Integrated aircraft nest and aircraft launching method

Abstract

The invention discloses an integrated aircraft nest and an aircraft launching method. The integrated aircraft nest comprises a storage device, a link landing gear, a rocket supporting assembly, a front lodging supporting assembly and a rear guide rail supporting assembly. The connecting rod undercarriage is rotationally connected to the interior of the storage device; the rocket supporting assembly, the front lodging supporting assembly and the rear guide rail supporting assembly are all detachably connected with the storage device. When the aircraft is in the recovery state, the connecting rod landing gear is located at the first position and abuts against the aircraft; when the aircraft is in a launching state, the link landing gear returns to the first position, the rocket supporting assembly, the front lodging supporting assembly and the rear guide rail supporting assembly abut against the aircraft, and the aircraft is configured to be launched under the action of the rocket supporting assembly, the front lodging supporting assembly and the rear guide rail supporting assembly. The storage, transportation and launching functions of the aircraft can be integrated, and centralized and efficient management of the aircraft in a limited space is achieved.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an integrated aircraft nest and an aircraft launching method. Background Art

[0002] With the rapid development of drone technology, drones have shown great application potential in many 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 many challenges. Especially in limited spaces, such as military vehicles, ships, or temporary command centers, how to efficiently and safely centrally manage multiple drones has become an urgent problem to be solved.

[0003] Traditional drone management methods often adopt decentralized storage and one-by-one operation, which is not only inefficient but also takes up a lot of space resources. At the same time, in an emergency, rapid deployment and launch of drones has also become a technical challenge. Summary of the invention

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

[0005] In the first aspect, an embodiment of the present application provides an integrated aircraft nest, comprising a storage device, a connecting rod landing gear, a rocket support assembly, a front lodging support assembly and a rear guide rail support assembly; the connecting rod landing gear is rotatably connected to the interior of the storage device; the rocket support assembly, the front lodging 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 connecting rod landing gear is in a first position and abuts against the aircraft; when the aircraft is in a lifted state, the connecting rod landing gear is in a second 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 lodging support assembly and the rear guide rail support assembly are all abutted against the aircraft, and the aircraft is configured to be launched under the action of the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly.

[0006] In combination with the first aspect, in a possible implementation, the link landing gear includes two first links, two second links and a landing gear; the first links and the second links are spaced apart in the length direction of the aircraft; the two first links and the two second links are symmetrically arranged relative to the aircraft; one end of the two first links is rotatably connected to the bottom plate of the storage device, and the other end of the two first links is rotatably connected to the landing gear; one end of the two second links is rotatably connected to the bottom plate of the storage device; the other end of the two second links is rotatably connected to the landing gear; and the landing gear abuts against the aircraft.

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

[0008] In combination with the first aspect, in a 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 outer side of the bushing; the rocket support seat is connected to the support plate, and the rocket support seat is configured to abut the aircraft; 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 combination with the first aspect, in a possible implementation, the front fallback support assembly includes a fallback fixing seat, a fallback fixing frame, a fixed shaft, a second elastic member, a fallback support seat and a second rotating mechanism; one end of the fallback fixing seat is connected to the fallback fixing frame, and the other end of the fallback fixing seat is connected to the fallback support seat; the fixed shaft is connected to the fallback fixing frame; the second elastic member is sleeved on the fixed shaft; one end of the second elastic member is connected to the second rotating mechanism, and the other end of the second elastic member abuts against the fallback 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 fallback support seat, and the third end of the second rotating mechanism abuts against the aircraft; the fallback fixing seat is detachably connected to the storage device on the side away from the aircraft.

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

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

[0012] In combination with the first aspect, in a possible implementation, the link landing gear also includes two extension levers and two gas springs; the gas spring is arranged between the first link and the second link; the two extension levers and the two gas springs are symmetrically arranged relative to the aircraft; the two extension levers are connected in the length direction of the landing frame; 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 frame.

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

[0014] In a second aspect, an embodiment of the present application provides an aircraft launching method, 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 frame until the aircraft reaches the predetermined launch angle; S3: Connect the two rear supports to the two launch rails respectively, install a second connecting rod between the two rear supports, install one end of the front fall support assembly in the housing, and fix the rocket support assembly to the second connecting rod; S4: removing the connection between the aircraft and the landing frame, removing the connection between the landing frame and the two launch rails, and lowering the landing frame. At this time, the aircraft is in contact with both the front lodging support assembly and the rear guide rail support assembly. S5: Check the attitude of the aircraft and control the aircraft to launch.

[0015] One or more technical solutions provided by this application have at least the following technical effects: The embodiment of the present application adopts an integrated aircraft nest and an aircraft launching method, wherein the integrated aircraft nest includes a storage device, a connecting rod landing gear, a rocket support assembly, a front lodging support assembly and a rear guide rail support assembly; the connecting rod landing gear is rotatably connected to the interior of the storage device; the connecting rod landing gear is used to assist in the launch of the aircraft, and the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly are all detachably connected to the storage device; the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly are used for launching the aircraft; 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 raised state When the connecting rod landing gear is in the second position, it is in contact with the aircraft; by converting the connecting rod landing gear from the first position to the second position, the aircraft can be lifted to the launch angle; when the aircraft is in the launch state, the connecting rod landing gear returns to the first position, and the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly are all in contact with the aircraft, and the aircraft can be launched under the action of the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly; when the aircraft is preparing for launch, the rocket support assembly, the front lodging support assembly and the rear guide rail support assembly are first arranged, and then the connecting rod landing gear is rotated to the first position, and finally the aircraft is launched. The present application solves the problems of low space utilization, low deployment efficiency and complex launch operation faced by aircraft in the prior art, and can integrate the storage, transportation and launch functions of the aircraft into one, realizing centralized and efficient management of the aircraft in a limited space. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the description of the embodiments of the present application will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 A schematic diagram of the recovery state of the integrated aircraft nest provided in an embodiment of the present application; Figure 2 A schematic diagram of the recovery state of the integrated aircraft nest provided in an embodiment of the present application; Figure 3 A schematic diagram of the lifted state of the integrated aircraft nest provided in an embodiment of the present application; Figure 4 A schematic diagram of the lifted state of the integrated aircraft nest provided in an embodiment of the present application; Figure 5 A schematic diagram of the launch state of the integrated aircraft nest provided in an embodiment of the present application; Figure 6 An axonometric view of a rocket support assembly provided for an embodiment of the present application; Figure 7 A front view of a rocket support assembly provided in an embodiment of the present application; Figure 8 for Figure 7 AA section view; Fig. 9 An axonometric view of a front lodging support assembly provided in an embodiment of the present application; Fig.10 A front view of a front lodging support assembly provided in an embodiment of the present application; Fig.11 for Fig.10 BB cross-sectional view; Fig.12 An axonometric view of a rear rail support assembly provided in an embodiment of the present application; Fig.13 A flowchart of an aircraft launching method provided in an embodiment of the present application.

[0018] Icons: 1-storage device; 11-shell; 12-front cover; 13-top cover; 14-tail cover; 2-link landing gear; 21-first link; 22-second link; 23-landing bracket; 24-extension lever; 25-gas spring; 3-rocket support assembly; 31-mounting plate; 32-first rotating mechanism; 321-bushing; 322-support plate; 323-rocket support seat; 33-connecting shaft; 34-first elastic member; 35-connecting block; 36-support platform; 4-front inversion support assembly; 41-inversion fixing seat; 42-fixed shaft; 43-second elastic member; 44-inversion support seat; 45-second rotating mechanism; 451-front support arm; 452-first connecting rod; 453-mounting seat; 46-inversion fixing bracket; 5-rear guide rail support assembly; 51-second connecting rod; 52-launch guide rail; 53-rear support. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0020] In the description of the embodiments of the present application, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limitations on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0021] The present application embodiment provides an integrated aircraft nest, such as Figure 1-12 As shown, it includes a storage device 1, a connecting rod landing gear 2, a rocket support assembly 3, a front lodging support assembly 4 and a rear guide rail support assembly 5; the connecting rod landing gear 2 is rotatably connected to the inside of the storage device 1; the rocket support assembly 3, the front lodging 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 a recovery state, the connecting rod landing gear 2 is in a first position and abuts against the aircraft; when the aircraft is in a lifted state, the connecting rod landing gear 2 is in a second position and abuts against the aircraft; when the aircraft is in a launching state, the connecting rod landing gear 2 returns to the first position, the rocket support assembly 3, the front lodging support assembly 4 and the rear guide rail support assembly 5 are all abutted against the aircraft, and the aircraft is configured to be launched under the action of the rocket support assembly 3, the front lodging support assembly 4 and the rear guide rail support assembly 5.

[0022] For example, Figure 1-5As shown, the link landing gear 2 has a first position and a second position. When the aircraft is in a recovery state, the link landing gear 2 is in the first position. At this time, the link landing gear 2 is placed at the bottom of the storage device 1, and the aircraft is placed on the link landing gear 2; the rocket support assembly 3, the front lodging 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] Exemplarily, the aircraft nest of the present application can be provided with multiple aircraft nests, which have the functions of single launch and stacked storage. Multiple aircraft nests are placed on a transport vehicle. After arriving at a designated location, a crane can lift a single aircraft nest to a target location, and can launch an aircraft in a single aircraft nest without the need for an additional power device. The aircraft nest integrates the functions of storage, transportation and launch, and has the advantages of simple operation, small footprint and low cost, realizing rapid deployment and efficient use of aircraft.

[0024] Illustratively, during the launch of the aircraft, the rocket support assembly 3 is used for launching the aircraft, the front fall support assembly 4 is used for supporting and launching the aircraft, and the rear guide rail support assembly 5 is used for supporting the aircraft. The rear guide rail support assembly 5 also has a guiding effect on the launch of the aircraft.

[0025] In the present application embodiment, Figure 1-12 As shown, the link landing gear 2 includes two first links 21, two second links 22 and a landing frame 23; the first links 21 and the second links 22 are arranged at intervals in the length direction of the aircraft, and the two first links 21 and the two second links 22 are symmetrically arranged relative to the aircraft; one end of the two first links 21 is rotatably connected to the bottom plate of the storage device 1, and the other end of the two first links 21 is rotatably connected to the landing frame 23; one end of the two second links 22 is rotatably connected to the bottom plate of the storage device 1; the other end of the two second links 22 is rotatably connected to the landing frame 23; the landing frame 23 abuts against the aircraft; Exemplarily, it also includes multiple bosses, which are respectively connected to the bottom plate of the storage device 1, and the multiple bosses are respectively 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 end of the two first connecting rods 21 and the other end of the two second connecting rods 22 are rotatably connected to the landing frame 23.

[0026] Exemplarily, the aircraft is placed on a landing frame 23, which is rectangular, and a plurality of bosses are rotatably connected to one end of two first connecting rods 21 and one end of two second connecting rods 22, respectively, and the other ends of the two first connecting rods 21 and the other ends of the two second connecting rods 22 are rotatably connected to the four corners of the landing frame 23, respectively.

[0027] In the present application embodiment, 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 member 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 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 mounting plate 31 is detachably connected to the storage device 1.

[0028] Exemplarily, the first rotating mechanism 32 can abut against the aircraft. During the launch of the aircraft, the force of the aircraft's forward flight can cause the first rotating mechanism 32 to rotate around the connecting axis 33 in the direction of movement of the aircraft. After the launch is completed, the first elastic member 34 can return the first rotating mechanism 32 to its initial state.

[0029] Exemplarily, an adjustment hole is provided on the support platform 36, and the connecting shaft 33 can adjust the distance between itself and the connecting block 35 through the adjustment hole, and the 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, and the position of the first rotating mechanism 32 can be adjusted according to the length and characteristics of the first elastic member 34.

[0030] Exemplarily, the rocket support assembly 3 also includes a top screw, which is threadedly connected to the support platform 36, and the end of the top screw abuts against the connecting shaft 33, so as to position the connecting shaft 33.

[0031] In the present application embodiment, Figure 6-8 As shown, the first rotating mechanism 32 includes a sleeve 321, a support plate 322 and a rocket support seat 323; the sleeve 321 is rotatably connected to the connecting shaft 33; the support plate 322 is fixedly connected to the outer side of the sleeve 321; the rocket support seat 323 is connected to the support plate 322, and the rocket support seat 323 is configured to abut 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] Exemplarily, a support plate 322 is fixedly connected to the outer side of the sleeve 321, and 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 force of the aircraft flying forward can cause the sleeve 321 to drive the support plate 322 and the rocket support seat 323 to rotate around the connecting shaft 33 in the direction of movement of the aircraft. After the launch is completed, the first elastic member 34 can return the support plate 322 and the rocket support seat 323 to their initial state.

[0033] In the present application embodiment, Figure 9-11 As shown, the front inversion support assembly 4 includes a inversion fixing seat 41, a inversion fixing frame 46, a fixed shaft 42, a second elastic member 43, a inversion support seat 44 and a second rotating mechanism 45; one end of the inversion fixing seat 41 is connected to the inversion fixing frame 46, and the other end of the inversion fixing seat 41 is connected to the inversion support seat 44; the fixed shaft 42 is connected to the inversion fixing frame 46; the second elastic member 43 is sleeved on the fixed shaft 42; one end of the second elastic member 43 is connected to the second rotating mechanism 45, and the other end of the second elastic member 43 abuts against the inversion fixing frame 46; the first end of the second rotating mechanism 45 is rotatably connected to the fixed shaft 42, the second end of the second rotating mechanism 45 is connected to the inversion support seat 44, and the third end of the second rotating mechanism 45 abuts against the aircraft; the inversion fixing seat 41 is detachably connected to the storage device 1 on the side away from the aircraft.

[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 movement of the aircraft. After the launch is completed, the second elastic member 43 can return the second rotating mechanism 45 to an initial state.

[0035] In the present application embodiment, Figure 9-11 As shown, the second rotating mechanism 45 includes a front support arm 451, a first connecting rod 452 and a mounting seat 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 is abutted against the aircraft; the mounting seat 453 is connected to the front support arm 451; one end of the first connecting rod 452 is rotatably connected to the mounting seat 453, and the other end of the first connecting rod 452 is connected to the inverted support seat 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 inverted fixed 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 movement of the aircraft. After the launch is completed, the second elastic member 43 can return the front support arm 451 to its initial state.

[0037] Exemplarily, the second elastic member 43 is a torsion spring, and the second elastic member 43 is sleeved on the fixed shaft 42. 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 abutted against the inverted fixed frame 46. The second elastic member 43 can be expanded or compressed in the radial direction of the fixed shaft 42, thereby achieving the technical effect of returning the front support arm 451 to the initial state after the aircraft is launched.

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

[0039] Exemplarily, the aircraft can slide on two launching guide rails 52 , and during the launching process of the aircraft, the two launching guide rails 52 have a guiding effect on the launching of the aircraft.

[0040] Exemplarily, the rear support 53 includes a connecting portion, a supporting portion and a mounting portion; the two ends of the supporting portion are respectively connected to the connecting portion and the mounting portion, and a slide groove is provided on the connecting portion, and the connecting portion is slidably connected to the storage device 1 through the slide groove, and the angle between the slide groove and the supporting portion is less than 90°, so that the rear support 53 is inclined after being connected to the storage device 1, thereby achieving the purpose of adjusting the aircraft to a predetermined launch angle; the mounting portion is detachably connected to the launch guide rail 52, and when the aircraft is in a recovery or lifting state, the launch guide rail 52 is connected to the landing and lifting frame 23, and at this time, the launch guide rail 52 and the supporting portion are in a disassembled state; when the aircraft is in a launching state, the launch guide rail 52 is connected to the supporting portion, and at this time, the launch guide rail 52 and the landing and lifting frame 23 are in a disassembled state.

[0041] In the present application embodiment, Figure 1-5 As shown, the link landing gear 2 also includes two extension levers 24 and two gas springs 25; the gas spring 25 is arranged between the first link 21 and the second link 22; the two extension levers 24 and the two gas springs 25 are symmetrically arranged relative to the aircraft; the two extension levers 24 are connected in the length direction of the landing frame 23; 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 frame 23.

[0042] Exemplarily, the two extension levers 24 have supporting and guiding functions. When the aircraft is in a lifted state, the gas spring 25 has supporting and locking functions. After the link landing gear 2 is manually lifted to the second position, under the action of the gravity of the aircraft, the link landing gear 2 has a downward movement tendency, and the gas spring 25 can lock the link landing gear 2 in the second position to prevent safety accidents.

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

[0044] Exemplarily, the shell 11 and the front cover 12, the shell 11 and the top cover 13, and the shell 11 and the tail cover 14 can all be connected by snaps. When the aircraft is launched, the snaps are first released to remove the front cover 12, the top cover 13 and the tail cover 14 before performing subsequent operations.

[0045] The present application embodiment provides an aircraft launching method, such as Fig.13 As shown, the aircraft launching method is applicable to the integrated aircraft nest, and the steps are as follows: S1: Open the top cover 13, the front cover 12 and the rear cover 14; S2: Lift the landing frame 23 until the aircraft reaches a 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 fall support assembly 4 in the housing 11, and fix the rocket support assembly 3 to the second connecting rod 51; S4: Remove the connection between the aircraft and the landing frame 23, remove the connection between the landing frame 23 and the two launch rails 52, and put down the landing frame 23. At this time, the aircraft is in contact with both the front lodging support assembly 4 and the rear guide rail support assembly 5. S5: Check the attitude of the aircraft and control the aircraft to launch.

[0046] The present application can safely launch the aircraft in the machine nest through the above steps. The coordinated work of various components ensures the stability and safety of the aircraft during the launch process, while also improving the convenience and efficiency of operation.

[0047] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0048] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. An integrated aircraft nest, characterized in that: It comprises a storage device (1), a connecting rod landing gear (2), a rocket support assembly (3), a front lodging support assembly (4) and a rear guide rail support assembly (5); The connecting rod landing gear (2) is rotatably connected to the interior of the storage device (1); The rocket support assembly (3), the front lodging 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 a recovery state, the link landing gear (2) is in a first position and abuts against the aircraft; When the aircraft is in a lifted state, the link landing gear (2) is in a second position and abuts against the aircraft; When the aircraft is in a launching state, the link landing gear (2) returns to the first position, the rocket support assembly (3), the front lodging support assembly (4) and the rear guide rail support assembly (5) are all in contact with the aircraft, and the aircraft is configured to be launched under the action of the rocket support assembly (3), the front lodging support assembly (4) and the rear guide rail support assembly (5).

2. The integrated aircraft nest according to claim 1, characterized in that: The link landing gear (2) comprises two first links (21), two second links (22) and a landing fixing frame (23); The first connecting rod (21) and the second connecting rod (22) are arranged at intervals in the length direction of the aircraft; The two first connecting rods (21) and the two second connecting rods (22) are symmetrically arranged relative to the aircraft; One end of each of the two first connecting rods (21) is rotatably connected to the bottom plate of the storage device (1), and the other end of each of the two first connecting rods (21) is rotatably connected to the landing bracket (23); One end of each of the two second connecting rods (22) is rotatably connected to the bottom plate of the storage device (1); the other end of each of the two second connecting rods (22) is rotatably connected to the landing bracket (23); The landing fixing frame (23) abuts against the aircraft.

3. The integrated aircraft nest according to claim 1, characterized in that: The rocket support assembly (3) comprises a mounting plate (31), a first rotating mechanism (32), a connecting shaft (33), a first elastic member (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 supporting platform (36); The 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 mounting plate (31) is detachably connected to the storage device (1).

4. The integrated aircraft nest according to claim 3, characterized in that: The first rotating mechanism (32) comprises a shaft sleeve (321), a support plate (322) and a rocket support seat (323); The shaft sleeve (321) is rotatably connected to the connecting shaft (33); The support plate (322) is fixedly connected to the outer side of the shaft sleeve (321); The rocket support seat (323) is connected to the support plate (322), and the rocket support seat (323) 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 connection block (35).

5. The integrated aircraft nest according to claim 1, characterized in that: The front lodging support assembly (4) comprises a lodging fixing seat (41), a lodging fixing frame (46), a fixing shaft (42), a second elastic member (43), a lodging support seat (44) and a second rotating mechanism (45); One end of the inversion fixing seat (41) is connected to the inversion fixing frame (46), and the other end of the inversion fixing seat (41) is connected to the inversion supporting seat (44); The fixed shaft (42) is connected to the lodging fixing frame (46); The second elastic member (43) is sleeved on the fixed shaft (42); One end of the second elastic member (43) is connected to the second rotating mechanism (45), and the other end of the second elastic member (43) is in contact with the inverted fixing frame (46); The first end of the second rotating mechanism (45) is rotatably connected to the fixed shaft (42), the second end of the second rotating mechanism (45) is connected to the inverted support seat (44), and the third end of the second rotating mechanism (45) is in contact with the aircraft; The side of the falling fixing seat (41) away from the aircraft is detachably connected to the storage device (1).

6. The integrated aircraft nest according to claim 5, characterized in that: The second rotating mechanism (45) comprises a front supporting arm (451), a first connecting rod (452) and a mounting seat (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) is in contact with the aircraft; The mounting seat (453) is connected to the front support arm (451); One end of the first connecting rod (452) is rotatably connected to the mounting seat (453), and the other end of the first connecting rod (452) is connected to the inverted support seat (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 inverted fixing frame (46).

7. The integrated aircraft nest according to claim 1, characterized in that: The rear guide rail support assembly (5) comprises a second connecting rod (51), two launching guide 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 guide rails (52) are respectively connected to one end of the two rear supports (53), and the other ends of the two rear supports (53) are slidably connected to the storage device (1); The two launching guide rails (52) are both in contact with the aircraft.

8. The integrated aircraft nest according to claim 2, characterized in that: The link landing gear (2) further comprises two extension levers (24) and two gas springs (25); The gas spring (25) is arranged between the first connecting rod (21) and the second connecting rod (22); The two extension levers (24) and the two gas springs (25) are symmetrically arranged relative to the aircraft; The two extension levers (24) are connected in the length direction of the landing bracket (23); 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 bracket (23).

9. The integrated aircraft nest according to claim 1, characterized in that: The storage device (1) comprises a housing (11), a front cover (12), a top cover (13) and a rear cover (14); The link landing gear (2) is rotatably connected to the interior of the housing (11); The rocket support assembly (3), the front lodging support assembly (4) and the rear guide rail support assembly (5) are all detachably connected to the housing (11); One end of the shell (11) is detachably connected to the front cover (12), the other end of the shell (11) is detachably connected to the rear cover (14), and the upper side of the shell (11) is detachably connected to the top cover (13).

10. A method for launching an aircraft, characterized in that: The aircraft launching method is applicable to the integrated aircraft nest according to any one of claims 1 to 9, and the steps are as follows: S1: Open the top cover (13), the front cover (12) and the rear cover (14); S2: lifting the landing fixture (23) until the aircraft reaches a predetermined launch angle; S3: connecting the two rear supports (53) to the two launch rails (52) respectively, installing a second connecting rod (51) between the two rear supports (53), installing one end of the front fall support assembly (4) in the housing (11), and fixing the rocket support assembly (3) to the second connecting rod (51); S4: removing the connection between the aircraft and the landing frame (23), removing the connection between the landing frame (23) and the two launch rails (52), and lowering the landing frame (23). At this time, the aircraft is in contact with both the front lodging support assembly (4) and the rear rail support assembly (5); S5: Check the attitude of the aircraft and control the aircraft to launch.

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