TWI743218B - System and method for washing and de-icing aircrafts - Google Patents

Abstract

The present discloses a system for washing and de-icing of aircrafts. The preset invention provides a hangar comprising three gantries to ensure different steps of the washing or the de-icing process. The structure of the gantries is essentially made of telescopic arms allowing more flexibility on the positioning of nozzle clusters during the washing and de-icing process. The use of such a mechanical system is easily accommodated to different aircraft bodies regardless their sizes. The whole functionality and positioning of the system is ensured by a programmable system.

Description

System and method for washing and deicing aircraft

The present invention generally relates to systems and methods for washing and deicing aircraft. More specifically, the present invention relates to a system and method for washing and deicing airplanes in enclosed areas.

The surface smoothness of the supporting surface of an airplane is considered to be one of the main factors that define the aerodynamic characteristics of an airplane. The rough surface increases air resistance, which may deteriorate flight performance to a considerable extent and increase fuel consumption. During the flight, the built-in deicing system of the aircraft is sufficient, but in the ground section, the deicing must be performed before starting under adverse weather conditions.

Conventionally, the aircraft's deicing and washing systems are manually operated. Generally, a team of operators perform the steps of spraying deicing fluid. This type of deicing procedure essentially relies on the skill of the operator, good visibility and thorough inspection of the aircraft, which may result in an incomplete deicing procedure before the aircraft takes off. Incorrect deicing caused ice formation on the control surface, resulting in a complete loss or at least a substantial loss of stability and flight control. Also, deicing fluid should not be applied in non-sprayed areas (such as engines, windows, or landing gear). Manual spraying does not guarantee the avoidance of such incidents. At the same time, de-icing automation is intended to prevent dramatic and/or disastrous effects on aircraft flight performance.

Generally speaking, the total cost of manual deicing can be divided into operating costs in the form of staff costs, material costs and other operating costs, and transportation costs for the aircraft being processed.

For certain safety issues during the deicing procedure, the general prior art solution is to keep the operator and the truck further away from the aircraft. Such solutions result in more waste of deicing fluid, which results in higher environmental pollution.

Moreover, the automated deicing system disclosed in the patent US 4,378,755 includes a stationary platform with a stationary frame in an open environment. Such systems are affected by wind, which requires a complex programmed system to place sensors or light beams to detect wind intensity.

The above and other objectives of the present invention are generally achieved by providing a system and method for washing and deicing aircraft in an enclosure and using a controller.

The automated system according to the present invention intends to reduce the total cost compared to the previous method by reducing the cost of employee training to a minimum. The system intends to avoid delays in the airport's traffic program by reducing the de-icing time to one-third of the actual time. It also intends to avoid collisions between flights and trucks, thereby reducing transportation costs.

In another aspect of the present invention, the automated system according to the present invention intends to increase the flexibility of changing the positioning of the deicing and washing system depending on the size and shape of the aircraft, while maintaining a constant amount of used deicing fluid.

In another aspect of the invention, the system includes a closed hangar. Such enclosed hangars are intended to increase the safety of the solution, avoid complex programmed systems, and eliminate or at least substantially reduce wind problems.

In addition to common automated de-icing systems (such as the system previously disclosed in the patent US 4,378,755), the present invention presents a washing system that is intended to improve the flight performance and fuel consumption of the aircraft. This type of washing system efficiently cleans all types of surface deposits, which prevents surface corrosion and improves surface smoothness.

In the first aspect of the present invention, a system for washing and deicing an aircraft is provided. The system includes: a hangar with a base; at least one transverse frame; each transverse frame includes at least one automated vertical elongated member adapted to move vertically, each vertical elongated member connected to a transverse member; spraying means attached to The transverse members are adapted to spray liquid under the transverse members; a controller is configured to control the movement of the elongate members and is configured to control the spraying means; a guide means is configured to be removably Attach to the aircraft, move the aircraft under the transverse frames of the hangar, and transfer the position of the isolator to the controller. The system further includes: at least one storage tank for storing fluid used for washing and deicing, and the storage tank is in fluid communication with the spraying means.

In another aspect of the present invention, the cross member can be automated and can be adapted to extend and collapse laterally, and the controller is further configured to control the extension and collapse of the cross member. The system may further include a first, second, and third lateral frame, the second lateral frame being adapted to move in parallel with the movement of the guiding means.

In a further aspect of the present invention, the vertical elongated members may be telescopic arms, the spraying means may be implemented as at least one nozzle or the spraying means may be implemented as at least one flushing plate.

In another aspect of the present invention, the system may further include a cabin for receiving an operator.

In yet another aspect of the present invention, the controller may be further configured to receive specifications of the aircraft and control the system for the specifications of the aircraft, or the controller may be further configured to receive current environmental conditions And control the system for these current environmental conditions.

In a further aspect of the present invention, the base of the hangar includes guide tracks, and the guiding means is an isolation unit adapted to be guided by the guide tracks, or the base of the hangar may include The spraying means of spraying fluid under the aircraft.

In another aspect of the present invention, the transverse member may include proximity sensors, the proximity sensors are configured to transmit a signal based on the distance between the transverse member and the aircraft, or each transverse member may include A plurality of sections, each section is pivotally connected to each end of the cross member, and each section includes at least one spraying means.

The invention also provides a method for washing and deicing an aircraft. The method includes the following steps: attaching the aircraft to a guiding means; using the guiding means with a hangar to move the aircraft, the hangar including at least one transverse frame; When the transverse frame moves, the vertical extension arms are moved above the aircraft body or wings without touching the aircraft; a first means for spraying a fluid is activated, the spraying means is attached to the transverse member, the The cross member is attached to one end of the extension arms; and the guide means is detached from the aircraft.

In another aspect of the present invention, the method may further include the steps of: transmitting the position of the guiding means to a controller; and using a controller to control the vertical extension arms based on the position received from the guiding means The movement and the activation of the first and second spraying means.

In yet another aspect of the present invention, the method may further include the steps of: transmitting the specifications and environmental conditions of the aircraft to the controller; changing the concentration of the fluid based on the environmental conditions; and based on the aircraft The same specifications use a controller to further control the movement of the vertical extension arms and the activation of the first and second spraying means.

In a further aspect of the invention, the hangar may include two transverse frames. The method then further includes the following steps: when the aircraft moves toward a second transverse frame including second vertical extension arms, moving the second vertical extensions over the aircraft body or wings without touching the aircraft Arm; and a second means for spraying a fluid is activated, the spraying means is attached to a second cross member, the second cross member is attached to one end of the second elongated arms.

In another aspect of the present invention, the method further includes the following steps: when the aircraft moves toward a third lateral frame including a third vertical extension arm, the aircraft body or Move the third vertical extension arms above the wing, the third transverse frame being the center between the other transverse frames; move the third central transverse frame along the length of the aircraft; and inspect the quality of the fluid sprayed on the aircraft .

The features of the present invention considered to be novel are elaborated in the appended claims.

A novel system and method for washing and deicing aircraft will be described below. Although the present invention is described in the form of specific illustrative embodiments, it should be understood that the embodiments described herein are only examples, and the scope of the present invention should not be limited by these embodiments.

The system 200 for washing and deicing generally includes two operation modes, the first mode is to wash the aircraft, and the second mode is to de-ic the aircraft. Indeed, washing and de-icing procedures are used in non-complementary conditions, because de-icing is used in cold temperatures and washing is used in warm conditions.

Figure 1 illustrates a possible but not restrictive external structure of a hangar 100, which provides adequate protection from weather conditions that are not conducive to the washing and/or deicing of the aircraft. In a preferred embodiment, the hangar 100 includes a wind curtain or door to keep the washing and/or deicing process in a closed environment. It is understood that in other embodiments, any other shape suitable for receiving an aircraft may be used for the hangar 100. Also, any material that withstands the weather environment can be used to construct the hangar 100, such as but not limited to tarpaulin, wood, cement, metal, or any other suitable materials.

Referring now to Figures 2 to 4, a preferred embodiment of a system 200 for washing and deicing aircraft is shown. The deicing and washing system 200 includes three transverse frame members or stands 20, 30, and 40. In a preferred embodiment, the second transverse frame member is movable along the length of the aircraft 50. It is understood that a system 200 including three stages 20, 30, and 40 is shown to illustrate the present invention. Those skilled in the art should understand that other embodiments may use only one frame member, two frame members, or more than 3 frame members.

Each frame member generally includes upper parts 21, 31 and 41 supported by two rails 10. In certain embodiments, the base 75 of the hangar 100 includes a longitudinal drain 90 adapted to collect used fluid. The water ditch 90 may be connected to one or more storage tanks or storage tanks 85 to store used fluid. As shown in FIGS. 2 and 4, the base 75 may further include a lower flushing system 80 for washing the aircraft 50. The base is generally made of concrete or any material that supports the weight of the aircraft.

Referring now to FIG. 3, each frame includes one or more telescopic arms 32 that are adapted to move the cross member 34 closer to the aircraft 50 vertically. A cross structural member 33 can be added between two or more telescopic arms 32 to reinforce the assembly, which is intended to increase the stability of the system when moving. The vertical telescopic arm 32 is attached to the frame 31 downward. The cross member 34 is attached to two or more telescopic arms 32 so as to be maintained near the aircraft 50. The lateral moving member 34 is generally implemented as a moving telescopic arm 34. The lateral movement member 34 is generally attached to the telescopic arm 32 using any attachment means 35 (for example, a mechanical bracket 35 as shown on FIGS. 3 and 6).

Still referring to FIG. 3, in an embodiment with three frames 20, 30 and 40, the central frame or stand 30 can be adapted to move between the two outer frames 20 and 40. In other embodiments, one of the frames 20, 30, and 40 may be adapted to support a cockpit 38 adapted to receive an operator. The operator is generally present to control the de-icing and washing procedures and stop the de-icing and washing procedures when there is a problem. It is understood that in other embodiments, the operator may be replaced by a camera and a remote system for controlling and/or stopping the deicing and washing procedures.

Each cross member 34 may include different sections 39. Such sections 39 can be adapted to rotate independently to allow different sections of the rotating arm to adapt to different aircraft bodies, regardless of the size of the aircraft bodies. It is understood that any means known in the art for rotating the different sections 39 can be used.

Referring now to FIG. 7, the flushing plate 22 includes one or more fluid spraying means (such as the nozzle group 37) and an engine 36 for rotating the nozzle group and the flushing plate. Generally speaking, spray means are attached to each cross member 34 to spray liquid toward the aircraft 50 under the cross member 34. In a preferred embodiment, the nozzle group 37 and the engine 36 are adapted to rotate in any direction and quickly sweep the aircraft surface backward and forward as the aircraft 50 moves under the cross member or arm 34. Any means known in the art, such as an actuator coupled to a gear, a hydraulic system, or an electric motor, is used to extend or collapse the telescopic arm 32 and the telescopic cross member 34.

In other embodiments, the cross member 34 implemented as a telescopic arm further includes one or more sections 39, and each area 39 is pivotally connected at each end of the cross member 34. The pivot section 39 includes a spraying means 36 or 37 adapted to spray the main body of the aircraft 50. Any actuator, such as a piston or electric motor, is used to activate the pivot section 39 to move the telescopic arm.

In some embodiments, the deicing system is connected to a controller (eg, a programmable system used to activate a logic controller). The controller can be programmed to control the individual pressure of each nozzle 37 or each nozzle group, and is intended to precisely control the washing procedure based on the distance from the area to be treated.

The control system can also be configured to synchronize the movement of the nozzle group 37 and the telescopic arms 34 and 32. In such an embodiment, the telescopic arms 34 and 32 and the nozzle 37 must be connected to the controller.

In a preferred embodiment, the control system is pre-programmed to synchronize the movement of the telescopic arms 32 and 34 of the frames 20, 30, and 40 with the position of the guide means 60 along the guide track 70. The program that enables synchronization behavior takes into account predetermined parameters. The predetermined parameters may be the dimensions of the aircraft, the wing length and the shape of the aircraft, the outside/inside environmental and atmospheric conditions, or any other related parameters.

The controller can be implemented as any computerized device, any programmable controller, or any type of computer system known in the art.

In a preferred embodiment, the one or more frames 20, 30, and 40 include one or more sensors or motor sensors, such as but not limited to proximity sensors. The sensor may, for example, be configured to send a signal when a part of the aircraft 50 is within a predetermined distance of the sensor. After receiving such a signal, the controller requires repositioning of the cross member 34 or the telescopic arm 32 to avoid touching the aircraft.

Referring back to FIG. 2, the aircraft 50 is shown inside the hangar 100. In a preferred embodiment, the isolation unit 60 is used to guide the aircraft along the road. Such an isolation unit is configured to communicate with the controller to control the movement of the aircraft 50 during the deicing/washing procedure. The isolation unit 60 travels between two guide rails 70 fixed to the base 75 of the hangar 100. The isolation unit 60 is intended to substantially maintain the aircraft within a predetermined path and continuously transmit the position of the aircraft 50 to the controller. Any proximity sensor or any other method used to identify the location of the isolation unit 60 (such as an accurate GPS unit or any other position measurement system) can be used to determine the location of the isolation unit 60. In a preferred embodiment, a mechanical system with cables should be used to determine the location of the isolation unit.

In a preferred embodiment, the fluid stored in the storage tank 85 is recirculated to the common manifold. The manifold is configured to adjust the concentration of the used fluid to weather conditions by adding glycol or heated water. The manifold can communicate with the controller and is adapted to adjust the fluid concentration based on the signal received from the controller. The controller can generate signals based on environmental conditions provided to the controller manually or through sensors. Any sensor (such as an electronic thermometer, barometer, wind speed sensor, etc.) can be used to provide environmental conditions to the controller.

Referring now to Figures 9 to 13, there is shown a method for washing and/or deicing an aircraft. The method generally includes the steps of attaching the aircraft to the isolation unit 60 and transferring the specifications and/or location of the aircraft 50 to the washing and/or deicing system. In another embodiment, after identifying the type and model of the aircraft or after receiving the type and model of the aircraft 50, the specifications of the aircraft may be extracted from a database or data storage that includes most or all of the specifications of the aircraft.

The method further includes the following steps: moving at least the first vertical telescopic arm 32 to a certain height according to the specifications of the aircraft 50, and intends to limit the distance between the spraying means and the main body of the aircraft 50. When the aircraft 50 moves toward the first frame 20, the spraying means 36 and/or 37 of the cross member 34 are activated. The spraying means 80, which generally provide the underflush of the aircraft 50 at the base 75, is generally only turned on during the washing procedure (refer to Figures 9 and 10). As the aircraft 50 moves towards the third frame 30 including the second set of spraying means, the second set of spraying means is activated during the washing procedure (refer to Figure 11-the activation of the spraying means is not shown for clarity).

When the system is used as a de-icing system, in an embodiment with at least three frames, when the aircraft 50 moves toward the second frame 30, it is generally preferred that the operator use the movable frame 30 to move along Move the length of the aircraft over the entire aircraft to perform quality inspections. In other embodiments, a sensor or any means for controlling the surface quality can be used instead of an operator. When the aircraft approaches the third frame 40, the spraying means 36 and/or 37 of the cross member 34 are activated to apply the final treatment, which is a polishing treatment when the system is used as a washing system or a deicing system when the system is used as a deicing system It is anti-icing treatment. When the aircraft 50 moves away from any of the first frame 20, the second frame 20, or the third frame 40, the spraying means of the first, second, and/or third groups are stopped or deactivated, respectively.

This embodiment is shown as having a hangar 100 including three frames 20, 30, and 40. It can be understood that the hangar 100 can be adapted to use one or two frames or more than three frames without departing from the principles of the present invention.

In an embodiment with an operator, for both washing and deicing, once the aircraft approaches the hangar 100 (as shown in FIG. 9), the operator generally uses radio or any other communication means to establish communication with the aircraft. During the communication, the conditions of the program are defined, and the control system is configured to the specifications of the aircraft. The airplane 50 is attached to the isolator 60.

In other embodiments, any type of communication protocol on a network (such as a LAN network, wireless communication, etc.) can be used to automate the communication between the controller and the aircraft.

In the general procedure of washing and/or deicing, the aircraft moves all the way from the frame 20 to the frame 40 for the first time to be washed and cleaned for the first time, and then performs a second time for deicing. It can be understood that other steps can be inserted in the middle of the current steps without departing from the present invention.

Once inside the hangar 100 (as shown in Figure 10), the isolator 60 between the two guide rails uses any type of communication (such as wireless communication or wired communication) to communicate the position of the aircraft to the control system . The control system is configured to control the movement and function of the nozzle group 37 on the frame 20 during the washing process or the deicing process. Generally speaking, the lower flushing system 80 is activated to apply foam to the underside of the aircraft 50 while the aircraft 50 is moving near the first frame 20.

Referring now to Figure 11, aircraft 50 is shown as being washed. During the washing procedure and when the aircraft 50 is moving towards the second frame 30, the lower flushing system 80 under the frame 30 is activated to remove the washing foam on both the upper and lower sides of the aircraft. Use spray means to completely flush the aircraft with hot water. Generally speaking, during the deicing procedure, when the aircraft 50 is moving under the second frame 30, the mobile platform 30 is used by the operator to perform a manual quality check.

Referring now to FIG. 12 and during the washing procedure, once the aircraft reaches the third frame 40, another fluid (such as but not limited to polishing liquid) is applied to the aircraft 50. However, during the de-icing procedure, anti-icing fluid (generally 100% glycol) is applied to the aircraft.

As shown on FIG. 13, once the washing process or the deicing process is completed, the isolator 60 pulls the airplane about 90 degrees before disconnection.

Although the illustrative and currently preferred embodiments of the present invention have been described in detail above, it should be understood that the inventive concept can be implemented and adopted in various different ways, and unless limited by the prior art, the accompanying claims require Is deemed to include such changes.

10‧‧‧rail 20‧‧‧transverse frame member/stand 21‧‧‧upper part 22‧‧‧washing plate 30‧‧‧transverse frame member/stand 31‧‧‧upper 32‧‧‧ telescopic arm 33‧‧ ‧Cross structural member 34‧‧‧Transverse member 35‧‧‧Attachment means/mechanical support 36‧‧‧Engine 37‧‧‧Nozzle group 38‧‧‧Cockpit 39‧‧‧Section 40‧‧‧Transverse frame member/ Platform 41‧‧‧Upper part 50‧‧‧Aircraft 60‧‧‧Guiding means 70‧‧‧Guiding track 75‧‧‧Base 80‧‧‧Spraying means 85‧‧‧Storage tank/tank 90‧‧‧Longitudinal drainage ditch 100‧‧‧Hangar 200‧‧‧System for washing and deicing

The above and other objectives, features and advantages of the present invention will be more easily understood through the following description with reference to the accompanying drawings. In the accompanying drawings:

Figure 1 is a perspective external view of a hangar in accordance with the principles of the present invention.

Fig. 2 is a perspective internal view of the hangar of Fig. 1, showing a deicing and washing system in accordance with the principles of the present invention.

Fig. 3 is a front internal view of the hangar of Fig. 1, showing a deicing and washing system in accordance with the principles of the present invention.

Fig. 4 is a front internal view of the hangar of Fig. 1 showing an under flush system according to the principles of the present invention.

Fig. 5 is a front view of a part of the gantry showing a part of a telescopic arm in accordance with the principles of the present invention.

Figure 6 is a close-up front view of the bottom of the stand, showing the attachment part of the telescopic arm in accordance with the principles of the present invention.

Figure 7 is a close-up front view showing an exemplary system of flushing plates and nozzle groups supported by a horizontal telescopic arm in accordance with the principles of the present invention.

Figure 8 is a side view showing an exemplary system of nozzle groups in accordance with the principles of the present invention.

Fig. 9 is a general perspective internal view of the hangar of Fig. 1, showing the first step of the deicing and washing procedure in accordance with the principles of the present invention.

Fig. 10 is a general perspective internal view of the hangar of Fig. 1, showing the second step of the deicing and washing procedure in accordance with the principles of the present invention.

Fig. 11 is a general perspective internal view of the hangar of Fig. 1, showing the third step of the deicing and washing procedure in accordance with the principles of the present invention.

Fig. 12 is a general perspective internal view of the hangar of Fig. 1, showing the fourth step of the deicing and washing procedure in accordance with the principles of the present invention.

Fig. 13 is a general perspective internal view of the hangar of Fig. 1, showing the fifth step of the deicing and washing procedure in accordance with the principles of the present invention.

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10‧‧‧Orbit

20‧‧‧Transverse frame member/bench

21‧‧‧Upper

30‧‧‧Transverse frame member/bench

31‧‧‧Upper

38‧‧‧Cockpit

40‧‧‧Transverse frame member/bench

41‧‧‧Upper

50‧‧‧Aircraft

60‧‧‧Means of Guidance

70‧‧‧Guide track

75‧‧‧Base

80‧‧‧Spray method

85‧‧‧storage tank/tank

90‧‧‧Longitudinal drainage ditch

200‧‧‧System for washing and deicing

Claims (21)

A system for washing and deicing an aircraft, the system comprising: at least one transverse frame; each of the at least one transverse frame includes at least one automated vertical elongated member adapted to move vertically, the at least one Each of the vertically elongated members is connected to a transverse member; spraying means is attached to the transverse members and is adapted to spray liquid under the transverse members; a controller is configured to control the elongated members The movement of the component is configured to control the spraying means; a guide means is configured to: removably attach to the aircraft; move the aircraft under the transverse frames; and transmit the guide means to the controller Location; at least one storage tank for storing fluid used for washing and deicing, the storage tank is in fluid communication with the spraying means. In the system for washing and deicing an aircraft as described in claim 1, the transverse member is automated and adapted to extend and collapse transversely, and the controller is further configured to control the extension and collapse of the transverse member Shrink. The system for washing and deicing an aircraft as described in claim 2, the system further comprising a first, second and third horizontal frame, The second lateral frame is adapted to move in parallel with the movement of the guiding means. In the system for washing and deicing an aircraft as described in any one of claims 1 to 3, the vertical elongated members are telescopic arms. In the system for washing and deicing an aircraft as described in claim 1, the spraying means is at least one nozzle. In the system for washing and deicing an aircraft as described in claim 1, the spraying means is at least one washing plate. For the system for washing and deicing an aircraft as described in claim 1, the controller is further configured to receive specifications of the aircraft and control the system for the specifications of the aircraft. In the system for washing and deicing an aircraft as described in claim 1, the controller is further configured to receive current environmental conditions and control the system according to the current environmental conditions. The system for washing and deicing an aircraft as described in claim 1, the system further includes guide tracks, and the guide means is adapted to be an isolation unit guided by the guide tracks. The system for washing and deicing an aircraft as described in claim 1, the system further includes a hangar having a base. In the system for washing and deicing an aircraft as described in claim 1, each cross member includes a plurality of sections, at least one section is pivotally connected to each end of the cross member, and each section includes at least one Spraying means. A method for washing and deicing an aircraft. The method includes the following steps: moving the aircraft under at least one lateral frame; In the case of the aircraft, the vertical extension arms are moved above the aircraft body or wings; a first spraying means for spraying a fluid is activated, the first spraying means is attached to the cross member, and the cross member is attached to the Wait for one end of the extension arm. The method for washing and deicing an aircraft as described in claim 12, the method further includes the steps of: transmitting the position of the guidance means to a controller; and using the guidance means based on the position received from the guidance means The controller controls the movement of the vertical extension arms and the activation of the first spraying means. As described in claim 12, the method for washing and deicing an aircraft further includes the following steps: determining the geographic coordinates of the aircraft; transmitting the geographic coordinates to a controller; and based on the received from the guidance means The geographic location uses the controller to control the movement of the vertical extension arms and the activation of the first spraying means. According to the method for washing and deicing an aircraft according to any one of claims 12 to 14, the method further includes the following steps: transmitting specifications and environmental conditions of the aircraft to the controller; Based on the specifications of the aircraft, the controller is used to further control the movement of the vertical extension arms and the activation of the first spraying means. The method for washing and deicing an aircraft as described in claim 13, the method further includes the following steps: when the aircraft is moving toward a second transverse frame including a second vertical extension arm, without touching the aircraft In the case of an aircraft, move the second vertical extension arms above the aircraft body or wing; and activate a second spraying means for spraying a fluid, the second spraying means being attached to the second cross member, the second The cross member is attached to one end of the second extension arms. The method for washing and deicing an aircraft as described in claim 12, the method further includes the following steps: attaching the aircraft to a guiding means; using the guiding means to move the aircraft; detaching the aircraft from the aircraft Guiding means. A system for washing and deicing an aircraft, the system comprising: at least one transverse frame, each of the at least one transverse frame includes at least one automated vertical elongated member adapted to move vertically, the at least one Each of the automated vertical extension members is connected to a cross member; a spraying system attached to the at least one cross member, the spraying system being adapted to spread liquid under the cross member; An aircraft pulling system adapted to move the aircraft in a predetermined path under the at least one transverse frame, the aircraft pulling system including an attachment member adapted to be removably Attached to the aircraft; a controller including a memory to store the shape and scale information of the aircraft; a position measuring system configured to: identify the position of the aircraft on the predetermined path of the aircraft; and The controller transmits the identified position; at least one storage tank for storing fluid for washing and deicing, the storage tank is in fluid communication with the spraying system; and the controller communicates with the position measuring system, and the controller is Programmed to control the movement of the at least one automated vertical elongated member and control the activation of the spraying system, wherein the controller uses the position transmitted by the aircraft and the shape and dimension information of the aircraft to continuously synchronize the automated The movement of the vertical elongated member conforms to the shape and dimensions of the aircraft and automatically activates the spraying system after positioning the automated vertical elongated member. As described in claim 18, the system for washing and deicing an aircraft, the position measuring system is further configured to identify the aircraft at any position on the predetermined path of the aircraft relative to the at least one transverse frame distance. The system for washing and deicing an aircraft as described in claim 18 or 19, wherein the position measuring system includes a position sensor. The system for washing and deicing an aircraft according to any one of claims 18 to 20, the system further comprising a hangar with a base.

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