CN112357111A - Ground intervention device for accelerating aircraft wake dissipation - Google Patents
Ground intervention device for accelerating aircraft wake dissipation Download PDFInfo
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Abstract
The invention discloses a ground intervention device for accelerating the dissipation of aircraft wake flow, which comprises a plate line system which is arranged in parallel, wherein the comparison between a plateless system and a vortex quantity vector diagram under the action of the plate line system shows that under the action of the plate line, obvious secondary vortex flow is generated, the turbulent kinetic energy of the wake vortex is interfered and inhibited due to the fact that the tangential air flow of the wake vortex is blocked and divided, meanwhile, the lower washing air flow of the wake vortex is blocked between the plate line and the ground, the size and the direction of the air flow velocity are changed, the main vortex of the wake vortex is deformed, the secondary vortex flow is induced and separated, the interference and dragging action is generated on the main vortex, the intensity attenuation and the dissipation of the vortex are intensified, the plate line system can accelerate the dissipation speed of the wake vortex, the influence of the wake flow on a rear aircraft is reduced, the wake flow interval is reduced, the airport capacity and the airspace use efficiency are improved, and the increasing air transportation.
Description
Technical Field
The invention relates to the technical field of aircraft ground devices, in particular to a ground intervention device for accelerating aircraft wake dissipation.
Background
Wake is a long-lasting rotating airflow generated by each aircraft. They are formed by "rolling" on the wing tip as air moves from a high pressure area below the wing to an upper low pressure area. These powerful vortices can have a severe impact on the aircraft following them and can also cause damage to the ground structure. When the aircraft generates lift, the pressure difference between the upper and lower airfoils causes airflow from the lower airfoil to flow around the tip to the upper airfoil, thereby creating a pair of counter-rotating vortices at the tip, commonly referred to as wake vortices, the entire process of which is known as wake flow. The wake flow poses a threat to the safety of aircraft following the aircraft generating the wake vortexes.
According to actual operation experience and consideration on operation safety, the International Civil Aviation Organization (ICAO) sets a relatively conservative wake interval standard, and increases the operation safety of flight at the expense of airspace capacity. However, with the continuous development of civil aviation transportation industry in China, the demand for air traffic capacity is also sharply increased, the increase of airport capacity is limited to a certain extent by a relatively conservative wake space standard, the use efficiency of airspace is seriously influenced, and local airspace congestion is caused. Meanwhile, if a new runway is constructed in an existing airport, residential areas are often affected by extension. Under the limit of the safety of the airplane and the capacity of the airport, how to accelerate the dissipation speed of the wake vortex on the ground becomes an urgent problem to be solved.
Disclosure of Invention
The invention aims to: aiming at the problem of how to accelerate the dissipation speed of wake vortexes on the ground in the prior art, a ground intervention device for accelerating the dissipation of the aircraft wake flow is provided; local face intervention device is including parallel arrangement's plate line system, and this plate line system weakens the torrent kinetic energy of wake vortex through blocking, bounce-back wake vortex, destroys the wake vortex structure, and induced main vortex separates out the secondary vortex system to reach the effect of accelerating the aircraft wake dissipation, can accelerate wake vortex dissipation speed, reduce the influence of wake to the back aircraft, thereby reduce the wake interval, improve airport capacity and airspace availability factor, satisfy ever-increasing air transportation demand.
In order to achieve the purpose, the invention adopts the technical scheme that:
a ground intervention device for accelerating the dissipation of aircraft wake flow comprises a plate line system arranged on the ground behind a runway entrance extension line;
the plate line system comprises a plurality of parallel plates 1 arranged at intervals along the width direction of the runway, and the parallel plates are arranged along the length direction of the runway.
The wake dissipation ground intervention device provided by the invention comprises a plate line system arranged on the ground behind a runway entrance extension line; the plate line system comprises a plurality of parallel plates arranged at intervals along the width direction of the runway, and the parallel plates are arranged along the length direction of the runway; it can be known through the comparison of vortex volume vector diagram under no plateline system and this plateline system effect, under the effect of plateline, obvious secondary vortex has been produced, because the tangential air current of wake vortex receives and blocks, cut apart, disturb and the torrent kinetic energy of having restrained the wake vortex, the lower washing air current of wake vortex is detained between plateline and ground simultaneously, the size and the direction of air velocity change, the main vortex of wake vortex is out of shape, the induced secondary vortex that separates, produce the interference drag effect to main vortex, intensify the intensity decay and the dissipation of vortex, this plateline system can accelerate wake vortex dissipation speed, reduce the influence of wake to the after-machine, thereby reduce the wake interval, improve airport capacity and airspace availability factor, satisfy ever-increasing air transportation demand.
Preferably, in the above ground intervention device for accelerating the dissipation of the aircraft wake, the parallel plates comprise a plurality of plate units, and the plate units are detachably connected.
The parallel plate provided by the invention is formed by splicing a plurality of plate units, and the parallel plate is formed by the basic plate units, so that the arbitrary combination and splicing of the basic plate units can be realized, and the parallel plate has the advantages of convenience in loading and unloading and easiness in adjusting the size of the parallel plate.
Preferably, in the ground intervention device for accelerating the aircraft wake dissipation, the distance between adjacent parallel plates is the same.
Preferably, the number of the parallel plates is 11, and the distance between the adjacent parallel plates is 10 m.
Or the number of the parallel plates is 22, and the distance between every two adjacent parallel plates is 5 m.
The parallel plates provided by the invention are uniformly arranged at intervals, and the total width of the parallel plate lines is set to be about 100m based on the comprehensive consideration of the spread range of the wingspan of the current heavy-duty machine and the wake vortex when reaching the plate lines and the occupation of the runway width, so that the full dissipation of the wake vortex can be ensured in the range without occupying too much runway; and meanwhile, two arrangement modes of the parallel plate lines are provided, and the wake vortex dissipation effect of the parallel plate line system is more obvious in the encryption arrangement mode.
Preferably, in the above ground intervention device for accelerating aircraft wake dissipation, the plate line system further includes: a plane plate disposed on top of each of the parallel plates, the plane plate being disposed in a horizontal direction.
Preferably, in the ground intervention device for accelerating the dissipation of the aircraft wake, the plane plate is perpendicular to the parallel plates.
Preferably, in the above ground intervention device for accelerating aircraft wake dissipation, the plate line system further includes: a vertical plate; the vertical plate is arranged between the adjacent parallel plates, and two ends of the vertical plate are respectively connected with the adjacent parallel plates.
In a further embodiment of the invention, a plate line system is improved into a composite plate line structure comprising a parallel plate, a plane plate and a vertical plate through comprehensive kinematic analysis of the x direction, the y direction and the z direction of the wake vortex, because a top plate line is added, when the wake vortex contacts a top plate, part of the vortex is retarded, shunting and rebounding occur, and a secondary vortex system is induced to be formed, meanwhile, the plate line parallel to and vertical to the central line of a runway retards and intervenes the motion of the wake vortex, and the primary vortex structure is induced to be unstable, the vortex body is deformed and twisted, and the secondary vortex is separated, so that the effect of the composite plate line on accelerating the dissipation of the wake vortex is more obvious.
Preferably, in the above ground intervention device for accelerating the dissipation of the aircraft wake, the dimensions of the parallel plates are: 7 m.times.10.5 m.times.0.01 m.
Preferably, in the ground intervention device for accelerating the dissipation of the aircraft wake flow, the plate line system is connected with the ground through a steel wire rope.
The steel wire rope is used for fixing the plate line system on the ground, so that the stability of the plate line system is better facilitated.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the wake dissipation ground intervention device provided by the invention comprises a plate line system arranged on the ground behind a runway entrance extension line; the plate line system comprises a plurality of parallel plates arranged at intervals along the width direction of the runway, and the parallel plates are arranged along the length direction of the runway; it can be known through the comparison of vortex volume vector diagram under no plateline system and this plateline system effect, under the effect of plateline, obvious secondary vortex has been produced, because the tangential air current of wake vortex receives and blocks, cut apart, disturb and the torrent kinetic energy of having restrained the wake vortex, the lower washing air current of wake vortex is detained between plateline and ground simultaneously, the size and the direction of air velocity change, the main vortex of wake vortex is out of shape, the induced secondary vortex that separates, produce the interference drag effect to main vortex, intensify the intensity decay and the dissipation of vortex, this plateline system can accelerate wake vortex dissipation speed, reduce the influence of wake to the after-machine, thereby reduce the wake interval, improve airport capacity and airspace availability factor, satisfy ever-increasing air transportation demand.
2. The parallel plates provided by the invention are uniformly arranged at intervals, and the total width of the parallel plate lines is set to be about 100m based on the comprehensive consideration of the spread range of the wingspan of the current heavy-duty machine and the wake vortex when reaching the plate lines and the occupation of the runway width, so that the full dissipation of the wake vortex can be ensured in the range without occupying too much runway; and meanwhile, two arrangement modes of the parallel plate lines are provided, and the wake vortex dissipation effect of the parallel plate line system is more obvious in the encryption arrangement mode.
3. In a further embodiment of the invention, a plate line system is improved into a composite plate line structure comprising a parallel plate, a plane plate and a vertical plate through comprehensive kinematic analysis of the x direction, the y direction and the z direction of the wake vortex, because the top plane plate line is added, when the wake vortex contacts a top plate, part of the vortex is retarded, shunting and rebounding occur, and a secondary vortex system is induced to be formed, meanwhile, the plate line which is parallel to and vertical to the central line of a runway retards and intervenes the motion of the wake vortex, the primary vortex structure is induced to be unstable, the vortex body is deformed and twisted, and the secondary vortex is separated, so the effect of the composite plate line on accelerating the dissipation of the wake vortex is more obvious.
Drawings
Fig. 1 is a schematic view 1 of a parallel plate line (with a pitch of 10m) structure according to an exemplary embodiment of the present invention.
Fig. 2 is a schematic diagram 2 of a parallel plate line (with a pitch of 5m) structure according to an exemplary embodiment of the present invention.
Fig. 3 is a schematic diagram of a composite plate line structure in accordance with an exemplary embodiment of the present invention.
FIG. 4 is a vector diagram of wake vortex momentum under plateless line action in accordance with an exemplary embodiment of the present invention.
Fig. 5 is a vector diagram of the amount of wake vortexes under the action of parallel plate lines (with a pitch of 10m) according to an exemplary embodiment of the present invention.
Fig. 6 is a vector diagram of the amount of wake vortexes under the action of parallel plate lines (with a pitch of 5m) according to an exemplary embodiment of the present invention.
FIG. 7 is a vector diagram of the amount of wake vortices under the action of the composite plate-line system in accordance with an exemplary embodiment of the present invention.
FIG. 8 is a z-direction velocity vector diagram of wake vortexes under a plateless line effect in accordance with an exemplary embodiment of the present invention.
FIG. 9 is a vector diagram of the z-direction velocity of wake vortexes with parallel plate lines (10 m pitch) in accordance with an exemplary embodiment of the present invention.
FIG. 10 is a vector diagram of the z-direction velocity of wake vortexes with parallel plate lines (5 m apart) in accordance with an exemplary embodiment of the present invention.
FIG. 11 is a z-direction velocity vector diagram of wake vortexes under the influence of a composite plate line system in accordance with an exemplary embodiment of the present invention.
FIG. 12 is a trailing vortex y-direction velocity vector diagram under plateless line action in accordance with an exemplary embodiment of the present invention.
FIG. 13 is a vector diagram of the y-direction velocity of wake vortices with parallel plate lines (10 m pitch) in accordance with an exemplary embodiment of the present invention.
FIG. 14 is a vector diagram of the y-direction velocity of wake vortices with parallel plate lines (5 m pitch) in accordance with an exemplary embodiment of the present invention.
FIG. 15 is a vector diagram of the y-direction velocity of wake vortices under the action of the compound plate line system in accordance with an exemplary embodiment of the present invention.
Reference numerals: 1-parallel plate; 2-a flat plate; 3-vertical plate.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Examples
As shown in figures 1-3, a plate line system is placed at a preset distance of 100m behind the extended line of the center of the runway entrance to perform wake vortex intervention. Considering that parameters such as wingspan and weight of various aircrafts are different in types of airport runways, parameters such as ring volume and vortex core spacing of generated wake vortexes are also different, in order to achieve the best effect of accelerating wake flow dissipation, the configuration and the position of a plate line need to be optimized and adjusted, and specifically, the plate line system comprises: the plate line system is a flat plate line system consisting of a series of parallel plates 1 with the same interval, or a composite plate line system consisting of a plane plate 2 and a vertical plate 3 which are additionally arranged on the parallel plates 1, and the whole plate line system is fixed on the ground by a steel wire rope. Wherein, the plate line system is additionally arranged behind the airport runway entrance to meet the related obstacle evaluation, and the OIS (object Identification surface) obstacle Identification surface is a group of inclined surfaces which are established around the airport and used for identifying the obstacles, and the gradient of the inclined surfaces is 2.5%. When an obstacle penetrates through the OIS surface, a flight course is required to be defined in an off-field procedure so as to safely avoid the obstacle; the starting point of OIS is 5m to the entrance, the gradient is 2.5%, so the plate line height 100m behind the runway is limited to 5+100 × 2.5% to 7.5m, and therefore the height of the parallel plate 1 should not exceed 7.5m, in this embodiment the height of the parallel plate 1 is designed to be 7 m.
Specifically, in order to meet the requirements for the dimension of the plate line and facilitate the assembly and disassembly, a proper basic metal plate is designed to splice to obtain the required parallel plates 1 so as to form the whole plate line system. The basic metal plate unit dimensions of the parallel plate 1 are: 3.5m 0.01m, small holes are reserved on the basic metal blocks, the metal connecting sheets are connected together through metal sheets and rivets to form a whole parallel plate, and six metal plates are spliced into a parallel plate of 7m 10.5m 0.01m (7m is the height of the parallel plate 1 from the ground, 10.5m is the transverse extension length of the parallel plate 1 along the extension line of the runway, and 0.01m is the thickness of the parallel plate 1), so that the plate line system is obtained. The interval between the adjacent parallel plates 1 is uniform, and the total width of the parallel plate lines is set to be about 100m based on the comprehensive consideration of the spread range of the wingspan of the current heavy-duty machine and the wake vortex when reaching the plate lines and the occupation of the runway width, so that the full dissipation of the wake vortex can be ensured in the range, and the excessive runway does not need to be occupied; meanwhile, two arrangements of the parallel plate lines shown in fig. 1 and fig. 2 are provided, and the wake vortex dissipation effect of the parallel plate line system is more obvious in the encryption arrangement of fig. 2. As shown in FIG. 1, 11 parallel plates 1 were placed 100m after the extended line from the center of the runway entrance, and the distance between the base parallel plates 1 was 10 m. As shown in FIG. 2, the plate line pitch was adjusted, the encryption process was performed, 22 parallel plates 1 were used, and the parallel plate 1 pitch was reduced to 5 meters. Further, as shown in fig. 3, a plane plate 2 of 0.01m × 10.5m × 5m is additionally arranged on the top of the parallel plate 1 with the distance of 10m, the thickness is 0.01m, and a vertical plate 3 is additionally arranged between two adjacent parallel plates 1, and the size of the vertical plate is as follows: 0.01m 5m 10.5m, thickness 0.01m, form the compound plate line structure, intervene the wake vortex from three different directions.
In a further embodiment of the present invention, the plate-line structures of FIGS. 1-3 are specifically described and their enhanced wake vortex dissipation effects are analyzed. The research on the evolution process and the law of the wake vortex generally analyzes parameters of the wake vortex, such as wake vortex amount, tangential speed, vortex core spacing, vortex core size, sinking speed and the like, and the comparison analysis is carried out on the vortex amount and the tangential speed under the actions of a spacing 10m plate line, a spacing 5m plate line and a composite plate line by using a plate-free line.
The vorticity is an important parameter for representing the strength of wake vortex, and the physical meaning of the vorticity is the vorticity of a fluid velocity vector. The rotation is a vector operator in vector analysis and can represent the rotation degree of a three-dimensional vector field to a infinitesimal element near a certain point. The vorticity vector form in the three-dimensional flow field can be expressed as follows:
wherein, ω isx、ωy、ωzRespectively representing the components of vorticity in the x, y, and z directions.
By analyzing the change of the vorticity, the evolution condition of the wake vortex after being influenced by the plate line can be revealed. In a plane flow field, the vorticity only has a component in one direction, and the component of the vorticity in the y direction is selected to analyze the vorticity change.
The vector diagrams of wake vortex amount under the calculated plate-free line action and the action of the pitch 10m plate line, the pitch 5m plate line and the composite plate line are shown in fig. 4, 5, 6 and 7, the vector diagrams of velocity in the Y direction are shown in fig. 8, 9, 10 and 11, and the vector diagrams of velocity in the Z direction are shown in fig. 12, 13, 14 and 15.
As shown in fig. 4, the maximum x-direction vorticity under the action of no plate line is 3.96, as shown in fig. 5, the maximum x-direction vorticity under the action of the parallel plate lines with the interval of 10m is 3.76, and the maximum vorticity is reduced by 5.05% in proportion, as can be seen from the comparison of the two vorticity vector diagrams, under the action of the plate lines, an obvious secondary vortex is generated, because the tangential airflow of the wake vortex is blocked and divided, the turbulent kinetic energy of the wake vortex is disturbed and inhibited, meanwhile, the lower washing airflow of the wake vortex is blocked between the plate lines and the ground, the size and the direction of the airflow speed are changed, the main vortex of the wake vortex is deformed, the secondary vortex is induced and separated, the interference drag action is generated on the main vortex, and the intensity attenuation and dissipation of the.
As shown in fig. 6, the maximum eddy amount in the x direction under the action of the parallel plate lines with the interval of 5m is 3.11, and compared with the case without the plate lines, the maximum eddy amount is reduced by 21.46% in the same ratio, and when comparing fig. 6 with fig. 4 and 5, it can be seen that because the plate lines are more dense, the airflow in the lower washing area is blocked by the plate lines more dispersedly, the intervention action is continuous, and the secondary eddy surrounds the main eddy due to the induction action.
As shown in fig. 7, the maximum vorticity in the x direction under the action of the composite plate line is 2.21, compared with the situation without the plate line, the maximum vorticity is reduced by 44.19% in the same ratio, and compared with fig. 7, fig. 4, fig. 5 and fig. 6, the wake vortex dissipation action under the action of the composite plate line is more obvious, because of the addition of the top plate line, when the wake vortex contacts the top plate, part of the vortex is retarded, the vortex is shunted and rebounded, and a secondary vortex system is induced to be formed, meanwhile, the plate line parallel and perpendicular to the central line of the runway retards and intervenes the movement of the wake vortex, so that the structure of the main vortex is induced to be unstable, the body is deformed and distorted, the secondary vortex is separated, the Rayleigh-ludwig crossing instability is triggered, and the secondary vortex rotates.
According to the vorticity comparison under different conditions in the four cases, the plate line system can effectively accelerate the dissipation of the aircraft wake flow, the main vortex of the wake vortex is subjected to a retarding separation effect when encountering each plate line in the plate line system, the structure is damaged, secondary vortices with different sizes and forms are formed, the secondary vortices move around the main vortex to trigger Rayleigh-Ludwieg intersection instability and interfere with the main vortex, so that the main vortex structure is unstable, and the dissipation is accelerated.
The wake intensity, also known as the wake vortex volume, is the integral of the fluid velocity on any closed curve in the wake flow field. In order to better study the wake flow intensity dissipation mechanism, parameters such as wake vortex induction speed, vortex core radius, descent speed and the like are often selected for characterization. From Kutta-Joukows, it is known that when the aircraft speed is V, the span is B and the aspect ratio is ARAt time, aircraft lift is equal to vorticity flux. The following can be obtained:
b0＝s*B (2)
in the formula: gamma-shaped0The initial ring volume of the aircraft wake vortex; b0Is the initial vortex spacing; clIs the aircraft lift coefficient; s is a load factor in the spanwise direction, and s is approximately equal to pi/4 when the airfoil is an elliptical wing; ρ is the air density of the atmosphere in which the aircraft is located. Therefore, the initial wake vortex ring amount can be expressed by the following formula
When the plane is under balanced force, the vertical momentum of the tail vortex of the plane is also equal to the gravity borne by the plane, and the initial circulating volume of the tail vortex can also be expressed as
Wherein M is the aircraft mass; g is the local gravitational acceleration.
The ring volume of a single wake vortex can be defined as a function of the tangential velocity and the radial distance from the center of the vortex core. The specific function is as follows:
Γ＝2πrV(r) (6)
therefore, by analyzing the tangential velocities of different flow field sections, the influence of the plate line on the wake vortex can be reflected, and the velocities in the z direction and the y direction are selected for comparison.
Fig. 6, 9, 12 and 15 are velocity vector diagrams in the Z direction under no plate line action, a parallel plate line with a pitch of 10m, a parallel plate line with a pitch of 5m and a composite plate line action.
As shown in FIG. 8, the maximum value of the velocity vector in the z direction under no plate line was 2.15m/s, and as shown in FIG. 9, the maximum value of the velocity vector in the z direction under the plate line of 10m pitch was 2.11m/s, which is a 1.86% decrease on the same scale.
As shown in FIG. 10, the maximum value of the velocity vector in the z direction by the plate line with a spacing of 5m was 2.02m/s, which was reduced by 6.05% as compared with that without the plate line.
As shown in FIG. 11, the maximum value of the velocity vector in the z direction under the action of the composite plate line was 2.00m/s, which was decreased by 6.98% as compared with the case where no plate line was applied.
Fig. 12, 13, 14 and 15 are velocity vector diagrams in the y direction for the plateless action, the 10m pitch plate line, the 5m pitch plate line and the composite plate line.
As shown in FIG. 12, the maximum value of the velocity vector in the y direction under no plate line was 2.26m/s, and as shown in FIG. 13, the maximum value of the velocity vector in the y direction under the plate line of a pitch of 10m was 2.23m/s, which is a 1.33% decrease in terms of the ratio. Comparing fig. 13 with fig. 12, it can be seen that under the action of the plate line, the rebound effect of the wake vortex is more obvious, the wake vortex airflow is affected by the plate line and the ground, and the main vortex is lifted to accelerate dissipation.
As shown in FIG. 14, the maximum value of the velocity vector in the y direction by the plate line with a pitch of 5m was 2.17m/s, which was reduced by 3.98% as compared with that by the plate line without. As can be seen from comparison of fig. 14 with fig. 12 and 13, the plate line pitch is reduced, and more secondary eddy currents are generated near the plate line, thereby accelerating wake vortex dissipation.
As shown in fig. 15, the maximum value of the velocity vector in the y direction under the action of the composite plate line was 1.73m/s, which was decreased by 23.45% as compared with the case without the plate line. As can be seen from comparison of fig. 15 with fig. 12, 13, and 14, the wake vortex motion retardation in the y direction is more pronounced due to the addition of the corresponding vertical plate lines between the plate lines.
In conclusion, the wake vortex interference device provided by the exemplary embodiment of the invention can play an excellent role in wake vortex interference, rebounds on the plate line to form a reverse vortex, and interacts with the original wake vortex to weaken the turbulent kinetic energy of the main vortex. Meanwhile, the sinking motion of the wake vortex is influenced by multiple intervention of the plate line and the ground, the downwash airflow is blocked, the wake vortex cannot sink continuously, the generated secondary vortex generates a lifting effect on the main vortex, and the original speed field of the main vortex of the wake vortex is damaged under the action of the rebounded secondary vortex and the near-earth cyclone, so that the intensity attenuation of the wake vortex is accelerated.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. A ground intervention device for accelerating the dissipation of aircraft wakes, characterized by comprising a plate line system arranged on the ground behind the extension line of a runway entrance;
the plate line system comprises a plurality of parallel plates (1) arranged at intervals along the width direction of the runway, and the parallel plates (1) are arranged along the length direction of the runway.
2. Ground intervention device to accelerate the dissipation of aircraft wakes according to claim 1, wherein the parallel plates (1) comprise several plate units, which are detachably connected.
3. Ground intervention device to accelerate the dissipation of aircraft wakes according to claim 2, characterized in that the spacing between adjacent parallel plates (1) is the same.
4. The ground intervention device for accelerating the dissipation of aircraft wakes according to claim 3, wherein the number of the parallel plates (1) is 11, and the distance between adjacent parallel plates (1) is 10 m;
or the number of the parallel plates (1) is 22, and the distance between every two adjacent parallel plates (1) is 5 m.
5. A ground intervention device to accelerate aircraft wake dissipation according to claim 3, wherein the trigger system further comprises: a plane plate (2) arranged on top of each parallel plate (1), the plane plate (2) being arranged in a horizontal direction.
6. A ground intervention device to accelerate the dissipation of aircraft wakes according to claim 5, wherein the plane plate (2) is arranged perpendicular to the parallel plate (1).
7. The ground intervention device of claim 6, wherein the trigger system further comprises: a vertical plate (3); the vertical plate (3) is arranged between the adjacent parallel plates (1), and two ends of the vertical plate (3) are respectively connected with the adjacent parallel plates (1).
8. Ground intervention device to accelerate the dissipation of aircraft wakes according to any of claims 1-7, characterized in that the parallel plates (1) are dimensioned: 7 m.times.10.5 m.times.0.01 m.
9. A ground intervention device to accelerate dissipation of aircraft wakes according to any of claims 1-7, wherein the plate line system is fixedly connected to the ground by means of a steel cable.
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