device shows almost no wear or wear. Only the tire wheel, especially only the tire part, directly handles various conditions outside the fuselage, especially the hard runway surface, and stably handles most of a number of adverse conditions. The tire portion is a member that is consumed more rapidly than other airframe materials.

When the aircraft enters the landing posture process, the landing gear is exposed to the outside from the fuselage and fixed to the fuselage structure so that it can withstand the impact of landing (gear down fixation check). The landing gear exposed to the airflow receives strong wind pressure resistance in line with the hydrodynamic theorem. Wind pressure resistance of the total landing gear is: air density (kg / m ³ ) × total landing gear's projected area (m ² ) × speed (m / s) squared × 1/2 simple fluid dynamics Can be calculated by the resistance equation of By the way, when looking at the resistance amount in m ² unit here, the wind pressure resistance amount received by the landing gear at the time of gear down of 360 km / h (100 m / s) is about 5,000 kg per 1 m ² , this resistance. The component is a negative element in conventional navigation.

  When the aircraft enters the final stage of landing, the aircraft fluctuates due to complex air currents, especially the turbulent airflow from the ground and terrain makes all the control surfaces of the aircraft function tactilely, and maneuvering makes the aircraft stable. I'm completely maneuvering. Pilots struggle to control aircraft landing more than during takeoff maneuvers. Stabilization technology is awaited by the development of a new mechanism that can control the swing of the attitude of the aircraft.

  At the moment when the aircraft touches down, there is an approach angle that causes serious damage to the aircraft at the boundary of about 3 ° of the ideal landing approach angle depending on the landing posture and landing approach angle. If the approach angle is less than 3 °, there will be no impact on the aircraft, but the sliding stop distance will be significantly longer. The approach angle where the airframe damage occurrence rate reaches a great degree starts from 3 ° or more, and the possibility of occurrence of an accident becomes large, and a so-called landing device or airframe is subjected to an excessive impact or load. Most pilots will not make such mistakes unless the aircraft has a control system or functional fault.

  Even if the landing posture is at an ideal angle, it is possible to create the worst situation where the aircraft is struck against the ground by a sudden downdraft due to the factors described in [0009]. The added airframe overloads the buffer stroke limit of the shock absorber, and in the worst case, the attachment portion and the structural member of the airframe body are safely destroyed by the fuel saving function. However, due to the reaction stress generated before the moment of failure, the fuselage, especially the nose, jumps up, forms the angle of attack of the main wing, causes the wing to stall, and this time there is a shock absorbing force of the shock absorber that thrusts into the runway surface from the nose The phenomenon repeats over and over while decaying.

  It is said to be so-called bouncing, and it will be in an uncontrollable and unrecoverable state regardless of what optimum operation the pilot fears most. In the worst case, the fuselage is overturned. The accident video at the N hub airport in the Far East was worthy of fear. Even if a bouncing state occurs in the fuselage, further improvement of the shock absorber system is required, which can be a one-bound state and contain the repeated state. However, if there is no shock absorber, the bouncing state does not occur. Even in this case, the fuselage landing is inevitable. Here, the bouncing state is a chain of repeated bounce and rebound. A bounce jumps upward from a horizontal plane, and a rebound is associated with a so-called sine curve figure that fluctuates up and down with a zero volt base line in an AC voltage waveform diagram that can be expressed by sinking downward from the horizontal plane.

  When the aircraft is in the aerial space during the landing process, the wind pressure resistance that the exposed part of the landing gear receives from the oncoming airflow is a negative so-called negative factor for the operation of the aircraft. In the present invention, a negative factor generated by exposing only the landing gear is a negative factor in landing operation of an aircraft, particularly in the navigation from the vicinity of the airport site to the landing landing and stoppage in the area. Rotating the tire wheel stabilizes the maneuvering, stabilizes the attitude during the aircraft's landing, reduces the consumption of the consumables, and provides economic benefits. This is a devised technology that makes four birds with one stone, which solves negative factors by preventing damage, etc., and transforms negative harmful projects into numerous benefits.

  The effect of the invention is to rotate the exposed part of the landing gear, in particular the tire wheel in the forward direction. The rotational force uses the flow velocity energy of the opposing airflow as the flow velocity of the airflow passing through the projection surface of the tire wheel and its side surface. The flow velocity energy of the gas received by the exposed part was explained in [0008], but the rotation method for rotating the tire wheel in the forward direction is the circumferential part surface (tlet part) of the tire contact surface and the tire side part (shoulder part). 2 to the side part surface) The figure shape shown in the present invention [Fig. 2] is knife-cut to the torette part, and the shape is baked on the side part with a rubber material of the same quality as the tire component during the manufacturing process. . Alternatively, if there is a flexible, tough, lightweight, and excellent quality material, it is possible to bond a figure that has been cut by a method that does not peel off. An effect can also be obtained by attaching and installing a shape mechanism that induces the rotation shown in FIGS.

  The torque received by the shaped object of the invention figure by the flow velocity of the airflow gradually overcomes the inertia weight of the tire wheel, energy is accumulated, and rotation starts. Eventually, the flow velocity of the airflow and the peripheral speed of the tire wheel become the same. The diameter of the tire wheel of a large aircraft aircraft is about 1 m, tire width is about 0.6 m, tire wheel weight is about 100 kg or more, tire wheel circumferential length is over 3.2 m, and the airflow velocity is about 100 m / s. Thus, the rotation speed of the wheel is 32 rotations per second, about 1900 rpm, and the air flow velocity, which has been a negative factor in the past, is applied to the tire wheel by rotational energy due to the effect of the devised figure and is rotated by itself.

  The rotation of a given tire wheel is a flywheel having a rotation speed of about 32 rotations per second and a weight of about 100 kg or more. Its inertial energy is strong. The kinetic energy that becomes the flywheel can be calculated by the following equation: E = 1/2 × G × V × V, where G is the weight of the rotating body and V is the circumferential speed / second of the rotating body. If simply calculated, in this specification, the accumulated rotational energy for one tire wheel is about 500 tons-meter. This huge amount of the total amount of energy was obtained from the all-landing landing wheel.

  The ripple effect of the total amount of rotational energy possessed by the entire landing ring of the fuselage is designed to be located near the center of gravity of the fuselage in order to stabilize the fuselage. In this connection, the inertial force that has become like a flywheel exerts a gyro effect with high efficiency in the vicinity of the center of gravity of the fuselage, and causes stability of the fuselage. Since the rotation direction axis and posture of the tire wheel are positioned perpendicular to the horizontal plane of the airframe, the inertial energy and the gyro effect are means that can sufficiently contribute to maintaining the horizontal posture of the airframe.

  When an aircraft enters a landing position, it must always enter the runway at a speed greater than the stall speed of the aircraft. The ground speed is approximately 200 km to 300 km per hour for large aircraft. Because the frictional heat is generated between the objectives, the melting evaporation disappears due to the heat, the collision between the frictional surfaces and the fracture tearing defect due to weight load. The material that is weak in strength between the friction materials due to the occurrence of friction, etc., is initially frictionally damaged and consumed. Here, concrete runway surface with special strength versus toughened rubber is used, but it wears out first due to the characteristics of the rubber material of the tire.

  In order to eliminate the friction at the time of sliding, it is a correct answer to adopt a tire wheel that is a rotating body that exhibits a minimum coefficient of friction in terms of mechanical efficiency. However, the friction application range of this roller rotating body is effective at low and medium speeds, but the roller effect is not applied at high speeds. The resistance coefficient of rolling friction on the runway surface under this condition is the best 0.01. (Although it is an aside, if the runway surface is covered with an oil film of oil and fat, the frictional resistance coefficient becomes 0.001 and the aircraft cannot be braked.) Even if there is a tension of the inertial force of the weight of the roller itself and the adhesion indicated by the frictional resistance coefficient, it does not rotate easily because it is an inertial body immediately. Even if this phenomenon is expanded to the actual state of the tire wheel inertial force analysis, it is physically equivalent.

  Assuming that the tire wheels of conventional aircraft do not rotate substantially, the negative inertia inherent in their weight immediately corresponds to the ground speed as non-inertial weight energy, as explained in [0016]. , It causes the cause of instantaneous high speed friction state. A so-called tire constituent is the occurrence of tire smoke caused by burn-off delamination due to frictional heat, and this is evidence. If you touch down at a ground speed of 250 km to 300 km per hour and a speed of 70 m to 83 m per second, the moment is defined as 1 second. From the viewpoint, it is not as important as the left. It can be confirmed that an infinite number of black tire marks are adhered to the runway surface near the threshold (thread shoulder) about 20 to 30 m. This is a slip mark and evidence of the occurrence of tire smoke. The present invention is a disclosure of the inventive technique for rotating a tire wheel for exempting a tire from damage caused by generation of a flat spot due to friction slip of the tire portion or abnormal wear.

  The most feared by the pilot is the bounce phenomenon that can be called force majeure during landing. Each airport has taken thorough measures to prevent weather forecasts, but it is an unfamiliar airport or the worst accident can be caused by the sudden downburst. Even if rarely misjudgment occurs due to improvement of current weather forecast monitoring technology, sometimes small and medium bounces can occur even if it is not a strong bounce phenomenon, looking at the landing tire slip trace at this time seems to be twisted strangely Inconsistent state is observed. The effect of the technology of the present invention includes an important effect that makes it possible to stop the bounce phenomenon in a one-bound state at least, if the bounce phenomenon is small or small.

  Here, the phenomenon of bouncing is verified in detail by enlarging 1 second by 100 times. In 1 second, which is instantaneous under the condition of [0020], the gliding body advances about 70 to 83 m. At this time, it is assumed that the ground was hit by ground acceleration at a gravitational acceleration of 1 G due to a downburst from about 10 m above the ground. The navigation descent angle at this time is about 8 °, which is slightly less than 3 times the appropriate descent angle of 3 °, and the tire wheel of the landing gear eventually comes into contact with the runway surface, where the descent is about 1 m in 0.1 seconds. The shock absorber contracts at a rate and the weight of the fuselage is increased, and the air oleo function is completely shrunk. (It is assumed here that the shock absorber is overloaded and the fuselage structure is not damaged.) The amount of shrinkage depends on the weight of the fuselage. The conditions are very different. This weight factor is an important bouncing bounce factor (extremely speaking, the so-called unsprung weight theory in which bouncing does not occur if the weight of the aircraft is light). Inertial energy of about 245 tons or more becomes a negative factor, and the negative inertial energy is given to the runway surface. This is a momentary kicking phenomenon, which is a so-called intense braking phenomenon.

  At this moment, depending on the weight of the fuselage, the shock absorber of the main leg is completely contracted, and this time it reacts and shifts to extension. Due to the braking effect, the fuselage further doubles with the extension reaction energy after contraction of the shock absorber around the tire axis, accelerating the kicking posture, and at that moment the nose is hit against the road surface and the weight of the fuselage on the shock absorber at the nose Part of the accelerating weight, the shock absorber contracts and restores soon, and the generation of repulsive force causes the nose to jump up, creating a vigorous airflow on the lower surface of the main wing and causing the wing to stall. It becomes a vicious circle. The periodic pattern of the repetitive chain is irregular and inconsistent depending on the state of the aircraft. Because of the irregularity, even an excellent pilot cannot control stabilization only when this phenomenon occurs.

  Here, assuming that about 245 tons of inertial energy for one bottle is reversely applied to the conventional case, what happens if a forward rotation is first applied to the tire wheel? Is the expectation of the result of the execution effect shown by the derivative technology of the present invention. This is a devised effect for eliminating the causal factor that becomes part of the trigger of bounce, that is, the negative factor of the brake effect caused by the negative inertia energy. In the state shown in [0023], what happens if the tire wheel already has a desired rotation before landing, in this case, assuming that the cruise speed when descending is about 360 km / h and the speed is 100 m / s, Since it is a landing gear, the inertial energy has already exceeded 500 ton-meters and has already acquired sufficient inertial energy. The amount of inertia energy, which was a negative factor at the time of conventional landing, is now used as a reverse driving force.

  The control of the malignant aircraft behavior that hits the nose of the second stage against the road surface in the bounced state is the effect of this driving force due to the strong total driving force of the flywheels of all tire wheels installed at the lower part of the center of gravity of the aircraft It is as if the nose up moment is generated instantly to prevent head nose buds. Changing the bounce into a single bounce will never repeat the malignant chain. As a result, the aircraft posture is kept parallel to the runway surface, and the gyroscopic effect of the tire wheel is restored to normal aircraft posture, creating a chain of superiority. In other words, the powerful energy capacity of the flywheel-like ability is directly connected to the runway surface momentarily and directly to the tire wheel, and the effect of the driving force acts as an absolute to restore the normal posture. At this time, the malignant / dominant aircraft posture is determined by determining the cause of safety in the course of several seconds for a few seconds in the case of an aircraft running distance of 70 m with an instant of 1 second. The effect of only one device will spread many dominance effects, and the chain effect of the results will be like five birds with one stone. This single effect of the invention is comparable to the amount of results obtained by integrating single technologies.

  In conventional aircraft, since the tire body is almost stationary at the moment of landing, a high-speed friction slip is generated between the runway surface and the tire of the tire wheel. In particular, this structural material causes peeling, combustion exhaustion, etc., so-called tire smoke phenomenon. The running safety strength of the tire body is significantly reduced by the generation and generation of flat spots, mainly erosion defects in the tire structural member. If the tire according to the present invention is preliminarily provided with a rotation corresponding to or faster than the ground speed, all the problems are solved. The solution effect increases the safety of expensive tires, extends the period of use and contributes to the economics of aircraft operation.

  The aircraft is in an unstable state due to the influence of the ground, topography, and ground structures during the landing process. If the tire which is the subject of the present invention is pre-rotated and placed, the effect of the accumulated physical mass due to the gyro effect acquired by the amount of inertial energy and the rotational speed exerted by the rotation is a turbulent airflow It can cope with energy disturbance. It can contribute to the stabilization of the landing posture of the aircraft and the stability of maneuvering.

  When the aircraft is at the end of the landing posture, suddenly abnormal turbulence and downdraft may cause the aircraft to fall and hit the runway surface. The so-called bounce occurs at the first time of the first bounce, and the device eliminates the bud that caused the occurrence within an initial time of 0.1 seconds (the sliding distance of the aircraft is about 7 m at this time). The principle of this invention is that the tire wheel, which is the subject of the present invention, gives the amount of inertial energy that corresponds to the ground speed in advance or that the rotation further includes, so that the driving force of the tire wheel can be instantaneously released. It is utilization. Even in the worst case of the occurrence of bounce in the situation where the airframe structure is destroyed, the effect of the idea will reduce the degree of damage and extent of damage.

  The tire wheel is rotated by imparting the shape function of the means for giving rotation to the tire wheel of the present invention, but the source of energy to rotate was inherently harmful, which is the utilization of the airflow velocity of the airflow from the moment of stepping out. Useful use of things. There is no spending on the energy resources in the aircraft. This is the creation and effective use of energy resources to convert harmful elements into useful elements.

  The contribution of the technology of the present invention to the stability and safety of aircraft navigation will be verified with respect to the operating expenses described above. Improvement of maintenance time and economy by reducing tire wheel damage and wear, long-term preservation of the aircraft by reducing overload stress on the fuselage, and sudden burst due to inclusion of damage history inside the tire In particular, the reduction of damage to the main wing structural materials, loss of credit due to suspension of operation due to trouble, and loss of operational revenue, etc., prevent the occurrence of damage that should be in normal operational management. The effect of the device suppresses the generation of those harmful factors.

It is a model drawing of the windmill blade-like of the metal foil part attachment of a tire wheel. FIG. 6 is a schematic diagram of a shape addition in which a tire wheel tire part acts as a windmill blade. It is a correlation diagram of the cross section of a tire wheel, and an inner liner with a windmill blade. Automatic mechanism device for stopping rotational stress of the inner liner and adhesion to the body.

  Although the effects of the technology of the present invention have been described in the previous section, the cause of the one-storied and five-bird ripple effect is that the air velocity energy of the airflow opposed to the tire wheel is shown in [Fig. All you have to do is catch it with the device. As a result, high speed air flow energy injects rotational energy into the weight of the tire wheel, and eventually the peripheral speed of the tire wheel and the air flow velocity are in phase or higher, thereby completing the title of the idea. Since the airframe structural elements other than those of the present invention have already been completed, the present invention is not related.

  The subject of the present invention is to rotate the tire wheel in the cyclic direction depending on the wind pressure of the airflow. Here, the invented figure is completed at the end of the manufacturing process at the end of the manufacturing process, and the difficulty of manufacturing is raised by extending the technology of precision stamping on the general tire side. The success or failure of the possibility of manufacturing, which allows the build-up molding, can be sufficiently manufactured. The shape construction of the idea figure on the outer peripheral part of the tire circumference is formed with a concave groove structure by the same technique as the knife cutting used in the current tire manufacturing process.

  Functional devices that cause forward rotation to the metal wheel section must take into account that aircraft metal wheels are now mostly made of aluminum alloy. [FIGS. 3 and 4] The structure of the device type shown in FIG. 3 can be easily attached to and detached from the wheel body. The fact that this attachment / detachment can be easily performed does not hinder maintenance, particularly when changing tires. Although the aluminum alloy is relatively soft compared to the steel plate, the inventive device does not cause damage or harm to the wheel body, but is somewhat difficult.

  The shape of this device is an inner liner shape that fits closely with the outer surface shape of the main body wheel part. The liner ring part near the rim part of the main body wheel part has an airflow saucer-like shape of a so-called meteorological wind measuring instrument. Alternatively, a shape corresponding to the effect is arranged on the rim portion circumferential line of the liner. However, the shape of the tray must be designed to ensure the strength and strength to withstand after considering the wind pressure above the design factor.

  The rotation of the inner liner against the wheel due to wind pressure stress is restrained by four stat bolts embedded in the wheel land. The inner liner is provided with a diagonally cut slit designed to automatically contact with the wind pressure engaged with the four stat bolts to promote close contact. After complete close contact, both the wheel and inner liner are The set is completed by fastening with nuts.

  The formation of the inner liner of the tire body that fulfills the gist of the present invention of the tire body is requested by a manufacturer who specializes in tire production according to the design figure of the present invention, the manufacturing process is a conventional universal technology There is no manufacturing difficulty there.

  Forming and manufacturing that fulfills the gist of the present invention to be attached to the wheel body is a windmill-like wind energy receiving tray that contributes to the rotational drive that should receive the airflow wind speed, and the rotation of the shape in close contact with the circular shape of the outer surface of the wheel body It is divided into a stress receiving portion and a so-called inner liner body. In making the two parts that are divided into an integral structure, excellent rigidity is recognized, but difficulty in manufacturing occurs, so that the cost for manufacturing becomes expensive. Manufacturing methods do not want them cost-effectively.

  As the main application of the present invention, the main body of the entire inner liner-like invention body is divided into two or three parts in the circumferential direction, and the use material of each part is made of tensile strength steel plate. Improvement of the modern precision welding technology in general, making it easy to make a complicated rim-shaped spoon shape as shown in Fig. 3 by using a welded structure and adapting to design changes. However, there is no problem in maintaining the shape or the strength in the manufacture of these because of the strength requirement of the present invention.

  As shown in Fig. 3, the spoon-shaped wind saucer to the rim-shaped part or the equivalent shape is not fixed to the rim-shaped part, and only the spoon-shaped single-piece part is detachable in the 3L part. It can also be made removable so that it can be adapted to the usage conditions. This is an extension method of the method of embedding / removing wind turbine components (Christmas tree type embedding method) of the steam pressure receiving vane, which is the tip of the impeller of the steam turbine, or [Fig. 3] with a simple one-touch desorption mechanism shown in 3L. You may use the technology which shows the equivalent result.

2A Wind-power receiving tret section A-side surface of knife cut groove A-A 'is wind-power receiving section 2B Wind-power receiving tire shoulder to side portion convex section B-B' section B'-surface is wind-power receiving section 3A Wheel cross section 3B Airflow receiving function Part mounting inner liner body 3C Inner liner mounting wind power tray device schematic principle diagram 3D Stud vault or penetrating bolt embedded in the wheel, 4E 3E Slit mechanism combined with inner liner detent and adhesion function 3F Wind power tray, principle diagram 3G inner liner 3H Aircraft tire 3I Wind saucer, side view schematic principle diagram 3J Wind saucer mounting bolt and one-tachchi fastening device to inner liner body 3K Wind pressure drag stay 3L Wind turbine component unit Detachable one-touch device part 4A IN Over liner 3 divided portions innermost liner 4B innerliner rotational stress direction 4C wind flow pan stress direction 4D Suttatoboruto 4E fastening locking special nut and flat washer 4F wheel cross sectional 4G innerliner body of the body to Suttatoboruto of

Claims (1)

  The majority of aircraft accidents and aircraft damage occur during the landing process at the time of landing. The tire wheel is rotated at high speed by the energy newly acquired and generated by the effect of the present invention. The invention resides in securing and acquiring the total rotational energy of the rotated inertial energy and the gyro effect by the rotational force. Its energy effect is to ensure stable posture at the time of landing, the beneficial effect shown by the driving force on the runway surface due to the rotational force of the tire wheel, creation of safety by extinction of the accident factor at the initial stage of the occurrence of high-risk bounces, Reduce tire wear and damage. The effect was a harmful product in the past, and the resistance energy of the opposed air flow, which was a negative product, was utilized to produce a second engine power source. The case where the invention effect of the invention technology was a conventional adverse effect was reversed and resolved to each of those useful cases. The function of the device of the present invention starts to operate when the landing device is advanced and fixed outside the aircraft. The idea of the present invention is to rotate the tire wheel, which is the only movable part of the landing gear, at high speed by utilizing the air velocity of the opposing airflow. Such devices are not found in conventional aircraft. The only outline of the device of the invention is the wind-powered saucer effect so that the tire wheel of the tire wheel and the wheel part are rotated in the forward direction by each device mechanism shown in [Fig. 1, 2, 3, 4]. It is to function. This entire device of the present invention is super-analogue and causes a level of security that is not sensitive to any influence of electronic digital elements. [FIG. 3] 3L of the present invention. In order to improve the convenience of maintenance by making it removable. The aircraft landing device of the present invention, the device devising device of the present invention produces great convenience and benefit for aircraft operation, the invention functional effect application unit and the mechanism device effect application unit benefit all of the present invention range.

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