An integrated aircraft nest and aircraft launching method

Abstract

The application discloses an integrated aircraft nest and an aircraft launching method, and relates to the field of aircraft nests.The integrated aircraft nest comprises a storage device, a connecting rod landing gear, a rocket support assembly, a front tilting support assembly and a rear guide rail support assembly; the connecting rod landing gear is rotationally connected to the inside of the storage device; the rocket support assembly, the front tilting support assembly and the rear guide rail support assembly are detachably connected to the storage device; when the aircraft is in a recovery state, the connecting rod landing gear is in a first position and abuts against the aircraft; when the aircraft is in a launching state, the connecting rod landing gear returns to the first position, the rocket support assembly, the front tilting support assembly and the rear guide rail support assembly all abut against the aircraft, and the aircraft is configured to be launched under the action of the rocket support assembly, the front tilting support assembly and the rear guide rail support assembly. The application can integrate the storage, transportation and launching functions of the aircraft, and realizes the centralized and efficient management of the aircraft in a limited space.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an integrated aircraft nest and aircraft launch method. Background Technology

[0002] With the rapid development of drone technology, drones have demonstrated enormous application potential in various fields such as military reconnaissance, target tracking, material delivery, and environmental monitoring. However, in practical applications, the deployment, maintenance, and launch of drones often face numerous challenges. Especially in confined spaces, such as military vehicles, ships, or temporary command centers, how to efficiently and safely manage multiple drones centrally has become an urgent problem to be solved.

[0003] Traditional drone management methods often involve decentralized storage and individual operation, which is not only inefficient but also consumes a significant amount of space. Furthermore, rapid deployment and launch of drones in emergency situations presents a significant technical challenge. Summary of the Invention

[0004] This application provides an integrated aircraft nest and aircraft launch method, which solves the problems of low space utilization, low deployment efficiency and complex launch operation faced by aircraft in the prior art. It can integrate the storage, transportation and launch functions of aircraft into one, and realize centralized and efficient management of aircraft in a limited space.

[0005] In a first aspect, embodiments of this application provide an integrated aircraft nacelle, including a storage device, a linkage landing gear, a rocket support assembly, a front collapsing support assembly, and a rear guide rail support assembly; the linkage landing gear is rotatably connected to the interior of the storage device; the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are all detachably connected to the storage device; when the aircraft is in a recovery state, the linkage landing gear is in a first position and abuts against the aircraft; when the aircraft is in a raised state, the linkage landing gear is in a second position and abuts against the aircraft; when the aircraft is in a launch state, the linkage landing gear returns to the first position, and the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly all abut against the aircraft, and the aircraft is configured to launch under the action of the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly.

[0006] In conjunction with the first aspect, in one possible implementation, the linkage landing gear includes two first links, two second links, and a landing gear fixing frame; the first links and second links are spaced apart along the length of the aircraft; both the two first links and both second links are symmetrically arranged relative to the aircraft; one end of each of the two first links is rotatably connected to the base plate of the storage device, and the other end of each of the two first links is rotatably connected to the landing gear fixing frame; one end of each of the two second links is rotatably connected to the base plate of the storage device; the other end of each of the two second links is rotatably connected to the landing gear fixing frame; the landing gear fixing frame abuts against the aircraft.

[0007] In conjunction with the first aspect, in one possible implementation, the rocket support assembly includes a mounting plate, a first rotating mechanism, a connecting shaft, a first elastic element, a connecting block, and a support platform; the support platform is connected to one end of the mounting plate, and the connecting block is connected to the other end of the mounting plate; the connecting shaft is connected to the support platform; the first rotating mechanism is rotatably connected to the connecting shaft; one end of the first elastic element is connected to the first rotating mechanism, and the other end of the first elastic element is connected to the connecting block; the mounting plate is detachably connected to the storage device.

[0008] In conjunction with the first aspect, in one possible implementation, the first rotating mechanism includes a bushing, a support plate, and a rocket support seat; the bushing is rotatably connected to the connecting shaft; the support plate is fixedly connected to the outside of the bushing; the rocket support seat is connected to the support plate and is configured to abut against the spacecraft; one end of the first elastic member is connected to the support plate, and the other end of the first elastic member is connected to the connecting block.

[0009] In conjunction with the first aspect, in one possible implementation, the forward-falling support assembly includes a falling-down fixing seat, a falling-down fixing frame, a fixed shaft, a second elastic element, a falling-down support seat, and a second rotating mechanism; one end of the falling-down fixing seat is connected to the falling-down fixing frame, and the other end of the falling-down fixing seat is connected to the falling-down support seat; the fixed shaft is connected to the falling-down fixing frame; the second elastic element is sleeved on the fixed shaft; one end of the second elastic element is connected to the second rotating mechanism, and the other end of the second elastic element abuts against the falling-down fixing frame; the first end of the second rotating mechanism is rotatably connected to the fixed shaft, the second end of the second rotating mechanism is connected to the falling-down support seat, and the third end of the second rotating mechanism abuts against the aircraft; the side of the falling-down fixing seat away from the aircraft is detachably connected to the storage device.

[0010] In conjunction with the first aspect, in one possible implementation, the second rotating mechanism includes a front support arm, a first connecting rod, and a mounting base; one end of the front support arm is rotatably connected to the fixed shaft, and the other end of the front support arm abuts against the aircraft; the mounting base is connected to the front support arm; one end of the first connecting rod is rotatably connected to the mounting base, and the other end of the first connecting rod is connected to the collapsing support base; one end of the second elastic element is connected to the front support arm, and the other end of the second elastic element is connected to the collapsing fixing frame.

[0011] In conjunction with the first aspect, in one possible implementation, the rear rail support assembly includes a second connecting rod, two launch rails, and two rear supports; the two launch rails and the two rear supports are symmetrically arranged relative to the aircraft; the two launch rails are respectively connected to one end of the two rear supports, and the other end of the two rear supports is slidably connected to the storage device; both launch rails abut against the aircraft.

[0012] In conjunction with the first aspect, in one possible implementation, the linkage landing gear further includes two extension levers and two gas springs; the gas springs are disposed between the first linkage and the second linkage; the two extension levers and the two gas springs are symmetrically arranged with respect to the aircraft; the two extension levers are connected along the length direction of the landing gear; one end of the two gas springs is rotatably connected to the storage device, and the other end of the two gas springs is rotatably connected to the landing gear.

[0013] In conjunction with the first aspect, in one possible implementation, the storage device includes a housing, a front cover, a top cover, and a tail cover; the linkage landing gear is rotatably connected to the interior of the housing; the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are all detachably connected to the housing; one end of the housing is detachably connected to the front cover, the other end of the housing is detachably connected to the tail cover, and the upper side of the housing is detachably connected to the top cover.

[0014] Secondly, embodiments of this application provide a method for launching an aircraft, which is applicable to the integrated aircraft nest described in the first aspect or any possible implementation of the first aspect, and the steps are as follows: S1: Open the top cover, front cover, and rear cover; S2: Raise the landing gear until the aircraft reaches the predetermined launch angle; S3: Connect the two rear supports to the two launch rails respectively, install the second connecting rod between the two rear supports, install one end of the front collapsing support assembly inside the shell, and fix the rocket support assembly to the second connecting rod; S4: Disconnect the connection between the aircraft and the landing gear, disconnect the connection between the landing gear and the two launch rails, and lower the landing gear. At this time, the aircraft is in contact with both the front collapsing support assembly and the rear rail support assembly. S5: Check the aircraft's attitude and control the aircraft's launch.

[0015] One or more technical solutions provided in this application have at least the following technical effects: This application embodiment employs an integrated aircraft nacelle and aircraft launch method. The integrated aircraft nacelle includes a storage device, a linkage landing gear, a rocket support assembly, a front collapsing support assembly, and a rear guide rail support assembly. The linkage landing gear is rotatably connected to the interior of the storage device. The linkage landing gear assists in the launch of the aircraft. The rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are all detachably connected to the storage device. The rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are used for aircraft launch. When the aircraft is in the recovery state, the linkage landing gear is in the first position and abuts against the aircraft. When the aircraft is in the raised state... When the linkage landing gear is in the second position and in contact with the aircraft, it can raise the aircraft to the launch angle by switching the linkage landing gear from the first position to the second position. When the aircraft is in the launch state, the linkage landing gear returns to the first position, and the rocket support assembly, the forward collapsing support assembly, and the rear guide rail support assembly are all in contact with the aircraft, allowing the aircraft to launch under the action of these components. During launch preparation, the rocket support assembly, the forward collapsing support assembly, and the rear guide rail support assembly are first arranged, then the linkage landing gear is rotated to the first position, and finally the launch operation is performed. This application solves the problems of low space utilization, low deployment efficiency, and complex launch operation faced by aircraft in the prior art, integrating the storage, transportation, and launch functions of the aircraft into one unit, achieving centralized and efficient management of the aircraft within a limited space. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of the recovery status of the integrated aircraft nest provided in the embodiments of this application; Figure 2 A schematic diagram of the recovery status of the integrated aircraft nest provided in the embodiments of this application; Figure 3 A schematic diagram of the raised state of the integrated aircraft nacelle provided in this application embodiment; Figure 4 A schematic diagram of the raised state of the integrated aircraft nacelle provided in this application embodiment; Figure 5 A schematic diagram of the launch status of the integrated aircraft nacelle provided in this application embodiment; Figure 6 An isometric view of a rocket support assembly provided in an embodiment of this application; Figure 7 A front view of a rocket support assembly provided in an embodiment of this application; Figure 8 for Figure 7 AA section view; Figure 9 An isometric view of the front collapse support assembly provided in the embodiments of this application; Figure 10 A front view of the front collapse support assembly provided in an embodiment of this application; Figure 11 for Figure 10 BB section view; Figure 12 An isometric view of the rear guide rail support assembly provided in an embodiment of this application; Figure 13 A flowchart of a flight vehicle launch method provided in an embodiment of this application.

[0018] Icons: 1-Storage device; 11-Shell; 12-Front cover plate; 13-Top cover; 14-Tail cover plate; 2-Linkage landing gear; 21-First link; 22-Second link; 23-Landing and landing frame; 24-Extension lever; 25-Gas spring; 3-Rocket support assembly; 31-Mounting plate; 32-First rotating mechanism; 321-Busset; 322-Support plate; 323-Rocket support seat; 33-Connecting shaft; 34-First elastic element; 35-Connecting block; 36-Support platform; 4-Front collapsing support assembly; 41-Collapsing fixing seat; 42-Fixed shaft; 43-Second elastic element; 44-Collapsing support seat; 45-Second rotating mechanism; 451-Front support arm; 452-First connecting rod; 453-Mounting seat; 46-Collapsing fixing frame; 5-Rear guide rail support assembly; 51-Second connecting rod; 52-Launch guide rail; 53-Rear support. Detailed Implementation

[0019] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0020] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for 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. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0021] This application provides an integrated aircraft nest, such as Figure 1-12 As shown, the system includes a storage device 1, a linkage landing gear 2, a rocket support assembly 3, a front collapsing support assembly 4, and a rear guide rail support assembly 5. The linkage landing gear 2 is rotatably connected to the interior of the storage device 1. The rocket support assembly 3, the front collapsing support assembly 4, and the rear guide rail support assembly 5 are all detachably connected to the storage device 1. When the aircraft is in the recovery state, the linkage landing gear 2 is in the first position and abuts against the aircraft. When the aircraft is in the raised state, the linkage landing gear 2 is in the second position and abuts against the aircraft. When the aircraft is in the launch state, the linkage landing gear 2 returns to the first position, and the rocket support assembly 3, the front collapsing support assembly 4, and the rear guide rail support assembly 5 all abut against the aircraft. The aircraft is configured to launch under the action of the rocket support assembly 3, the front collapsing support assembly 4, and the rear guide rail support assembly 5.

[0022] For example, such as Figure 1-5As shown, the linkage landing gear 2 has a first position and a second position. When the aircraft is in the recovery state, the linkage landing gear 2 is in the first position. At this time, the linkage landing gear 2 is placed at the bottom of the storage device 1, and the aircraft is placed on the linkage landing gear 2. The rocket support assembly 3, the front collapsing support assembly 4, and the rear guide rail support assembly 5 are all placed inside the storage device 1 for use when launching the aircraft.

[0023] For example, multiple aircraft nests can be configured according to this application, each with the functions of individual launch and stacked storage. Multiple aircraft nests are placed on a transport vehicle, and upon arrival at the designated location, a crane can lift a single aircraft nest to the target position and launch the aircraft from within that single nest without requiring an additional power unit. This aircraft nest integrates storage, transportation, and launch functions into one unit, offering advantages such as simple operation, small footprint, and low cost, enabling rapid deployment and efficient use of aircraft.

[0024] For example, during the launch of the aircraft, the rocket support assembly 3 is used for the launch of the aircraft, the front collapsing support assembly 4 is used for the support and launch of the aircraft, and the rear guide rail support assembly 5 is used for the support of the aircraft. The rear guide rail support assembly 5 also has a guiding function for the launch of the aircraft.

[0025] In the embodiments of this application, such as Figure 1-12 As shown, the linkage landing gear 2 includes two first linkages 21, two second linkages 22, and a landing gear 23. The first linkages 21 and second linkages 22 are spaced apart along the length of the aircraft, and both the first linkages 21 and the second linkages 22 are symmetrically arranged relative to the aircraft. One end of each of the two first linkages 21 is rotatably connected to the base plate of the storage device 1, and the other end of each of the two first linkages 21 is rotatably connected to the landing gear 23. One end of each of the two second linkages 22 is rotatably connected to the base plate of the storage device 1, and the other end of each of the two second linkages 22 is rotatably connected to the landing gear 23. The landing gear 23 abuts against the aircraft. For example, it also includes multiple bosses, which are respectively connected to the base plate of the storage device 1. The multiple bosses are rotatably connected to one end of the two first connecting rods 21 and one end of the two second connecting rods 22, and the other ends of the two first connecting rods 21 and the two second connecting rods 22 are rotatably connected to the lifting and fixing frame 23.

[0026] For example, the aircraft is placed on the landing gear 23, which is rectangular. Multiple protrusions are rotatably connected to one end of two first links 21 and one end of two second links 22, respectively. The other ends of the two first links 21 and the other ends of the two second links 22 are rotatably connected to the four corners of the landing gear 23.

[0027] In the embodiments of this application, such as Figure 6-8 As shown, the rocket support assembly 3 includes a mounting plate 31, a first rotating mechanism 32, a connecting shaft 33, a first elastic element 34, a connecting block 35, and a support platform 36; the support platform 36 is connected to one end of the mounting plate 31, and the connecting block 35 is connected to the other end of the mounting plate 31; the connecting shaft 33 is connected to the support platform 36; the first rotating mechanism 32 is rotatably connected to the connecting shaft 33; one end of the first elastic element 34 is connected to the first rotating mechanism 32, and the other end of the first elastic element 34 is connected to the connecting block 35; the mounting plate 31 is detachably connected to the storage device 1.

[0028] For example, the first rotating mechanism 32 can come into contact with the aircraft. During the launch of the aircraft, the force of the aircraft flying forward can cause the first rotating mechanism 32 to rotate around the connecting shaft 33 in the direction of the aircraft's movement. After the launch is completed, the first elastic element 34 can cause the first rotating mechanism 32 to return to its initial state.

[0029] For example, the support platform 36 is provided with an adjustment hole, and the connecting shaft 33 can adjust the distance between itself and the connecting block 35 through the adjustment hole. A first rotating mechanism 32 is rotatably connected to the connecting shaft 33. One end of the first elastic member 34 is connected to the first rotating mechanism 32, and the other end of the first elastic member 34 is connected to the connecting block 35. The position of the first rotating mechanism 32 can be adjusted according to the length and characteristics of the first elastic member 34.

[0030] For example, the rocket support assembly 3 also includes a set screw, which is threaded onto the support platform 36. The end of the set screw abuts against the connecting shaft 33, thereby positioning the connecting shaft 33.

[0031] In the embodiments of this application, such as Figure 6-8 As shown, the first rotating mechanism 32 includes a bushing 321, a support plate 322, and a rocket support seat 323; the bushing 321 is rotatably connected to the connecting shaft 33; the support plate 322 is fixedly connected to the outside of the bushing 321; the rocket support seat 323 is connected to the support plate 322 and is configured to abut against the aircraft; one end of the first elastic member 34 is connected to the support plate 322, and the other end of the first elastic member 34 is connected to the connecting block 35.

[0032] For example, a support plate 322 is fixedly connected to the outer side of the bushing 321. A rocket support seat 323 is connected to the side of the support plate 322 away from the mounting plate 31. The rocket support seat 323 can abut against the aircraft. During the launch of the aircraft, the forward flight force of the aircraft can cause the bushing 321 to drive the support plate 322 and the rocket support seat 323 to rotate around the connecting shaft 33 in the direction of the aircraft's movement. After the launch is completed, the first elastic element 34 can return the support plate 322 and the rocket support seat 323 to their initial state.

[0033] In the embodiments of this application, such as Figure 9-11 As shown, the front collapse support assembly 4 includes a collapse fixing seat 41, a collapse fixing frame 46, a fixing shaft 42, a second elastic element 43, a collapse support seat 44, and a second rotation mechanism 45. One end of the collapse fixing seat 41 is connected to the collapse fixing frame 46, and the other end of the collapse fixing seat 41 is connected to the collapse support seat 44. The fixing shaft 42 is connected to the collapse fixing frame 46. The second elastic element 43 is sleeved on the fixing shaft 42. One end of the second elastic element 43 is connected to the second rotation mechanism 45, and the other end of the second elastic element 43 abuts against the collapse fixing frame 46. The first end of the second rotation mechanism 45 is rotatably connected to the fixing shaft 42, the second end of the second rotation mechanism 45 is connected to the collapse support seat 44, and the third end of the second rotation mechanism 45 abuts against the aircraft. The side of the collapse fixing seat 41 away from the aircraft is detachably connected to the storage device 1.

[0034] For example, during the launch of the aircraft, the force of the aircraft flying forward can cause the second rotating mechanism 45 to rotate around the fixed axis 42 in the direction of the aircraft's movement. After the launch is completed, the second elastic element 43 can cause the second rotating mechanism 45 to return to its initial state.

[0035] In the embodiments of this application, such as Figure 9-11 As shown, the second rotating mechanism 45 includes a front support arm 451, a first connecting rod 452, and a mounting base 453; one end of the front support arm 451 is rotatably connected to the fixed shaft 42, and the other end of the front support arm 451 abuts against the aircraft; the mounting base 453 is connected to the front support arm 451; one end of the first connecting rod 452 is rotatably connected to the mounting base 453, and the other end of the first connecting rod 452 is connected to the collapsing support base 44; one end of the second elastic member 43 is connected to the front support arm 451, and the other end of the second elastic member 43 is connected to the collapsing fixing frame 46.

[0036] For example, during the launch of the aircraft, the force of the aircraft flying forward can cause the front support arm 451 to rotate around the fixed axis 42 in the direction of the aircraft's movement. After the launch is completed, the second elastic element 43 can cause the front support arm 451 to return to its initial state.

[0037] For example, the second elastic element 43 is a torsion spring. The second elastic element 43 is sleeved on the fixed shaft 42. One end of the second elastic element 43 is connected to the front support arm 451, and the other end of the second elastic element 43 abuts against the inverted fixing frame 46. The second elastic element 43 can open or compress in the radial direction of the fixed shaft 42, thereby achieving the technical effect of returning the front support arm 451 to its initial state after the aircraft is launched.

[0038] In the embodiments of this application, such as Figure 12As shown, the rear rail support assembly 5 includes a second connecting rod 51, two launch rails 52 and two rear supports 53; the two launch rails 52 and the two rear supports 53 are symmetrically arranged relative to the aircraft; the two launch rails 52 are respectively connected to one end of the two rear supports 53, and the other end of the two rear supports 53 is slidably connected to the storage device 1; the two launch rails 52 are in contact with the aircraft.

[0039] For example, the aircraft can slide on two launch rails 52, which guide the launch of the aircraft during the launch process.

[0040] For example, the rear support 53 includes a connecting part, a supporting part, and a mounting part; the two ends of the supporting part are respectively connected to the connecting part and the mounting part, and a sliding groove is provided on the connecting part. The connecting part is slidably connected to the storage device 1 through the sliding groove. The angle between the sliding groove and the supporting part is less than 90°, so that the rear support 53 is tilted after being connected to the storage device 1, thereby achieving the purpose of adjusting the aircraft to a predetermined launch angle; the mounting part is detachably connected to the launch rail 52. When the aircraft is in the recovery or lifting state, the launch rail 52 is connected to the landing gear 23. At this time, the launch rail 52 is detached from the supporting part; when the aircraft is in the launch state, the launch rail 52 is connected to the supporting part. At this time, the launch rail 52 is detached from the landing gear 23.

[0041] In the embodiments of this application, such as Figure 1-5 As shown, the linkage landing gear 2 also includes two extension levers 24 and two gas springs 25; the gas springs 25 are disposed between the first linkage 21 and the second linkage 22; the two extension levers 24 and the two gas springs 25 are symmetrically arranged with respect to the aircraft; the two extension levers 24 are connected to the landing gear 23 along its length; one end of the two gas springs 25 is rotatably connected to the storage device 1, and the other end of the two gas springs 25 is rotatably connected to the landing gear 23.

[0042] For example, the two extension levers 24 have a supporting and guiding function. When the aircraft is in the raised state, the gas spring 25 has a supporting and locking function. After the linkage landing gear 2 is manually raised to the second position, the linkage landing gear 2 has a downward movement tendency under the action of the aircraft's gravity. The gas spring 25 can lock the linkage landing gear 2 in the second position to prevent safety accidents from occurring.

[0043] In the embodiments of this application, such as Figure 1As shown, the storage device 1 includes a housing 11, a front cover 12, a top cover 13, and a tail cover 14; the linkage landing gear 2 is rotatably connected to the inside of the housing 11; the rocket support assembly 3, the front collapsing support assembly 4, and the rear guide rail support assembly 5 are all detachably connected to the housing 11; one end of the housing 11 is detachably connected to the front cover 12, the other end of the housing 11 is detachably connected to the tail cover 14, and the upper side of the housing 11 is detachably connected to the top cover 13.

[0044] For example, the housing 11 can be connected to the front cover 12, the housing 11 to the top cover 13, and the housing 11 to the tail cover 14 by means of snap fasteners. When the aircraft is launched, the snap fasteners are first released to remove the front cover 12, the top cover 13 and the tail cover 14 before proceeding with the subsequent operations.

[0045] This application provides a method for launching an aircraft, such as... Figure 13 As shown, the aircraft launch method is applicable to integrated aircraft nests, and its steps are as follows: S1: Open the top cover 13, front cover 12 and rear cover 14; S2: Raise the landing gear 23 until the aircraft reaches the predetermined launch angle; S3: Connect the two rear supports 53 to the two launch rails 52 respectively, install the second connecting rod 51 between the two rear supports 53, install one end of the front collapsing support assembly 4 inside the housing 11, and fix the rocket support assembly 3 to the second connecting rod 51. S4: Disconnect the connection between the aircraft and the landing gear 23, disconnect the connection between the landing gear 23 and the two launch rails 52, and lower the landing gear 23. At this time, the aircraft is in contact with the front collapsing support assembly 4 and the rear rail support assembly 5. S5: Check the aircraft's attitude and control the aircraft's launch.

[0046] This application enables the safe launch of an aircraft from a nest through the aforementioned steps. The coordinated operation of each component ensures the stability and safety of the aircraft during launch, while also improving the convenience and efficiency of operation.

[0047] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0048] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. An integrated aircraft nest, characterized in that, It includes a storage device, a linkage landing gear, a rocket support assembly, a front collapsing support assembly, and a rear guide rail support assembly. The linkage landing gear is rotatably connected to the interior of the storage device. The rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are all detachably connected to the storage device. The rocket support assembly includes a mounting plate, a first rotating mechanism, a connecting shaft, a first elastic element, a connecting block, and a support platform. The support platform is connected to one end of the mounting plate, the connecting block is connected to the other end of the mounting plate, the connecting shaft is connected to the support platform, the first rotating mechanism is rotatably connected to the connecting shaft, one end of the first elastic element is connected to the first rotating mechanism, and the other end of the first elastic element is connected to the connecting block. The mounting plate is detachably connected to the storage device. During the launch of the aircraft, the force of the aircraft's forward flight can cause the first rotating mechanism to rotate around the connecting shaft in the direction of the aircraft's movement. After the launch is completed, the first elastic element can cause the first rotating mechanism to return to its initial state. The forward-falling support assembly includes a falling-off fixing seat, a falling-off fixing frame, a fixed shaft, a second elastic element, a falling-off support seat, and a second rotating mechanism. One end of the falling-off fixing seat is connected to the falling-off fixing frame, and the other end of the falling-off fixing seat is connected to the falling-off support seat. The fixed shaft is connected to the falling-off fixing frame. The second elastic element is sleeved on the fixed shaft. One end of the second elastic element is connected to the second rotating mechanism, and the other end of the second elastic element abuts against the falling-off fixing frame. The first end of the second rotating mechanism is rotatably connected to the fixed shaft, the second end of the second rotating mechanism is connected to the falling-off support seat, and the third end of the second rotating mechanism abuts against the aircraft. The side of the falling-off fixing seat away from the aircraft is detachably connected to the storage device. During the launch of the aircraft, the forward force of the aircraft can cause the second rotating mechanism to rotate around the fixed axis in the direction of the aircraft's movement. After the launch is completed, the second elastic element can cause the second rotating mechanism to return to its initial state. When the aircraft is in the recovery state, the linkage landing gear is in the first position and abuts against the aircraft; when the aircraft is in the raised state, the linkage landing gear is in the second position and abuts against the aircraft; when the aircraft is in the launch state, the linkage landing gear returns to the first position, and the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly all abut against the aircraft, and the aircraft is configured to launch under the action of the rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly.

2. The integrated aircraft nest according to claim 1, characterized in that, The linkage landing gear includes two first linkages, two second linkages, and a landing gear fixing frame; The first link and the second link are spaced apart along the length of the aircraft; The two first links and the two second links are symmetrically arranged with respect to the aircraft. One end of each of the two first connecting rods is rotatably connected to the base plate of the storage device, and the other end of each of the two first connecting rods is rotatably connected to the landing and fixing frame. One end of each of the two second links is rotatably connected to the base plate of the storage device; the other end of each of the two second links is rotatably connected to the landing and fixing frame. The landing gear abuts against the aircraft.

3. The integrated aircraft nest according to claim 1, characterized in that, The first rotating mechanism includes a bushing, a support plate, and a rocket support base; The bushing is rotatably connected to the connecting shaft; The support plate is fixedly connected to the outside of the bushing; The rocket support is connected to the support plate, and the rocket support is configured to abut against the spacecraft. One end of the first elastic element is connected to the support plate, and the other end of the first elastic element is connected to the connecting block.

4. The integrated aircraft nest according to claim 1, characterized in that, The second rotating mechanism includes a front support arm, a first connecting rod, and a mounting base; One end of the front support arm is rotatably connected to the fixed shaft, and the other end of the front support arm abuts against the aircraft; The mounting base is connected to the front support arm; One end of the first connecting rod is rotatably connected to the mounting base, and the other end of the first connecting rod is connected to the overturned support base; One end of the second elastic element is connected to the front support arm, and the other end of the second elastic element is connected to the tilting fixing frame.

5. The integrated aircraft nest according to claim 1, characterized in that, The rear guide rail support assembly includes a second connecting rod, two launch rails, and two rear supports; Both launch rails and both rear supports are symmetrically arranged relative to the aircraft; The two launch rails are respectively connected to one end of the two rear supports, and the other end of the two rear supports is slidably connected to the storage device; Both launch rails are in contact with the aircraft.

6. The integrated aircraft nest according to claim 2, characterized in that, The linkage landing gear also includes two extension levers and two gas springs; The gas spring is disposed between the first connecting rod and the second connecting rod; Both of the aforementioned extension levers and both of the aforementioned gas springs are symmetrically arranged relative to the aircraft; The two extension levers are connected along the length of the landing gear; One end of each of the two gas springs is rotatably connected to the storage device, and the other end of each of the two gas springs is rotatably connected to the landing frame.

7. The integrated aircraft nest according to claim 1, characterized in that, The storage device includes a housing, a front cover, a top cover, and a rear cover; The linkage landing gear is rotatably connected to the interior of the housing; The rocket support assembly, the front collapsing support assembly, and the rear guide rail support assembly are all detachably connected to the housing; One end of the housing is detachably connected to the front cover plate, the other end of the housing is detachably connected to the rear cover plate, and the upper side of the housing is detachably connected to the top cover.

8. A method for launching an aircraft, characterized in that, The aircraft launch method is applicable to the integrated aircraft nest as described in any one of claims 1-7, and its steps are as follows: S1: Open the top cover, front cover, and rear cover; S2: Raise the landing gear until the aircraft reaches the predetermined launch angle; S3: Connect the two rear supports to the two launch rails respectively, install the second connecting rod between the two rear supports, install one end of the front collapsing support assembly inside the shell, and fix the rocket support assembly to the second connecting rod; S4: Disconnect the connection between the aircraft and the landing gear, disconnect the connection between the landing gear and the two launch rails, and lower the landing gear. At this time, the aircraft is in contact with both the front collapsing support assembly and the rear rail support assembly. S5: Check the aircraft's attitude and control the aircraft's launch.

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