A device and method for docking / separating an aircraft in the air based on a cylinder

Abstract

The present invention relates to a device and method for docking / separating an aircraft in mid-air based on a cylinder, belonging to the technical field of fixed-wing aircraft. The device can be directly mounted on the wingtip of an aircraft. Gas is injected into the device through an electromagnetic valve. After gas injection, the cylinder shaft enters a corresponding groove, and two connecting plates are connected. After gas is released, the cylinder shaft is retracted under the action of a return spring force, and the connection is released. The present invention can largely solve the problem of docking or separation of the wingtips of aircraft, especially unmanned aerial vehicles, in the air, taking into account the three characteristics of simple structure, reliability, and economy. The device has good adaptability and has certain application and promotion in the aviation field and related fields.

Description

Technical Field

[0001] The present invention relates to the technical field of fixed-wing aircraft, and in particular to a device and method for docking / separating an aircraft in the air based on a cylinder. Background Art

[0002] The larger the aspect ratio of a single aircraft, the greater its lift-to-drag ratio, thereby improving its cruising performance and enabling long-duration, high-altitude flight. However, as the aspect ratio of the wing increases, the manufacturing cost and difficulty of a single aircraft also increase significantly, and the requirements for takeoff and landing sites also become more stringent. At the same time, aeroelastic issues become more prominent in high-aspect-ratio aircraft.

[0003] At present, when two aircraft complete docking in the air, the docking process has problems such as long docking time and unstable docking, and it is impossible to complete rapid docking in actual applications.

[0004] The Chinese patent application number CN108583877A installs this mechanism on the rib of the wingtip of the aircraft, and uses a telescopic device to place the docking point on the outside of the wingtip; there is a docking rod on the extending side, and a gripper with a locking mechanism on the grasping side. When the two aircraft are close together, the docking rod is inserted into the gripper and locked, and then the two aircraft are pulled closer using the telescopic device to complete the docking. During the separation process, the telescopic device is used to push the two aircraft apart, and the electromagnet unlocks the gripper device. The gripper ejects the docking rod, and the mechanism is retracted to complete the separation. Although this method reduces the difficulty of the gripping process during the docking process, it does not effectively limit the position of the gripper. During the docking process, the position of the entire aircraft cannot be accurately fixed, and there is a problem of unstable docking.

[0005] Chinese patent publication number CN103963972B proposes a method for aerial wingtip docking for wingtip connection / dragging technology. However, this method requires very high accuracy in aircraft attitude control during the docking process, and the docking time is long and unstable, making it impossible to achieve rapid docking in actual applications.

[0006] Therefore, the above problems need to be solved urgently. Summary of the Invention

[0007] In view of the above problems, the present invention provides a device and method for aerial docking / separation of aircraft based on a cylinder. The device can be directly installed on the wingtip of the wing. The device is injected with air through an electromagnetic valve. After the air is injected, the cylinder shaft will enter the corresponding groove, and the two connecting plates will be connected. After the air is deflated, the cylinder shaft will be retracted under the action of the reset spring force, and the connection will be released. The present invention can solve the problem of wingtip docking or separation of aircraft, especially drones, in the air to a large extent, and takes into account the three characteristics of simple structure, reliability, and economy. The device has good adaptability and has certain application and promotion in the aviation field and related fields.

[0008] The present invention provides a device for docking / separating an aircraft in the air based on a cylinder, comprising:

[0009] Connecting plate 1 11, connecting plate 2 12, cylinder assembly and groove assembly;

[0010] The groove assembly is provided on the connecting plate 1 11 and is used to connect the cylinder assembly; the cylinder assembly is provided on the connecting plate 2 12;

[0011] Preferably, the connecting plate 11 is connected to the wingtip of the aircraft wing 1; the connecting plate 2 12 is connected to the wingtip of the aircraft wing 2;

[0012] Furthermore, the groove assembly includes: groove one 1, groove two 2 and groove three 3;

[0013] The cylinder assembly includes cylinder 1 6 and cylinder 2 7;

[0014] Furthermore, the cylinder 1 6 is axially arranged on the connecting plate 2 12 via the boss 1 61, and the cylinder 2 7 is axially arranged on the connecting plate 2 12 via the boss 2 71;

[0015] For example, the groove 1 is provided at the front end of the connecting plate 11 to reduce the weight of the rib of the aircraft wing 1; Figure 1 ;

[0016] The present invention designs the first groove as a weight-reducing groove, which is used to reduce the weight of the front end of the aircraft wing rib;

[0017] Exemplarily, the groove 1 and the groove 3 are respectively arranged on both sides of the groove 2;

[0018] The shape of the groove 2 matches the boss 1 61 on which the cylinder 1 is provided. During the wingtip docking of two aircraft, the cylinder 1 6 and the boss 1 61 dock with the groove 2 2.

[0019] The shape of the groove 3 matches the boss 2 71 on which the cylinder 2 7 is provided. During the wingtip docking of two aircraft, the cylinder 2 7 and the boss 2 71 dock with the groove 3 3.

[0020] Furthermore, the cylinder 1 and the cylinder 2 are connected to the solenoid valve through the pipeline 10 and the pipeline 2 respectively; the solenoid valve is connected to the main system of the aircraft;

[0021] The pipe 10 passes through the connecting plate 2 and is connected to the cylinder 1; the pipe 2 passes through the connecting plate 2 and is connected to the cylinder 2;

[0022] Furthermore, the cylinder assembly further includes a cylinder shaft 1 9 and a cylinder shaft 2 8;

[0023] The cylinder shaft 1 9 is arranged on the inner side of the cylinder 1 6; the cylinder shaft 2 8 is arranged on the inner side of the cylinder 1 7;

[0024] Furthermore, the connecting plate 11 further includes an axis connecting member 5, a connecting member 1 4 and a connecting member 2 13;

[0025] Exemplarily, the shaft connecting member 5 is arranged between the groove 2 and the groove 3; a connecting hole is provided in the shaft connecting member 5 for clamping the cylinder shaft 1 and the cylinder shaft 2;

[0026] The two ends of the connecting member 1 4 are respectively connected to the groove 1 and the groove 2;

[0027] The second connecting member 13 is connected to one side of the third groove;

[0028] The groove three is provided between the shaft connecting member 5 and the connecting member 2 13; Figure 1 ;

[0029] Furthermore, the cylinder shaft 1 9 is opposite to the cylinder shaft 2 8 and both are used to fix the shaft connecting member 5;

[0030] The cylinder shaft 1 9 has a telescopic function. When the wingtips of the aircraft are not docked, the cylinder shaft 1 is retracted in the cylinder 1. When receiving the extension signal from the cylinder, the cylinder shaft 1 extends out of the cylinder 1 and connects with the connecting hole of the shaft connector 5.

[0031] The cylinder shaft 2 has a telescopic function. When the wingtips of the aircraft are not docked, the cylinder shaft 2 is retracted in the cylinder 2. When receiving the extension signal from the cylinder, the cylinder shaft 2 extends out of the cylinder 2 and connects with the connecting hole of the shaft connector 5.

[0032] Furthermore, the cylinder 1 and the cylinder 2 are axially aligned and arranged axially at the position where the wingtip of the aircraft has the largest thickness; and longitudinally arranged at the middle position of the wingtip of the aircraft;

[0033] Furthermore, the axial length of the cylinder 1, the axial length of the cylinder 2, and the axial

[0034] The ratio of the intervals is 1:1:1;

[0035] The ratio of the axial spacing between the first and second cylinders to the axial length of the shaft connecting member is 1:1;

[0036] Exemplarily, the ratio between the axial length of the cylinder 1 and the rib chord of the aircraft wing tip is 1-2:20;

[0037] The ratio between the axial length of the second cylinder and the rib chord of the wingtip of the aircraft wing is 1-2:20;

[0038] The ratio between the axial spacing between the cylinder 1 and the cylinder 2 and the rib chord of the aircraft wing tip is 1-2:20;

[0039] In the technical solution of the present invention, the length of the two cylinders is 5% to 10% of the wingtip chord line, and the spacing between the two cylinders is 5% to 10% of the wingtip chord line, which is beneficial for the aircraft wing to present an optimal load-bearing state, ensure the stability of the flight state, and ensure that the connecting device has rotational freedom.

[0040] Furthermore, the cylinder-based aircraft aerial docking / separation device is applicable to aircraft wing airfoils with a wing rib chord length ≥ 200 mm.

[0041] Specifically, the axial length of the cylinders 1 and 2 is 5-10 mm;

[0042] The wingtip connection device in the technical solution of the present invention is small in size and quick in response.

[0043] In one embodiment of the present invention, when the wingtips of aircraft one and aircraft two reach a certain horizontal distance, the main systems of aircraft one and aircraft two send a docking signal, and the cylinder one 6 and boss one 61 in the wing rib of aircraft one dock into the groove two 2 until there is no gap at the docking; the cylinder two 7 and boss two 71 dock into the groove three 3 until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into the cylinder one and cylinder two, so that the cylinder shaft one and cylinder shaft two enter the shaft connector 5, forming a connection;

[0044] In one embodiment of the present invention, when the wingtips of aircraft 1 and aircraft 2 are in a docked state, the main systems of aircraft 1 and aircraft 2 send a separation signal, the solenoid valve stops injecting air, and after the injection stops, the cylinder 1 and cylinder 2 are deflated, and the cylinder shaft 1 and cylinder shaft 2 both leave the shaft connector 5, completing the separation of the wingtips of aircraft 1 and aircraft 2.

[0045] Furthermore, the material of the connecting plate 1 and the connecting plate 2 is aluminum alloy.

[0046] The connecting plate of the present invention is made of aluminum alloy plate, which has medium strength, good fatigue resistance and damage resistance, and also takes into account corrosion resistance. It is beneficial to improve the reliability, service life, safety and maintainability of the main structure of the aircraft body and other damage resistance. It has high fracture toughness, fatigue resistance and low fatigue crack growth rate.

[0047] Another object of the present invention is to provide a method for using a cylinder-based device for docking / separating an aircraft in mid-air, comprising:

[0048] The two aircraft, one on the left and one on the right, maintain a certain distance and fly level at the same height and front-to-back position, reducing the distance between the wings of the two aircraft until the wingtips of aircraft one and aircraft two reach a certain horizontal distance. The main systems of aircraft one and aircraft two send docking signals, and the cylinder one 6 and boss one 61 in the wing rib of aircraft one dock into the groove two 2 until there is no gap at the docking; the cylinder two 7 and boss two 71 dock into the groove three 3 until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into cylinder one and cylinder two, causing the cylinder shaft one and cylinder shaft two to enter the shaft connector 5 to form a connection;

[0049] In one embodiment of the present invention, when the wingtips of aircraft 1 and aircraft 2 are in a docked state, the main systems of aircraft 1 and aircraft 2 send a separation signal, the solenoid valve stops injecting air, and after the injection stops, the cylinder 1 and cylinder 2 are deflated, and the cylinder shaft 1 and cylinder shaft 2 both leave the shaft connector 5, completing the separation of the wingtips of aircraft 1 and aircraft 2.

[0050] Preferably, the chord length of the connecting plates 1 and 2 is 300 mm;

[0051] The axes of the cylinder 1 and the cylinder 2 are kept consistent so that the mechanism retains a relative roll angle of ±45°.

[0052] Compared with the prior art, the present invention has at least the following beneficial effects:

[0053] The device of the present invention uses a cylinder to improve the reaction speed of wingtip docking, and the device occupies a small space and can be suitable for docking and separating the wingtips of smaller wings. The present invention can solve the problem of wingtip docking or separation of aircraft, especially unmanned aerial vehicles, in the air to a large extent, taking into account the three characteristics of simple structure, reliability and economy. The device has good adaptability and has certain application and promotion in the aviation field and related fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] The drawings are only for purposes of illustrating particular embodiments and are not to be considered limiting of the invention.

[0055] Figure 1 Schematic diagram of a connecting plate 1 in an embodiment of the present invention;

[0056] Figure 2 A schematic diagram of a second connecting plate in an embodiment of the present invention;

[0057] Figure 3 (a) is a schematic diagram of a front view of the device after docking in an embodiment of the present invention;

[0058] Figure 3(b) is a schematic diagram of a top view of the device after docking in an embodiment of the present invention;

[0059] Figure 3 (c) is a schematic diagram of a perspective view of the front of the device after docking in an embodiment of the present invention;

[0060] Figure 4 Schematic diagram of a solenoid valve connected to the device of the present invention.

[0061] Reference numerals:

[0062] Groove 1 1, groove 2 2, groove 3 3, connector 1 4, shaft connector 5, cylinder 1 6, cylinder 2 7, boss 1 61, boss 2 71, cylinder shaft 2 8, cylinder shaft 1 9, pipe 1 10, connecting plate 1 11, connecting plate 2 12, connecting piece 2 13. DETAILED DESCRIPTION

[0063] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. In addition, the present invention can also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited by the specific embodiments disclosed below.

[0064] A specific embodiment of the present invention, as Figure 1-4 , discloses a device and method for aerial docking / separation of an aircraft based on a cylinder.

[0065] In order to illustrate the effectiveness of the method proposed by the present invention, the above technical solution of the present invention is described in detail below through a specific embodiment:

[0066] The present invention provides a device for docking / separating an aircraft in the air based on a cylinder, comprising:

[0067] Connecting plate 1 11, connecting plate 2 12, cylinder assembly and groove assembly;

[0068] The groove assembly is provided on the connecting plate 1 11 and is used to connect the cylinder assembly; the cylinder assembly is provided on the connecting plate 2 12;

[0069] Preferably, the connecting plate 11 is connected to the wingtip of the aircraft wing 1; the connecting plate 2 12 is connected to the wingtip of the aircraft wing 2;

[0070] Furthermore, the groove assembly includes: groove one 1, groove two 2 and groove three 3;

[0071] The cylinder assembly includes cylinder 1 6 and cylinder 2 7;

[0072] Furthermore, the cylinder 1 6 is axially arranged on the connecting plate 2 12 via the boss 1 61, and the cylinder 2 7 is axially arranged on the connecting plate 2 12 via the boss 2 71;

[0073] For example, the groove 1 is provided at the front end of the connecting plate 11 to reduce the weight of the rib of the aircraft wing 1; Figure 1 ;

[0074] The present invention designs the first groove as a weight-reducing groove, which is used to reduce the weight of the front end of the aircraft wing rib;

[0075] Exemplarily, the groove 1 and the groove 3 are respectively arranged on both sides of the groove 2;

[0076] The shape of the groove 2 matches the boss 1 61 on which the cylinder 1 is provided. During the wingtip docking of two aircraft, the cylinder 1 6 and the boss 1 61 dock with the groove 2;

[0077] The shape of the groove 3 matches the boss 2 71 on which the cylinder 2 7 is provided. During the wingtip docking of two aircraft, the cylinder 2 7 and the boss 2 71 are docked with the groove 3 3. Furthermore, the cylinder 1 and the cylinder 2 are connected to the solenoid valve via the pipe 10 and the pipe 2, respectively. The solenoid valve is connected to the main system of the aircraft.

[0078] The pipe 10 passes through the connecting plate 2 and is connected to the cylinder 1; the pipe 2 passes through the connecting plate 2 and is connected to the cylinder 2;

[0079] Furthermore, the cylinder assembly further includes a cylinder shaft 1 9 and a cylinder shaft 2 8;

[0080] The cylinder shaft 1 9 is arranged on the inner side of the cylinder 1 6; the cylinder shaft 2 8 is arranged on the inner side of the cylinder 1 7;

[0081] Furthermore, the connecting plate 11 further includes an axis connecting member 5, a connecting member 1 4 and a connecting member 2 13;

[0082] Exemplarily, the shaft connecting member 5 is arranged between the groove 2 and the groove 3; a connecting hole is provided in the shaft connecting member 5 for clamping the cylinder shaft 1 and the cylinder shaft 2;

[0083] The two ends of the connecting member 1 4 are respectively connected to the groove 1 and the groove 2;

[0084] The second connecting member 13 is connected to one side of the third groove;

[0085] The groove three is provided between the shaft connecting member 5 and the connecting member 2 13; Figure 1 ;

[0086] Furthermore, the cylinder shaft 1 9 is opposite to the cylinder shaft 2 8 and both are used to fix the shaft connecting member 5;

[0087] The cylinder shaft 1 9 has a telescopic function. When the wingtips of the aircraft are not docked, the cylinder shaft 1 is retracted in the cylinder 1. When receiving the extension signal from the cylinder, the cylinder shaft 1 extends out of the cylinder 1 and connects with the connecting hole of the shaft connector 5.

[0088] The cylinder shaft 2 has a telescopic function. When the wingtips of the aircraft are not docked, the cylinder shaft 2 is retracted in the cylinder 2. When receiving the extension signal from the cylinder, the cylinder shaft 2 extends out of the cylinder 2 and connects with the connecting hole of the shaft connector 5.

[0089] Furthermore, the cylinder 1 and the cylinder 2 are axially aligned and arranged axially at the position where the wingtip of the aircraft has the largest thickness; and longitudinally arranged at the middle position of the wingtip of the aircraft;

[0090] Furthermore, the axial length of the cylinder 1, the axial length of the cylinder 2, and the axial

[0091] The ratio of the intervals is 1:1:1;

[0092] The ratio of the axial spacing between the first and second cylinders to the axial length of the shaft connecting member is 1:1;

[0093] Exemplarily, the ratio between the axial length of the cylinder 1 and the rib chord of the aircraft wing tip is 1-2:20;

[0094] The ratio between the axial length of the second cylinder and the rib chord of the wingtip of the aircraft wing is 1-2:20;

[0095] The ratio between the axial spacing between the cylinder 1 and the cylinder 2 and the rib chord of the aircraft wing tip is 1-2:20;

[0096] In the technical solution of the present invention, the length of the two cylinders is 5% to 10% of the wingtip chord line, and the spacing between the two cylinders is 5% to 10% of the wingtip chord line, which is beneficial for the aircraft wing to present an optimal load-bearing state, ensure the stability of the flight state, and ensure that the connecting device has rotational freedom.

[0097] Furthermore, the ratio of the stroke of the cylinders 1 and 2 to the axial length of the cylinders 1 and 2 is 12:5-10;

[0098] The cylinder-based aircraft aerial docking / separation device is applicable to aircraft wing airfoils with a wing rib chord length of ≥200 mm.

[0099] Specifically, the axial length of the cylinders 1 and 2 is 5-10 mm;

[0100] The wingtip connection device in the technical solution of the present invention is small in size and quick in response.

[0101] In one embodiment of the present invention, when the wingtips of aircraft one and aircraft two reach a certain horizontal distance, the main systems of aircraft one and aircraft two send a docking signal, and the cylinder one 6 and boss one 61 in the wing rib of aircraft one dock into the groove two 2 until there is no gap at the docking; the cylinder two 7 and boss two 71 dock into the groove three 3 until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into the cylinder one and cylinder two, so that the cylinder shaft one and cylinder shaft two enter the shaft connector 5, forming a connection;

[0102] In one embodiment of the present invention, when the wingtips of aircraft 1 and aircraft 2 are in a docked state, the main systems of aircraft 1 and aircraft 2 send a separation signal, the solenoid valve stops injecting air, and after the injection stops, the cylinder 1 and cylinder 2 are deflated, and the cylinder shaft 1 and cylinder shaft 2 both leave the shaft connector 5, completing the separation of the wingtips of aircraft 1 and aircraft 2.

[0103] Furthermore, the material of the connecting plate 1 and the connecting plate 2 is aluminum alloy.

[0104] The connecting plate of the present invention is made of aluminum alloy plate, which has medium strength, good fatigue resistance and damage resistance, and also takes into account corrosion resistance. It is beneficial to improve the reliability, service life, safety and maintainability of the main structure of the aircraft body and other damage resistance. It has high fracture toughness, fatigue resistance and low fatigue crack growth rate.

[0105] Another object of the present invention is to provide a method for using a cylinder-based device for docking / separating an aircraft in mid-air, comprising:

[0106] The two aircraft, one on the left and one on the right, maintain a certain distance and fly level at the same height and front-to-back position, reducing the distance between the wings of the two aircraft until the wingtips of aircraft one and aircraft two reach a certain horizontal distance. The main systems of aircraft one and aircraft two send docking signals, and the cylinder one 6 and boss one 61 in the wing rib of aircraft one dock into the groove two 2 until there is no gap at the docking; the cylinder two 7 and boss two 71 dock into the groove three 3 until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into cylinder one and cylinder two, causing the cylinder shaft one and cylinder shaft two to enter the shaft connector 5 to form a connection;

[0107] In one embodiment of the present invention, when the wingtips of aircraft 1 and aircraft 2 are in a docked state, the main systems of aircraft 1 and aircraft 2 send a separation signal, the solenoid valve stops injecting air, and after the injection stops, the cylinder 1 and cylinder 2 are deflated, and the cylinder shaft 1 and cylinder shaft 2 both leave the shaft connector 5, completing the separation of the wingtips of aircraft 1 and aircraft 2.

[0108] Preferably, the chord length of the connecting plates 1 and 2 is 300 mm;

[0109] The axes of the cylinder 1 and the cylinder 2 are kept consistent so that the mechanism retains a relative roll angle of ±45°.

[0110] Furthermore, the axial length of the cylinder 1, the axial length of the cylinder 2, and the axial

[0111] The ratio of the intervals is 1:1:1;

[0112] Exemplarily, the ratio between the axial length of the cylinder 1 and the rib chord of the aircraft wing tip is 1-2:20;

[0113] The ratio between the axial length of the second cylinder and the rib chord of the wingtip of the aircraft wing is 1-2:20;

[0114] The ratio between the axial spacing between the cylinder 1 and the cylinder 2 and the rib chord of the aircraft wing tip is 1-2:20;

[0115] In the technical solution of the present invention, the length of the two cylinders is 5% to 10% of the wingtip chord line, and the spacing between the two cylinders is 5% to 10% of the wingtip chord line, which is beneficial for the aircraft wing to present an optimal load-bearing state, ensure the stability of the flight state, and ensure that the connecting device has rotational freedom.

[0116] Going further,

[0117] The cylinder-based aircraft aerial docking / separation device is applicable to aircraft wing airfoils with a wing rib chord length of ≥200 mm.

[0118] Specifically, the axial length of the cylinders 1 and 2 is 5-10 mm;

[0119] Example 1

[0120] A device for docking / separating multiple aircraft in mid-air, comprising a first connecting plate 11, a second connecting plate 12, a cylinder assembly, and a groove assembly; the groove assembly is disposed on the first connecting plate 11 for docking with the cylinder assembly; the cylinder assembly is disposed on the second connecting plate 12; the second connecting plate 12 is screwed to the wingtip rib of the left wing of the aircraft via multiple bolts, and the second connecting plate 11 is screwed to the wingtip rib of the right wing of the aircraft via multiple bolts;

[0121] The shapes of the connecting plates 1 and 2 are consistent with the shape of the wingtip of the NACA3315 airfoil, with a chord length of 300 mm and made of aluminum alloy, which can ensure sufficient strength while being relatively light in weight;

[0122] The connecting plate 12 includes: groove 1 1, groove 2 2 and groove 3;

[0123] The cylinder assembly includes a cylinder 1 6 and a cylinder 2 7; the cylinder 1 includes a cylinder shaft 1 9, and the cylinder 2 includes a cylinder shaft 2 8;

[0124] The cylinder 1 6 is arranged on the connecting plate 1 through the boss 1, and the cylinder 2 7 is arranged on the connecting plate 1 through the boss 2;

[0125] The groove 1 and the groove 3 are respectively arranged on both sides of the groove 2;

[0126] The shape of the groove 2 matches the boss 1 61 on which the cylinder 1 is provided. During the wingtip docking of two aircraft, the cylinder 1 6 and the boss 1 61 dock with the groove 2;

[0127] The shape of the groove 3 matches the boss 2 71 on which the cylinder 2 7 is provided. During the wingtip docking of two aircraft, the cylinder 2 7 and the boss 2 71 are docked with the groove 3 3. Furthermore, the cylinder 1 and the cylinder 2 are connected to the solenoid valve via the pipe 10 and the pipe 2, respectively. The solenoid valve is connected to the main system of the aircraft.

[0128] The pipe 10 passes through the connecting plate 2 and is connected to the cylinder 1; the pipe 2 passes through the connecting plate 2 and is connected to the cylinder 2;

[0129] Furthermore, the cylinder assembly further includes a cylinder shaft 1 9 and a cylinder shaft 2 8;

[0130] The cylinder shaft 1 9 is arranged on the inner side of the cylinder 1 6; the cylinder shaft 2 8 is arranged on the inner side of the cylinder 1 7; the cylinder shaft 1 9 and the cylinder shaft 2 8 are opposite to each other and are both used to fix the groove 2 2;

[0131] The cylinder shaft 1 9 has a telescopic function. When the wingtips of the aircraft are not docked, the cylinder shaft 1 is retracted in the cylinder 1. When receiving the extension signal from the cylinder, the cylinder shaft 1 extends out of the cylinder 1 and connects with the groove 2 2.

[0132] The cylinder shaft 2 has a telescopic function. When the wingtip of the aircraft is not docked, the cylinder shaft 2 is retracted in the cylinder 2. When receiving the extension signal from the cylinder, the cylinder shaft 2 extends out of the cylinder 2 and connects with the groove 2. Furthermore, the connecting plate 11 also includes a shaft connector 5, a connector 1 4 and a connector 2 13.

[0133] Exemplarily, the shaft connecting member 5 is arranged between the groove 2 and the groove 3; a connecting hole is provided in the shaft connecting member 5 for clamping the cylinder shaft 1 and the cylinder shaft 2;

[0134] The two ends of the connecting member 1 4 are respectively connected to the groove 1 and the groove 2;

[0135] The second connecting member 13 is connected to one side of the third groove;

[0136] The groove three is provided between the shaft connecting member 5 and the connecting member 2 13; Figure 1 ;

[0137] Furthermore, the cylinder 1 and the cylinder 2 are axially aligned and arranged axially at the position where the thickness of the aircraft wing tip is the largest; and longitudinally arranged at the middle position of the aircraft wing tip; Figure 1 .

[0138] Example 2

[0139] A method for using a device for mid-air docking / separation of multiple aircraft, comprising:

[0140] The two aircraft, one on the left and one on the right, maintain a certain distance and fly level at the same height and front-to-back position, reducing the distance between the wings of the two aircraft until the wingtips of aircraft one and aircraft two reach a certain horizontal distance. The main systems of aircraft one and aircraft two send docking signals, and the cylinder one 6 and boss one 61 in the wing rib of aircraft one dock into the groove two 2 until there is no gap at the docking; the cylinder two 7 and boss two 71 dock into the groove three 3 until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into cylinder one and cylinder two, causing the cylinder shaft one and cylinder shaft two to enter the shaft connector 5 to form a connection;

[0141] In one embodiment of the present invention, when the wingtips of aircraft 1 and aircraft 2 are in a docked state, the main systems of aircraft 1 and aircraft 2 send a separation signal, the solenoid valve stops injecting air, and after the injection stops, the cylinder 1 and cylinder 2 are deflated, and the cylinder shaft 1 and cylinder shaft 2 both leave the shaft connector 5, completing the separation of the wingtips of aircraft 1 and aircraft 2.

[0142] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

Claims

1. A device for docking / separating an aircraft in the air based on a cylinder, characterized in that: include: Connecting plate one (11), connecting plate two (12), a cylinder assembly and a groove assembly; the groove assembly is arranged on the connecting plate one (11); the cylinder assembly is arranged on the connecting plate two (12); The groove assembly includes: groove two (2) and groove three (3); The cylinder assembly includes cylinder 1 (6) and cylinder 2 (7); cylinder 1 and cylinder 2 are connected to the solenoid valve through pipeline 1 (10) and pipeline 2 respectively; The cylinder 1 is connected to the groove 2, and the cylinder 2 is connected to the groove 3; The cylinder assembly further includes a boss 1 (61) and a boss 2 (71); The cylinder 1 (6) is axially arranged on the connecting plate 2 (12) through the boss 1 (61), and the cylinder 2 (7) is axially arranged on the connecting plate 2 (12) through the boss 2 (71); The cylinder 1 (6) is connected to the boss 1 (61); the cylinder 1 is connected to the groove 2 (2); the cylinder 2 (7) is arranged behind the boss 2 (71) and connected to the groove 3 (3); The cylinder assembly also includes a cylinder shaft 1 (9) and a cylinder shaft 2 (8); The cylinder shaft 1 (9) is arranged on the inner side of the cylinder 1 (6); the cylinder shaft 2 (8) is arranged on the inner side of the cylinder 2 (7); The connecting plate 1 (11) further includes a shaft connecting member (5); The shaft connecting member (5) is arranged between the second groove (2) and the third groove (3); connecting holes are arranged in the shaft connecting member (5), both of which are used to fix the first cylinder shaft and the second cylinder shaft.

2. The device for docking / separating an aircraft in the air based on a cylinder according to claim 1, characterized in that: The groove assembly comprises: groove one (1); The connecting plate 1 (11) further comprises a connecting piece 1 (4) and a connecting piece 2 (13); groove 1 (1) and groove 2 (2) are respectively provided at both ends of the connecting piece 1 (4); The second connecting member (13) is connected to the third groove.

3. The device for docking / separating an aircraft in the air based on a cylinder according to claim 1, characterized in that: The ratio of the axial length of the first cylinder, the axial length of the second cylinder, and the axial length of the shaft connecting member (5) is 1:1:

1.

4. The device for docking / separating an aircraft in the air based on a cylinder according to claim 1, characterized in that: The ratio between the axial length of the cylinder 1 and the rib chord of the aircraft wing tip is 1-2:

20.

5. The device for docking / separating an aircraft in the air based on a cylinder according to claim 1, characterized in that: The cylinder-based aircraft aerial docking / separation device is applicable to aircraft wing airfoils with a rib chord length of ≥200 mm.

6. The method for using the cylinder-based aircraft aerial docking / separation device according to any one of claims 1 to 5, characterized in that include: The two aircrafts, one on the left and one on the right, maintain a certain distance, and the wingtips of aircraft one and aircraft two reach a certain horizontal distance. The main systems of aircraft one and aircraft two send docking signals, and the cylinder one (6) and boss one (61) in the wing rib of aircraft one dock into the groove two (2) until there is no gap at the docking; the cylinder two (7) and boss two (71) dock into the groove three (3) until there is no gap at the docking; the solenoid valve receives the air injection control signal and injects air into cylinder one and cylinder two, so that the cylinder shaft one and cylinder shaft two enter the shaft connecting member (5) to form a connection; When the wingtips of aircraft one and aircraft two are in a docked state, the main systems of aircraft one and aircraft two send a separation signal, the solenoid valve stops injecting air, and after the injection of air is stopped, the cylinder one and cylinder two are deflated, and the cylinder shaft one and cylinder shaft two both leave the shaft connector (5), completing the separation of the wingtips of aircraft one and aircraft two.

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