An adsorption-type aircraft static pressure hole protection device

Abstract

An adsorption-type aircraft static pressure hole protection device includes a shielding component and a lifting component. The shielding component includes a baffle plate with a static pressure hole plug on its back and suction cups at its four corners. The front of the baffle plate has a mounting base and an adsorption control component. The adsorption control component includes a first directional slide rod and a second directional slide rod, a first sliding sleeve slidably fitted on the first directional slide rod, a second sliding sleeve slidably fitted on the second directional slide rod, a push plate connected to the first and second sliding sleeves, a drive rod located in the middle of the push plate, a return spring connected to the push plate and the mounting base, and a linkage rod connected to the first and second sliding sleeves respectively. The other end of the linkage rod is connected to an adsorption control handle on the suction cups. This device raises the shielding component using the lifting component and adsorbs it onto the aircraft surface using the suction cups, causing the static pressure hole plug to block the static pressure holes on the aircraft, ensuring that the static pressure holes are not blocked during cleaning and preventing scratches on the smooth surfaces around the static pressure holes.

Description

Technical Field

[0001] This invention relates to the field of aircraft ground maintenance equipment, and more particularly to an adsorption-type aircraft static pressure hole protection device. Background Technology

[0002] To keep aircraft surfaces clean, airlines regularly perform surface cleaning. Aircraft pressure vents are critical components of the aircraft system, located on the fuselage surface. To maintain the cleanliness of the pressure vent area and prevent clogging by foreign objects, the pressure vent area needs to be shielded and protected during aircraft washing. Existing protective devices for aircraft pressure vents consist of a plastic sheet secured to the pressure vent area with tape. This method of using a plastic sheet to shield the pressure vents has the following drawbacks:

[0003] 1) Because tape is used for fixing, the tape can only be used once, which wastes resources;

[0004] 2) The use of tape leaves adhesive residue;

[0005] 3) Using tape for assembly and disassembly is not quick or convenient;

[0006] 4) Because the static pressure hole area is located in the middle of the fuselage and is at a high position, it requires a push ladder for installation, which seriously affects the efficiency of aircraft surface cleaning work. Summary of the Invention

[0007] The purpose of this invention is to provide an adsorption-type aircraft static pressure hole protection device to overcome the shortcomings and deficiencies of the prior art.

[0008] To achieve the above objectives, this case utilizes the following technical solution:

[0009] An adsorption-type aircraft barometric pressure port protection device includes a shielding assembly and a detachable lifting assembly docked to the shielding assembly, further comprising:

[0010] The shielding assembly includes a baffle plate with a static pressure hole plug matching the static pressure hole of the aircraft located at the center of its back side, and suction cups located at the four corners of the baffle plate; a mounting base is located at the center of the front side of the baffle plate, with symmetrical docking holes on both side walls of the mounting base, and a suction control hole is formed through the top of the mounting base; a suction control assembly is also located on the baffle plate at the periphery of the mounting base.

[0011] The adsorption control assembly includes a first directional slide rod and a second directional slide rod fixedly mounted parallel to the baffle plate, a first sliding sleeve slidably mounted on the first directional slide rod, a second sliding sleeve slidably mounted on the second directional slide rod, a push plate fixedly connected laterally to the first and second sliding sleeves, a drive rod fixedly mounted in the middle of the push plate and extending through the adsorption control hole into the mounting base, a reset spring with its two ends connected to the push plate and the mounting base respectively, and four linkage rods connected to the two ends of the first and second sliding sleeves respectively. The other ends of the four linkage rods are respectively connected to the adsorption control handles on the four suction cups.

[0012] Furthermore, the lifting assembly includes a pair of connectors and a connecting rod integrally connected to the bottom of the connectors; a straight through groove is vertically opened in the center of the front of the connectors, and a pair of spring pins are symmetrically arranged laterally inside the connectors, each spring pin passing through the side wall of the straight through groove laterally, and the pair of spring pins correspond to a pair of docking holes on the side wall of the mounting base; the connecting rod is a hollow tube, and the cavity of the connecting rod communicates with the straight through groove on the connector to form an assembly slide, in which a lifting assembly is slidably installed.

[0013] Furthermore, the lifting assembly includes a lifting slide rod and a lifting slider connected as one piece; the lifting slide rod is installed inside the cavity of the docking rod, and the lifting slider is installed inside the straight groove of the docking joint.

[0014] Furthermore, the lifting slider has a conical head at one end facing the adsorption control rod, and three position slots are arranged sequentially at intervals on the side of the lifting slider. The first position slot is located at the upper end of the slope of the conical head, the second position slot is located at the lower end of the slope of the conical head, and the third position slot is located on the flat side of the lifting slider. The three position slots respectively cooperate with the spring pin.

[0015] Preferably, a control push button is fixedly provided at the bottom end of the lifting slide rod, and the control push button extends laterally to the outside of the side wall of the docking rod.

[0016] Preferably, the baffle plate is also provided with a number of weight-reducing holes.

[0017] Preferably, the mounting base is U-shaped with the opening expanding outwards.

[0018] Preferably, the baffle is made of plastic and the static pressure hole plug is made of waterproof sponge.

[0019] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0020] 1) The adsorption-type aircraft static pressure hole protection device in this case raises the shielding component by lifting the lifting component and adsorbs it onto the surface of the aircraft with a suction cup, so that the static pressure hole plug blocks the static pressure hole on the aircraft, ensuring that the static pressure hole is not blocked during the aircraft cleaning process, and also ensuring that the smooth surface around the static pressure hole is not scratched.

[0021] 2) The lifting assembly is equipped with a lifting component. The lifting slider in the lifting component has three positions that cooperate with the spring pin. Each of the three positions has three control functions, which allows the operator to control the shielding component at a higher position from the ground through the docking rod in the lifting assembly. This enables the installation base and connector to be docked and locked, the suction cup to be attached to the aircraft surface, the docking base and connector to be unlocked, and the suction cup to be unlocked from the aircraft surface. The operation is simple and convenient, ensuring that the static pressure hole is not blocked during the aircraft cleaning process, and also ensuring that the smooth surface around the static pressure hole is not scratched, effectively improving the aircraft surface cleaning work.

[0022] 3) The adsorption-type aircraft static pressure hole protection device in this case controls the four suction cups at the four corners of the baffle through the adsorption control component. The operator only needs to switch the lifting slider between the second and third positions on the ground by using the control push button on the docking rod to control the self-locking or unlocking state of the suction cups. The operation is simple and efficient.

[0023] To provide a clearer understanding of the present invention, the preferred embodiments of the present invention will be described below in conjunction with the accompanying drawings. Attached Figure Description

[0024] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0025] Figure 2 This is a front view structural diagram of the present invention;

[0026] Figure 3 This is a rear view structural schematic diagram of the present invention;

[0027] Figure 4 This is a side view of the structure of the present invention;

[0028] Figure 5 This is a schematic diagram showing the connection between the shielding component and the raising component in this invention;

[0029] Figure 6 This is a schematic diagram of the shielding component of the present invention;

[0030] Figure 7 This is a schematic diagram of the structure of the lifting component of the present invention;

[0031] Figure 8 This is a schematic diagram of the lifting assembly of the present invention;

[0032] Figure 9 for Figure 8 A magnified view of position A in the middle;

[0033] Figure 10 This is a schematic diagram of the suction cup mechanism in this invention.

[0034] The names referred to by the numerical labels are:

[0035] 1-Shielding assembly; 2-Lifting assembly; 11-Baffle plate; 12-Static pressure hole plug; 14-Mounting base; 21-Connecting joint; 22-Connecting rod; 211-Straight through slide groove; 23-Spring pin; 31-First directional slide rod; 32-Second directional slide rod; 33-First sliding sleeve; 34-Second sliding sleeve; 35-Push plate; 36-Drive rod; 37-Reset spring; 38-Linkage rod; 41-Lifting slide rod; 42-Lifting slider; 44-Control push button; 421-First gear slot; 422-Second gear slot; 423-Third gear slot; 9-Suction cup; 91-Suction control handle; 92-Cam hinge seat. Detailed Implementation

[0036] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0037] Furthermore, if terms such as "first" or "second" are used for descriptive purposes only, they are mainly used to distinguish different devices, components or parts (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, components or parts, and should not be construed as indicating or implying relative importance.

[0038] Please also refer to Figure 1-10 An adsorption-type aircraft static pressure hole protection device includes a shielding component 1 and a detachable lifting component 2 that is docked to the shielding component 1. The shielding component 1 is used to shield the static pressure holes on the aircraft surface during surface cleaning, ensuring that the static pressure holes are not blocked and also protecting the smooth surface area around the static pressure holes. The lifting component 2 is used to raise the shielding component 1, making it easier for the shielding component 1 to be aligned with the static pressure holes located at a higher position on the aircraft surface.

[0039] The shielding assembly 1 includes a baffle 11, on the back center of which a static pressure hole plug 12 matching the static pressure hole of the aircraft is provided, and suction cups 9 are provided at the four corners of the baffle 11.

[0040] A mounting base 14 is provided at the center of the front of the baffle 11. The mounting base 14 is used to dock with the lifting component 2. The mounting base 14 is U-shaped with an outwardly expanding opening, so as to guide the docking with the lifting component 2. The two side walls of the mounting base 14 are symmetrically provided with docking holes (not shown in the figure), and the top of the mounting base 14 is provided with a suction control hole (not shown in the figure). The docking holes are used to lock the lifting component 2 when the baffle 1 docks with the lifting component 2, and the suction control hole is used to connect the lifting component 2 and the suction control component provided on the baffle 11.

[0041] The adsorption control assembly is used to control the four suction cups 9 at the four corners of the baffle 11. The adsorption control assembly includes a first directional slide rod 31 and a second directional slide rod 32 that are fixedly arranged in parallel on the baffle 11, a first sliding sleeve 33 that is slidably sleeved on the first directional slide rod 31, a second sliding sleeve 34 that is slidably sleeved on the second directional slide rod 32, a push plate 35 that is horizontally fixedly connected to the first sliding sleeve 33 and the second sliding sleeve 34, a drive rod 36 that is fixedly arranged in the middle of the push plate 35 and extends through the adsorption control hole into the mounting base 14, a reset spring 37 whose two ends are respectively connected to the push plate 35 and the mounting base 14, and four linkage rods 38 that are respectively connected to the two ends of the first sliding sleeve 33 and the two ends of the second sliding sleeve 34. The other ends of the four linkage rods 38 are respectively connected to the adsorption control handles 91 on the four suction cups 9.

[0042] Furthermore, both ends of the first sliding sleeve 33 are integrally provided with sliding seats, and both ends of the second sliding sleeve 34 are also integrally provided with sliding seats. The four linkage rods 38 and the push plate 35 are all connected through the sliding seats.

[0043] The lifting assembly 2 includes a pair of connectors 21 and a connecting rod 22 integrally connected to the bottom of the connectors 21. The connectors 21 correspond to the mounting base 14, allowing them to be inserted and removed from the mounting base 14. A vertical through-slide groove 211 is vertically formed in the center of the front of the connector 21. A pair of spring pins 23 are symmetrically arranged laterally inside the connector 21. Each spring pin 23 penetrates the side wall of the through-slide groove 211 laterally. The pair of spring pins 23 correspond to a pair of mating holes on the side wall of the mounting base 14. When the connector 21 is inserted into the mounting base 14, the outer end of the spring pin 23 elastically sinks into the corresponding mating hole under external force, thus locking the connector 21 onto the mounting base 14. When the external force on the spring pin 23 is removed, the spring pin 23 returns to its original position outside the mating hole, allowing the connector 21 to be pulled out of the mounting base 14, thus unlocking the connector 21 from the mounting base 14.

[0044] Furthermore, the connecting rod 22 is a hollow tube, and the cavity of the connecting rod 22 is connected to the straight slide groove 211 on the connecting joint 21 to form an assembly slide, in which a lifting component is slidably installed.

[0045] The lifting assembly includes a lifting slide rod 41 and a lifting slider 42 connected as one piece. The lifting slide rod 41 is installed in the cavity of the connecting rod 22, and the lifting slider 42 is installed in the straight slide groove 211 of the connecting joint 21 and aligned with the adsorption control hole on the mounting base 14, so that when the lifting assembly is lifted as a whole by external force, the lifting slider 42 can lift the adsorption control rod in the adsorption control hole.

[0046] Furthermore, a control push button 44 is fixedly provided at the bottom end of the lifting slide rod 41. The control push button 44 extends laterally to the outside of the side wall of the docking rod 22. When the control push button 44 is pushed or pulled along the axial direction of the docking rod 22, the lifting assembly moves as a whole.

[0047] Furthermore, the lifting slider 42 has a conical head at one end facing the adsorption control rod, and three position slots are sequentially spaced on its side. The first position slot 421 is located at the upper end of the slope of the conical head, the second position slot 422 is located at the lower end of the slope of the conical head, and the third position slot 423 is located on the flat side of the lifting slider 42. The three position slots respectively cooperate with the spring pin 23, and the movement of the lifting slider 42 provides a lateral force to the spring pin 23, so that the lifting slider 42 has three functional positions, specifically:

[0048] First gear: This is the initial gear. The spring pin 23 corresponds to the first gear slot 421. At this time, the connector 21 can be freely inserted into the mounting base 14 or freely pulled out from the mounting base 14.

[0049] Second position: This position is the locking position of the connector 21. The spring pin 23 corresponds to the second position groove 422. Due to the action of the tapered head ramp, the spring pin 23 moves laterally to the outside and inserts into the corresponding mating hole on the mounting base 14, locking the connector 21 on the mounting base 14.

[0050] Third position: This position is the suction cup actuation position. The spring pin 23 corresponds to the third position slot 423. Due to the effect of the conical head ramp, when the lifting slider 42 moves from the second position to the third position, the spring pin 23 continues to move laterally outward. The spring pin 23 remains inserted in the corresponding docking hole on the mounting base 14. At the same time, the lifting slider 42 pushes the adsorption control rod upward. The adsorption control rod drives the push plate 35. The push plate 35 drives the reset spring 37, the first sliding sleeve 33 and the second sliding sleeve 34. The first sliding sleeve 33 and the second sliding sleeve 34 simultaneously drive the four linkage rods 38. The four linkage rods 38 respectively drive the adsorption control handles 91 on the four suction cups 9 to deflect to different switch positions, thereby controlling the adsorption action (locking or unlocking) of the suction cups 9.

[0051] As a preferred embodiment, the suction cup 9 in this case is a product in the prior art, which includes a suction cup 9 body and an adsorption control handle 91 disposed on the suction cup 9 body. The adsorption control handle 91 is connected to the suction cup 9 body through a cam hinge seat 92. Since the cam hinge seat 92 has a different radius, the adsorption action of the suction cup 9 (i.e., the locked or unlocked state of the suction cup 9) can be controlled by controlling the deflection direction of the adsorption control handle 91 under the cooperation of the suction cup spring.

[0052] Preferably, in this embodiment, the baffle 11 is made of plastic to reduce weight; the static pressure hole plug 12 is made of waterproof sponge to effectively prevent cleaning water and other foreign objects from entering the static pressure hole on the aircraft surface.

[0053] The actual operating procedure for this device is as follows:

[0054] 1) Before cleaning the aircraft surface, on the ground, the staff connects the lifting assembly 2 to the shielding assembly 1. Specifically, the lifting slider 42 is kept in the first position, the connector 21 is inserted into the mounting base 14, and the lifting slider 42 is pushed from the first position to the second position by the control push button 44, so that the connector 21 is locked in the mounting base 14.

[0055] 2) The operator holds the docking rod 22 to raise the shielding component 1 and gradually brings the baffle 11 closer to the aircraft surface, and blocks the static pressure hole with the static pressure hole plug 12. Then, the lifting slider 42 is pushed from the second position to the third position. At this time, the lifting slider 42 pushes the adsorption control rod to move upward. The adsorption control rod drives the push plate 35 and the return spring 37. The push plate 35 drives the first sliding sleeve 33 and the second sliding sleeve 34. The first sliding sleeve 33 and the second sliding sleeve 34 simultaneously drive the four linkage rods 38. The four linkage rods 38 respectively drive the adsorption control handles 91 on the four suction cups 9 to deflect upward, so that the suction cups 9 are in the open (unlocked) state, and at this time the return spring 37 is in the stretched state.

[0056] 3) The staff moves the lifting slider 42 from the third position back to the second position. At this time, as the return spring 37 gradually returns to its original position (retracted state), and as the lifting slider 42 gradually moves down and separates from the adsorption control rod, the return spring 37 also gradually retracts and drives the push plate 35 and the adsorption control rod to move down. The push plate 35 drives the first sliding sleeve 33 and the second sliding sleeve 34. The first sliding sleeve 33 and the second sliding sleeve 34 simultaneously drive the four linkage rods 38. The four linkage rods 38 respectively drive the adsorption control handles 91 on the four suction cups 9 to deflect downward, so that the suction cups 9 automatically adsorb onto the surface of the aircraft and the suction cups 9 are in the closed (locked) state.

[0057] 4) The staff uses the push button 44 to push the lifting slider 42 back from the second position to the first position, so that the connector 21 is unlocked from the mounting base 14. The staff removes the lifting assembly 2 (at this time, the shielding assembly 1 remains attached to the aircraft surface. The purpose of removing the lifting assembly 2 at this time is to reduce the overall weight of the hanging parts on the baffle 11 and prevent the shielding assembly 1 from falling off the aircraft surface).

[0058] 5) Staff begin cleaning the aircraft surface (during the cleaning process, the static pressure hole area remains shielded and protected);

[0059] 6) After the cleaning work is completed, the staff inserts the connector 21 into the mounting base 14 again, and first pushes the lifting slider 42 from the first position to the second position through the control push button 44. The connector 21 is locked in the mounting base 14 again. The lifting slider 42 continues to be pushed from the second position to the third position. The suction cup 9 moves to the open position (unlocked state) again, so that the suction cup 9 is released from the surface of the aircraft.

[0060] 7) Ground personnel remove the shielding component 1 via the docking rod 22.

[0061] Compared with the prior art, the beneficial effects of the present invention are as follows: The adsorption-type aircraft static pressure hole protection device of this invention controls the four suction cups 9 at the four corners of the baffle through the adsorption control component. The operator only needs to switch the lifting slider between the second and third positions on the ground by using the control push button on the docking rod to control the self-locking or unlocking state of the suction cups 9. The operation is simple and efficient.

[0062] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. An adsorption-type aircraft static pressure port protection device, comprising a shielding assembly and a detachable lifting assembly docked to the shielding assembly, characterized in that: The shielding assembly includes a baffle plate with a static pressure hole plug matching the static pressure hole of the aircraft located at the center of its back side, and suction cups located at the four corners of the baffle plate; a mounting base is located at the center of the front side of the baffle plate, with symmetrical docking holes on both side walls of the mounting base, and a suction control hole is formed through the top of the mounting base; a suction control assembly is also located on the baffle plate at the periphery of the mounting base. The adsorption control assembly includes a first directional slide rod and a second directional slide rod fixedly mounted parallel to the baffle plate, a first sliding sleeve slidably mounted on the first directional slide rod, a second sliding sleeve slidably mounted on the second directional slide rod, a push plate fixedly connected laterally to the first and second sliding sleeves, a drive rod fixedly mounted in the middle of the push plate and extending through the adsorption control hole into the mounting base, a reset spring with its two ends connected to the push plate and the mounting base respectively, and four linkage rods connected to the two ends of the first and second sliding sleeves respectively. The other ends of the four linkage rods are respectively connected to the adsorption control handles on the four suction cups.

2. The adsorption-type aircraft static pressure hole protection device according to claim 1, characterized in that: The lifting assembly includes a pair of connectors and a connecting rod integrally connected to the bottom of the connectors; a straight through groove is vertically opened in the center of the front of the connectors, and a pair of spring pins are symmetrically arranged laterally inside the connectors, each spring pin passing through the side wall of the straight through groove laterally, and the pair of spring pins correspond to a pair of docking holes on the side wall of the mounting base; the connecting rod is a hollow tube, and the cavity of the connecting rod is connected to the straight through groove on the connector to form an assembly slide, in which a lifting assembly is slidably installed.

3. The adsorption-type aircraft static pressure hole protection device according to claim 2, characterized in that: The lifting assembly includes a lifting slide rod and a lifting slider connected as one piece; the lifting slide rod is installed in the cavity of the docking rod, and the lifting slider is installed in the straight groove of the docking joint.

4. The adsorption-type aircraft static pressure hole protection device according to claim 3, characterized in that: The lifting slider has a conical head at one end facing the adsorption control rod, and three position slots are arranged at intervals on the side of the lifting slider. The first position slot is located at the upper end of the slope of the conical head, the second position slot is located at the lower end of the slope of the conical head, and the third position slot is located on the flat side of the lifting slider. The three position slots are respectively engaged with the spring pin.

5. The adsorption-type aircraft static pressure hole protection device according to claim 4, characterized in that: A control push button is fixedly installed at the bottom end of the lifting slide rod, and the control push button extends laterally to the outside of the side wall of the docking rod.

6. The adsorption-type aircraft static pressure hole protection device according to claim 4, characterized in that: The baffle plate is also provided with several weight-reducing holes.

7. The adsorption-type aircraft static pressure hole protection device according to claim 4, characterized in that: The mounting base is U-shaped with an opening that expands outwards.

8. The adsorption-type aircraft static pressure hole protection device according to claim 4, characterized in that: The baffle is made of plastic, and the static pressure hole plug is made of waterproof sponge.

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