Telescopic sliding block device of aircraft

Abstract

The invention provides a telescopic sliding block device of an aircraft, which relates to the technical field of aircraft sliding blocks, is arranged on an aircraft cabin and comprises a first accommodating groove, a second accommodating groove and a sliding block, the sliding block is arranged in the first containing groove in a sliding mode, and part of the sliding block can stretch out of the first containing groove; the first elastic component is connected with the aircraft cabin and the sliding block and is used for applying first elastic force to the sliding block, and the first elastic force enables the sliding block to retract into the first containing groove; the clamping part is arranged in the first containing groove, and the clamping part is used for being connected with the sliding block in a clamped mode; the cover plate is in sliding connection with the aircraft cabin, and the cover plate can close the first containing groove; the problems that in the prior art, a sliding block device of an aircraft is located outside an aircraft cabin, air resistance is increased, stealth performance is affected, and flight precision is reduced are solved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft slider technology, and more specifically, relates to an aircraft telescopic slider device. Background Technology

[0002] The aircraft's mounting blocks are typically installed on the outer wall of the aircraft and connect to the mounting rails on the carrier aircraft for mounting the aircraft. Currently, aircraft mounting blocks are usually standard fixed blocks, directly mounted on the outer wall of the aircraft cabin, with two to three blocks per aircraft. After launch, the blocks are exposed on the outer side of the aircraft cabin wall. During high-speed flight, the exposed blocks increase air resistance, reducing the aircraft's speed, range, and maneuverability to some extent. Simultaneously, the blocks' installation on the outer side of the cabin wall increases the radar cross-section, reducing the aircraft's stealth capabilities. Furthermore, in engineering practice, the exposed blocks have been found to cause slight vibrations during flight, potentially reducing the aircraft's target tracking accuracy. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of existing technologies by providing a telescopic slider device for aircraft, which solves the problems of existing aircraft slider devices being located outside the aircraft cabin, increasing air resistance, affecting stealth performance, and reducing flight accuracy.

[0004] To achieve the above objectives, the present invention provides a telescopic slider device for aircraft, which is installed on the aircraft cabin and includes: A first receiving slot is formed in the aircraft cabin and is open at its outer end; A slider, wherein the slider is slidably disposed within the first receiving groove, and a portion of the slider is capable of extending out of the first receiving groove; A first elastic component is connected to the aircraft cabin and the slider, and is used to apply a first elastic force to the slider to retract it into the first receiving groove. A snap-fit ​​component is disposed within the first receiving groove and is used to snap-fit ​​with the slider; A cover plate, which is slidably connected to the aircraft cabin, is capable of closing the first receiving slot.

[0005] Optionally, the first receiving groove has an inwardly protruding first limiting part on the groove wall near its open end, forming a stepped groove, and the slider has a second limiting part on both sides that cooperates with the first limiting part.

[0006] Optionally, the two side walls of the first receiving groove are provided with a first mounting groove communicating with it, the snap-fit ​​component is disposed in the first mounting groove, the second limiting part is provided with a snap-fit ​​groove, and the snap-fit ​​component can snap-fit ​​with the snap-fit ​​groove.

[0007] Optionally, the locking component engages with the locking groove when the slider is in the extended state, and the locking component engages with the second limiting part when the slider is in the retracted state.

[0008] Optionally, the snap-fit ​​component includes a push-pull electromagnet, the telescopic end of which engages with the snap-fit ​​groove.

[0009] Optionally, a second receiving groove is provided on one side wall of the first receiving groove, and the cover plate is slidably disposed in the second receiving groove.

[0010] Optionally, a second elastic member is provided in the second receiving groove. The second elastic member is connected to the cover plate and is used to apply a second elastic force to the cover plate to move it in the direction of closing the first receiving groove.

[0011] Optionally, the cover plate is provided with a resilient snap-fit ​​element, which can snap into the aircraft cabin when the cover plate closes the first receiving slot.

[0012] Optionally, a cylindrical portion is provided on one side of the cover plate, and a second mounting groove is formed inside the cylindrical portion. The cover plate has a through hole communicating with the second mounting groove, and the elastic snap-fit ​​member is disposed in the second mounting groove and can extend out from the through hole.

[0013] Optionally, the elastic snap-fit ​​component includes a U-shaped leaf spring and a locking block. The U-shaped leaf spring is disposed in the second mounting groove. One end of the locking block is connected to one end of the U-shaped leaf spring, and the other end of the locking block can pass through the through hole and extend out, and can engage with the groove wall of the first receiving groove when the cover plate closes the first receiving groove.

[0014] This invention provides a telescopic slider device for aircraft, which has the following advantages: The telescopic slider device features a telescopic design, allowing the slider to retract into a first receiving slot under the action of a first elastic component. This reduces air resistance during flight, potentially increasing the aircraft's range, speed, and maneuverability. It also reduces the radar cross-section of the aircraft cabin, thus improving its stealth capabilities. Furthermore, it avoids slight vibrations during flight caused by exposed sliders, improving the accuracy of target tracking. Finally, the sliding cover closes the first receiving slot, ensuring a degree of airtightness at the slot opening and preventing rainwater and dust from entering the aircraft cabin.

[0015] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0016] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0017] Figure 1 An exploded structural schematic diagram of an aircraft telescopic slider device according to an embodiment of the present invention is shown.

[0018] Figure 2 A side view of an aircraft telescopic slider device in the extended state, according to an embodiment of the present invention, is shown.

[0019] Figure 3 It shows Figure 2 A schematic diagram of the cross-sectional structure along direction A.

[0020] Figure 4 A top view of an aircraft telescopic slider device in the retracted state, according to an embodiment of the present invention, is shown.

[0021] Figure 5 It shows Figure 4 A schematic diagram of the cross-sectional structure along direction B.

[0022] Figure 6 A three-dimensional structural schematic diagram of a telescopic slider device for aircraft according to an embodiment of the present invention is shown.

[0023] Figure 7 A top view of a slotted section on the aircraft cabin is shown, illustrating a telescopic slider device for an aircraft according to an embodiment of the present invention.

[0024] Figure 8 It shows Figure 7 A schematic diagram of the C-direction cross-section structure.

[0025] Figure 9 A three-dimensional structural schematic diagram of the cover plate in the retracted state of an aircraft telescopic slider device according to an embodiment of the present invention is shown.

[0026] Figure 10 A side view of the cover plate of an aircraft telescopic slider device in the retracted state according to an embodiment of the present invention is shown.

[0027] Figure 11 It shows Figure 10 A schematic diagram of the D-direction cross-section structure.

[0028] Figure 12 A side view of the cover plate of an aircraft telescopic slider device with the locking block extended, according to an embodiment of the present invention, is shown.

[0029] Figure 13 It shows Figure 12 Schematic diagram of the cross-sectional structure along direction E.

[0030] Explanation of reference numerals in the attached figures: 1. Slider; 2. First elastic component; 3. Snap-fit ​​component; 4. Cover plate; 5. Second elastic component; 6. Elastic snap-fit ​​component; 7. Aircraft cabin. Detailed Implementation

[0031] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0032] like Figures 1 to 5 As shown, the present invention provides a telescopic slider device for aircraft, which is installed on the aircraft cabin and includes: The first receiving slot is located in the aircraft cabin 7 and is open at its outer end; Slider 1 is slidably disposed in the first receiving groove, and a portion of slider 1 can extend out of the first receiving groove; The first elastic component 2 is connected to the aircraft cabin 7 and the slider 1, and is used to apply a first elastic force to the slider 1 to retract it into the first receiving groove. The snap-fit ​​component 3 is disposed in the first receiving groove and is used to snap-fit ​​with the slider 1; Cover plate 4 is slidably connected to the aircraft cabin 7 and can close the first receiving slot.

[0033] Specifically, to address the problems in existing technologies where the slider device of an aircraft is located outside the aircraft cabin 7, increasing air resistance, affecting stealth performance, and reducing flight accuracy, the telescopic slider device provided by this invention features a telescopic design for the slider 1. Under the action of the first elastic component 2, the slider 1 can be retracted into the first receiving slot, thereby reducing air resistance during flight and increasing the aircraft's range, speed, and maneuverability to some extent. It also reduces the radar cross-section of the aircraft cabin 7, thus improving the aircraft's stealth capability to some extent. Furthermore, it avoids the problem of slight vibrations during flight caused by the exposed slider 1, which is beneficial for ensuring the accuracy of the aircraft in tracking targets. Finally, by closing the first receiving slot with a sliding cover 4, it also ensures the airtightness of the area where the first receiving slot is located in the aircraft cabin 7 to a certain extent, preventing rainwater and sand from entering the aircraft cabin 7.

[0034] Optionally, the first receiving groove has an inwardly protruding first limiting part on the groove wall near its open end, forming a stepped groove, and the slider 1 has a second limiting part on both sides that cooperates with the first limiting part.

[0035] Specifically, such as Figures 6 to 8 As shown, the main body of slider 1 has a π-shaped structure, and outwardly extending wing plates are provided on both sides of its top surface, which are different from the second limiting part. These wing plates can cooperate with the guide rail of the aircraft's mounting device. In other words, slider 1 has an overall I-shaped structure with the upper and lower sides twisted by 90°. The interior of slider 1 is hollowed out to reduce its weight. The second limiting parts on both sides of the lower part of slider 1 can cooperate with the first limiting part on the groove wall of the first receiving groove when slider 1 is in the extended state, so as to bear the weight of the aircraft's mounting.

[0036] Optionally, the two side walls of the first receiving groove are provided with a first mounting groove communicating with it, the snap-fit ​​component 3 is provided in the first mounting groove, and the second limiting part is provided with a snap-fit ​​groove, so that the snap-fit ​​component 3 can snap-fit ​​with the snap-fit ​​groove.

[0037] Specifically, the two snap-fit ​​components 3 are respectively set in two oppositely arranged first mounting slots. The snap-fit ​​components 3 snap-fit ​​with the snap-fit ​​slot at the lower end of the slider 1, which can snap-fit ​​and position the slider 1.

[0038] Optionally, the snap-fit ​​component 3 engages with the snap-fit ​​groove when the slider 1 is in the extended state, and engages with the second limiting part when the slider 1 is in the retracted state.

[0039] Specifically, when the slider 1 is in the extended state, the locking component 3 engages with the locking groove on the second limiting part at the lower end of the slider 1 to position the slider 1 in the extended state. When the slider 1 is in the retracted state, the second limiting part moves down, and the locking component 3 can engage with the upper surface of the second limiting part to position the slider 1 in the retracted state.

[0040] Optionally, the snap-fit ​​component 3 includes a push-pull electromagnet, the telescopic end of which engages with the snap-fit ​​groove.

[0041] Specifically, the push-pull electromagnet includes a pin, a retaining ring, and a frame structure. Its rear end is connected to the integrated control unit and battery of the aircraft via a cable to receive electrical signals. On one hand, when the push-pull electromagnet is de-energized, its pin can pop out of the frame structure under the elastic force of the retaining ring. When the second limiting part of the slider 1 contacts the first limiting part at the upper end of the first receiving groove, the pin of the push-pull electromagnet can extend into the locking groove of the slider 1 to limit and fix the slider 1 in the extended state, keeping its wing part extended outside the aircraft cabin 7. When the second limiting part of the slider 1 moves to the bottom of the first receiving groove inside the aircraft cabin 7, the pin of the push-pull electromagnet can extend into the upper side of the slider 1 to limit and fix the slider 1 in the retracted state, keeping it retracted back into the aircraft cabin 7. On the other hand, when the push-pull electromagnet is energized, the pin retracts and is pulled out under the action of electromagnetic force, releasing the limitation on the slider 1 in both states, and at the same time, the retaining ring of the push-pull electromagnet is compressed.

[0042] In this embodiment, a square pin hole is opened in the middle of the second limiting part on both the front and rear sides of the lower part of the slider 1. The second limiting part is slidably disposed in the first receiving groove. When the second limiting part of the slider 1 slides up to contact the first limiting part, the square pin hole is aligned with the pin of the push-pull electromagnet. The pin of the push-pull electromagnet extends into the square pin hole under the drive of its retaining spring force, limiting the slider 1 from both sides at the same time. At the same time, the second limiting part at the lower part of the slider 1 is limited by the first limiting part, so that the slider 1 cannot move up and down along the first receiving groove, and its wing plate part remains in the state of extending out of the cabin wall of the aircraft body 7, ensuring the stable mounting of the aircraft. A trapezoidal groove is opened in the middle of the upper part of the slider 1. When the slider 1 retracts under the action of the pulling force of the first elastic component 2, After retracting into the aircraft cabin 7, the position of the trapezoidal groove corresponds exactly to the position of the pin of the push-pull electromagnet in the aircraft cabin 7. The slider 1 releases the limit on the pin of the push-pull electromagnet, and the pin of the push-pull electromagnet will extend again under the drive of its retaining spring force and lock into the trapezoidal groove on the upper side of the slider 1, thus limiting the slider 1 and keeping it retracted into the aircraft cabin 7, preventing the slider 1 from moving up and down during the flight of the aircraft. The four sides of the square pin hole and the front and rear sides of the trapezoidal groove are all provided with chamfers to facilitate the locking of the pin of the push-pull electromagnet. The outer side of the wing plate is provided with chamfers to facilitate the assembly and connection of the slider 1 and the guide rail. A circular groove is opened in the middle of the lower surface of the slider 1 for installing the first elastic component 2.

[0043] Optionally, a second receiving groove is provided on one side wall of the first receiving groove, and the cover plate 4 is slidably disposed in the second receiving groove.

[0044] Specifically, the cover plate 4 can be stored in the second receiving groove when the slider 1 is in the extended state, and slides with the second receiving groove. At this time, the end of the cover plate 4 near the slider 1 is pushed and limited by the slider 1 to keep it in a retracted state, so that when the slider 1 is in the retracted state, the cover plate 4 can extend and close the open first receiving groove.

[0045] Optionally, a second elastic member 5 is provided in the second receiving groove. The second elastic member 5 is connected to the cover plate 4 and is used to apply a second elastic force to the cover plate 4 to move it in the direction of closing the first receiving groove.

[0046] Specifically, the second elastic component 5 can compress and store energy when the cover plate 4 retracts, and can release energy and push the cover plate 4 out when the slider 1 retracts, thereby closing the first receiving groove.

[0047] In this embodiment, the first elastic component 2 and the second elastic component 5 are a tension spring and a compression spring, respectively.

[0048] Optionally, the cover plate 4 is provided with a resilient snap-fit ​​element 6, which can snap into the aircraft cabin 7 when the cover plate 4 closes the first receiving slot.

[0049] Specifically, the elastic snap-fit ​​6 can be elastically protruding from the surface of the cover plate 4 to achieve snap-fit ​​positioning with the aircraft cabin 7. When the cover plate 4 retracts, the elastic snap-fit ​​6 retracts. When the cover plate 4 extends, the elastic snap-fit ​​6 extends from the cover plate 4 and snaps onto the groove wall of the first receiving groove of the aircraft cabin 7, keeping the cover plate 4 closed to the first receiving groove.

[0050] Optionally, a cylindrical portion is provided on one side of the cover plate 4, and a second mounting groove is formed inside the cylindrical portion. The cover plate 4 has a through hole communicating with the second mounting groove. The elastic snap-fit ​​member 6 is disposed in the second mounting groove and can extend out from the through hole.

[0051] Specifically, the cylindrical part is integrally formed with the cover plate 4. The cylindrical part accommodates the installation of the elastic snap-fit ​​6, and the second elastic component 5 can press against the end of the cylindrical part to achieve connection with the cover plate 4. The elastic snap-fit ​​6 can extend from the through hole on the cover plate 4 to form a protruding state, and snap onto the groove wall of the first receiving groove of the aircraft cabin 7 when the cover plate 4 is extended.

[0052] In this embodiment, as Figure 9 As shown, the cover plate 4 is a curved plate conforming to the inner surface of the aircraft cabin wall. Its material is the same as that of the aircraft cabin 7, and its thickness is the same as that of the cabin wall. The right middle part of the cover plate 4 is thickened to form a cylindrical part, which slides in conjunction with a cylindrical groove connected to one side of the second receiving groove. The cylindrical part has a cuboid groove inside for installing the elastic snap-fit ​​part 6. When the cover plate 4 slides to contact the groove wall of the first receiving groove on the aircraft cabin 7 or is inserted into the receiving groove on the groove wall of the first receiving groove, the first receiving groove in the middle of the aircraft cabin 7 and the slider 1 retracted into the aircraft cabin 7 are covered by the cover plate 4, which can reduce air resistance during flight and maintain the airtightness of the aircraft cabin 7 to a certain extent. When the slider 1 retracts into the aircraft cabin 7, the pin of the push-pull electromagnet extends into the upper part of the slider 1 to limit the slider 1. There is a sufficient gap between the retracted slider 1 and the cover plate 4, and the retracted slider 1 will not interfere with the closing of the cover plate 4.

[0053] Optionally, the elastic snap-fit ​​element 6 includes a U-shaped leaf spring and a locking block. The U-shaped leaf spring is disposed in the second mounting groove, one end of the locking block is connected to one end of the U-shaped leaf spring, and the other end of the locking block can pass through the through hole and extend out, and can snap into the groove wall of the first receiving groove when the cover plate 4 closes the first receiving groove.

[0054] Specifically, the other end of the U-shaped leaf spring contacts the groove wall of the second mounting groove, and the U-shaped leaf spring provides a third elastic force to the locking block. Under the action of the third elastic force, the locking block can extend from the through hole and engage with the groove wall of the first receiving groove, thereby positioning and fixing the cover plate 4. The U-shaped leaf spring can be limited by the upper locking block, the slightly longer lower leaf spring, and the hole wall of the through hole, without the need to add other structures to limit the U-shaped leaf spring. In addition, the entire telescopic slider device of the aircraft is driven only by spring force and electric power, avoiding the use of pyrotechnic devices such as gas actuators, making it safe to use.

[0055] In this embodiment, as Figures 10 to 13 As shown, the elastic locking component 6 includes an upper square locking block and a lower U-shaped leaf spring. The upper leaf spring of the U-shaped leaf spring is connected to the locking block, and the lower leaf spring is slightly longer than the upper leaf spring, used to limit the U-shaped leaf spring. In the initial state, the elastic locking component 6 can be installed into the cylindrical part in the middle of the right side of the cover plate 4 by pressing down the locking block, and the locking block extends out from the through hole. After the U-shaped leaf spring is installed, the left end of its locking block will abut against the left end face of the through hole on the cover plate 4, and the right end of its slightly longer lower leaf spring will abut against the right end face of the second mounting groove in the cylindrical part. Under the combined action of the two directions, the cover plate 4 limits the installation of the U-shaped leaf spring. In addition, the lower part of the right end face of the through hole is shaped with a 45° chamfer to leave space so that the locking block can be pressed into the through hole when subjected to downward force. When slider 1 is in the extended state, the wing plate of slider 1 extends outside the aircraft cabin 7. Slider 1 limits the cover plate 4 and the second elastic component 5, causing the second elastic component 5 to be compressed. At the same time, the cabin wall of the aircraft cabin 7 limits the U-shaped leaf spring, causing its locking block to be compressed into the through hole. When the pin of the push-pull electromagnet releases the limitation on slider 1, slider 1 is pulled back into the aircraft cabin 7 by the first elastic component 2. At this time, slider 1 releases the limitation on cover plate 4, and cover plate 4 slides under the drive of the second elastic force, closing the first receiving groove and exposing the through hole. The cabin wall releases the limitation on the locking block of the U-shaped leaf spring, causing the locking block to extend under the drive of the third elastic force. At this time, the right end of the locking block is locked onto the right end of the groove wall of the first receiving groove, locking cover plate 4 and preventing cover plate 4 from moving back and forth during the flight of the aircraft.

[0056] In this embodiment, the installation process of the aircraft telescopic slider device is as follows: First, install the push-pull electromagnets. Install two push-pull electromagnets into the first mounting slots on both sides of the first receiving slot. Then, connect the cables extending from the rear of the push-pull electromagnets to the aircraft's integrated control unit and battery to receive power signals. The push-pull electromagnets are not energized during installation, and their pins are in a state of extending out of the frame structure under the action of the snap ring. It should be noted that during the installation of the aircraft's retractable slider device or in the ground test state, the push-pull electromagnets can also be energized directly through the cables to make them actuate, so as to apply or release the limit on slider 1.

[0057] Secondly, the slider 1 is installed. An opening is provided at the bottom of the first receiving slot of the aircraft cabin 7, and a bottom baffle is provided. The bottom baffle is fixed to the first receiving slot by bolts distributed around it. At the same time, the bottom baffle is provided with a circular groove for installing the first elastic component 2. Therefore, the first receiving slot can communicate with the interior of the aircraft cabin 7 for installing the slider 1. Before installing the slider 1, the front and rear push-pull electromagnets are energized to retract their pins back into the frame structure to avoid interfering with the installation of the slider 1. When the slider 1 is installed, the bolts of the bottom baffle are opened and the bottom baffle is removed. Inside the aircraft cabin 7, the slider 1 is installed from the bottom of the first receiving slot into the first receiving slot, and the slider 1 is pushed to the top so that the square pin hole of the slider 1 corresponds to the position of the pin of the push-pull electromagnet. The front and rear push-pull electromagnets are de-energized, and the pins will extend into the square pin holes of the front and rear protrusions on the lower part of the slider 1 under the drive of the spring force of the retaining spring, thus limiting the slider 1 and keeping its wing section extended outside the aircraft cabin 7.

[0058] Next, install the first elastic component 2, extend the upper end of the first elastic component 2 into the first receiving groove, install it into the circular groove on the lower surface of the slider 1, and install the lower end of the first elastic component 2 into the circular groove of the bottom baffle. At this time, the first elastic component 2 is in a stretched state; then install the bottom baffle onto the first receiving groove with bolts.

[0059] Then, install the elastic locking member 6 into the cover plate 4, compress the upper and lower leaf springs of the elastic locking member 6, and push the elastic locking member 6 into the cylindrical part until the locking block extends out of the through hole; at this time, the left end of the locking block will be locked into the left end face of the through hole, and the right end of the lower leaf spring of the elastic locking member 6 will push against the right end face of the cylindrical part; when the locking block is pressed down, the locking block can be pressed into the through hole on the right side of the cover plate 4, ensuring that the cover plate 4 can slide to the left under the drive of the second elastic member 5.

[0060] Finally, the cover plate 4 and the second elastic component 5 are installed. Since the cover plate 4 is larger than the opening area of ​​the first receiving slot in the middle of the aircraft cabin 7, it cannot be installed from the first receiving slot. To solve this problem, similar to the bottom opening of the stepped slot of the aircraft cabin 7, a right baffle can be set in the second receiving slot and the upper rear opening of the aircraft cabin 7, and fixed to the aircraft cabin 7 with bolts. After connecting the right end of the cover plate 4 and the left end of the second elastic component 5, the cover plate 4 and the second elastic component 5 can be installed into the second receiving slot of the aircraft cabin 7 from the rear opening inside the aircraft cabin 7. Then, the right baffle is fixed with bolts to complete the installation of the cover plate 4 and the second elastic component 5. At this time, the right end of the slider 1 limits the cover plate 4, the right end of the cover plate 4 limits the second elastic component 5, and the right baffle limits the right end of the second elastic component 5, so that it is in a compressed state.

[0061] At this point, all components of the telescopic slider device for the aircraft have been installed. The wing plate of slider 1 is extended out of the aircraft cabin 7, and the aircraft can be mounted onto the guide rail of the aircraft mounting device on the carrier aircraft via slider 1.

[0062] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. An aircraft telescoping skid device, disposed on an aircraft fuselage, characterized by, The utility model relates to an aircraft cabin door structure, which comprises: a first accommodating groove formed in the aircraft cabin and having an open end; a sliding block arranged in the first accommodating groove and capable of being partially extended from the first accommodating groove; a first elastic component connected with the aircraft cabin and the sliding block and used for applying a first elastic force to the sliding block to retract the sliding block into the first accommodating groove; a clamping component arranged in the first accommodating groove and used for clamping the sliding block; a cover plate slidingly connected with the aircraft cabin and capable of closing the first accommodating groove.

2. The aircraft telescoping skid apparatus of Claim 1, wherein, The groove wall of the first accommodating groove near the open end is provided with a first limiting portion protruding inward to form a stepped groove, and the two sides of the sliding block are provided with second limiting portions for limiting cooperation with the first limiting portion.

3. The aircraft telescoping skid apparatus of Claim 2, wherein, The two groove walls of the first accommodating groove are provided with first mounting grooves in communication with the first accommodating groove, the clamping component is arranged in the first mounting groove, the second limiting portion is provided with a clamping groove, and the clamping component is capable of clamping cooperation with the clamping groove.

4. The aircraft telescoping skid apparatus of Claim 3, wherein, The clamping component is capable of clamping cooperation with the clamping groove when the sliding block is in the extended state, and the clamping component is capable of clamping cooperation with the second limiting portion when the sliding block is in the retracted state.

5. The aircraft telescoping skid apparatus of Claim 3, wherein, The clamping component comprises a push-pull electromagnet, and the telescopic end of the push-pull electromagnet is capable of clamping cooperation with the clamping groove.

6. The aircraft telescoping skid apparatus of Claim 1, wherein, One side groove wall of the first accommodating groove is provided with a second accommodating groove in communication with the first accommodating groove, and the cover plate is slidingly arranged in the second accommodating groove.

7. The aircraft telescoping skid apparatus of Claim 6, wherein, The second accommodating groove is provided with a second elastic component connected with the cover plate and used for applying a second elastic force to the cover plate to move the cover plate towards the direction of closing the first accommodating groove.

8. The aircraft telescoping skid apparatus of Claim 7, wherein, The cover plate is provided with an elastic clamping piece capable of clamping with the aircraft cabin when the cover plate closes the first accommodating groove.

9. The aircraft telescoping skid apparatus of Claim 8, wherein, One side of the cover plate is provided with a cylindrical portion, a second mounting groove is formed in the cylindrical portion, the cover plate is provided with a through hole in communication with the second mounting groove, the elastic clamping piece is arranged in the second mounting groove and capable of being extended from the through hole.

10. The aircraft telescoping skid apparatus of Claim 8, wherein, The elastic clamping piece comprises a U-shaped plate spring and a lock block, the U-shaped plate spring is arranged in the second mounting groove, one end of the lock block is connected with one end of the U-shaped plate spring, the other end of the lock block is capable of penetrating through the through hole and extending out and capable of clamping with the groove wall of the first accommodating groove when the cover plate closes the first accommodating groove.

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