Fixing device and method for disassembled universal aircraft

Abstract

A fixing device for a disassembled general aircraft comprises a transportation frame, a fuselage fixing assembly, a wing fixing assembly arranged on a frame bottom plate, an engine fixing assembly arranged on the frame bottom plate and a horizontal stabilizer fixing assembly arranged on the frame bottom plate. The transportation frame is provided with a frame bottom plate. The machine body fixing assembly comprises a machine body fixing base part arranged on the frame bottom plate. The central wing fixing assembly comprises a first supporting piece arranged at one end of the fuselage fixing base piece at a first preset angle, and a second supporting piece arranged at the top of the first supporting piece. The central wing fixing piece is arranged at one end of the fuselage fixing base piece and forms a second preset angle with the fuselage fixing base piece; the fuselage tail boom fixing assembly is arranged at the other end of the fuselage fixing base piece and forms a third preset angle; and the fuselage tail boom fixing piece is arranged at the top of the second supporting piece and forms a fourth preset angle with the central wing fixing piece. And parallel fixation of the disassembly parts of the general aircraft is realized. And the occupied space of the fuselage of the general aircraft in the horizontal direction is reduced.

Description

Technical Field

[0001] This application relates to the technical field of aircraft transport and securing, and more specifically, to a securing device and method for a disassembled general aviation aircraft. Background Technology

[0002] General aviation aircraft refer to civil aircraft that do not engage in periodic commercial air transport (passenger or cargo flights). Before transporting a general aviation aircraft, transport personnel need to secure it, which involves using transport securing devices. Traditional transport securing devices are integral designs and require the entire general aviation aircraft to be transported.

[0003] The inventors of this application have discovered that the aforementioned traditional transport securing devices use an integrated welded frame, resulting in an excessively large overall size, high material consumption, and excessive weight. Furthermore, the aforementioned traditional transport securing devices occupy too much space, and the fixed transport of the entire aircraft increases the damage rate during general aviation transport.

[0004] The content in the background section is merely technology known to the public and does not necessarily represent existing technology in this field. Summary of the Invention

[0005] This application provides a fixing device and method for a disassembled general aviation aircraft to solve at least one of the above-mentioned technical problems.

[0006] According to one aspect of this application, a fixing device for a disassembled general aviation aircraft is provided. The disassembled general aviation aircraft includes a fuselage, wings, engines, and a horizontal stabilizer. The fuselage includes a center wing and a tail boom. The center wing is equipped with landing gear, which includes a first landing gear and a second landing gear. The fixing device includes a transport frame, a fuselage fixing assembly, a wing fixing assembly, an engine fixing assembly, and a horizontal stabilizer fixing assembly. The transport frame is provided with a frame base plate. The fuselage fixing assembly includes a fuselage fixing base, a center wing fixing assembly, and a tail boom fixing assembly. The fuselage fixing base is disposed on the frame base plate. The center wing fixing assembly includes a first support member and a center wing fixing member. The first support member is disposed at one end of the fuselage fixing base member at a first preset angle. The center wing fixing member is disposed on top of the first support member and at a second preset angle to the fuselage fixing base member. The tail boom fixing assembly includes a second support member and a tail boom fixing member. The second support member is disposed at the other end of the fuselage fixing base member at a third preset angle. The tail boom fixing component is located on top of the second support component and forms a fourth preset angle with the center wing fixing component. The wing fixing assembly is located on the frame base plate. The engine fixing assembly is located on the frame base plate. The horizontal stabilizer fixing assembly is located on the frame base plate.

[0007] According to some embodiments of this application, the center wing fixing component includes a center wing fixing rod and a landing gear fixing assembly. The two ends of the center wing fixing rod are respectively connected to both sides of the center wing. The landing gear fixing assembly includes a first landing gear fixing member and a second landing gear fixing member. The first landing gear fixing member is disposed at a first position on the center wing fixing rod, the first position being a position on the center wing fixing rod corresponding to the first landing gear. The second landing gear fixing member is disposed at a second position on the center wing fixing rod, the second position being a position on the center wing fixing rod corresponding to the second landing gear.

[0008] According to some embodiments of this application, the first landing gear fixing member includes a first landing gear fixing base and a first movable member. The first landing gear fixing base is disposed at a first position on the center wing fixing rod. The first movable member is movably disposed on the first landing gear fixing base and is used to fix the first landing gear.

[0009] According to some embodiments of this application, the second landing gear fixing member includes a second landing gear fixing base and a second movable member. The second landing gear fixing base is disposed at a second position on the center wing fixing rod. The second movable member is slidably disposed on the second landing gear fixing base for fixing the second landing gear.

[0010] According to some embodiments of this application, the fuselage fixing assembly further includes a movable member. The movable member is disposed at the bottom of the fuselage fixing base.

[0011] According to some embodiments of this application, the wing fixing assembly includes a wing fixing base, a first wing fixing member, and a second wing fixing member. The first wing fixing member is vertically disposed at one end of the wing fixing base and has a first through hole through which one end of the wing passes. The second wing fixing member is vertically disposed at the other end of the wing fixing base and is used to fix the other end of the wing.

[0012] According to some embodiments of this application, the engine mounting assembly includes an engine mounting frame, an engine fixing member, and an engine support member. The engine mounting frame is hollow inside. The engine fixing member is disposed at a fifth preset angle on the inner bottom surface of the engine mounting frame for fixing the engine. The engine support member is disposed at a sixth preset angle on the inner bottom surface of the engine mounting frame for supporting the bottom of the engine.

[0013] According to some embodiments of this application, the engine mounting component includes an engine mounting base and an engine mounting portion. The engine mounting base is disposed at a seventh preset angle on the inner bottom surface of the engine mounting bracket. The engine mounting portion is disposed on the engine mounting base and at an eighth preset angle to the inner bottom surface of the engine mounting bracket, for fixing the engine.

[0014] According to some embodiments of this application, the horizontal stabilizer fixing assembly includes a horizontal stabilizer fixing base, a first horizontal stabilizer fixing member, and a second horizontal stabilizer fixing member. The first horizontal stabilizer fixing member is vertically disposed at one end of the horizontal stabilizer fixing base and has a second through hole through which one end of the horizontal stabilizer passes. The second horizontal stabilizer fixing member is vertically disposed at the other end of the horizontal stabilizer fixing base and has a third through hole through which the other end of the horizontal stabilizer passes.

[0015] According to another aspect of this application, a method for securing a disassembled general aviation aircraft is also provided, the method being performed based on the aforementioned securing device. The securing method includes: securing the fuselage to a fuselage securing assembly; securing the fuselage securing assembly after securing the fuselage to a frame base plate; securing the wing to a wing securing assembly; securing the wing securing assembly to the frame base plate; securing the engine to an engine securing assembly; securing the engine securing assembly to the frame base plate; securing the horizontal stabilizer to a horizontal stabilizer securing assembly; and securing the horizontal stabilizer securing assembly to the frame base plate to complete the securing of the disassembled general aviation aircraft.

[0016] Beneficial effects

[0017] This application achieves parallel fixing of disassembled components of a general aviation aircraft by independently designing fixing assemblies for the fuselage, wings, engines, and horizontal stabilizer. The fixing assemblies for different disassembled components are disassembled and maintained separately, thereby reducing the overall size, weight, and material consumption of the fixing device. The separate fixing of the wings, engines, and horizontal stabilizer of the general aviation aircraft reduces the risk of damage during transportation. The design where the angle difference between the fourth preset angle and the second preset angle is a preset angle difference value reduces the horizontal space occupied by the fuselage of the general aviation aircraft. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A schematic diagram of the fixing device according to an embodiment of this application is shown;

[0020] Figure 2 A schematic diagram of the fuselage fixing assembly according to an embodiment of this application is shown;

[0021] Figure 3A schematic diagram of the structure of the wing fixing assembly according to an embodiment of this application is shown;

[0022] Figure 4 A schematic diagram of the engine mounting assembly according to an embodiment of this application is shown;

[0023] Figure 5 A schematic diagram of the structure of the engine mounting assembly according to an embodiment of this application is shown;

[0024] Figure 6 A flowchart illustrating the fixing method according to an embodiment of this application is shown.

[0025] Explanation of reference numerals in the attached figures:

[0026] Fixed device 1; Transport frame 11; Fuselage fixed assembly 12; Wing fixed assembly 13; Engine fixed assembly 14; Horizontal stabilizer fixed assembly 15; Frame base plate 111; Fuselage fixed base 121; Center wing fixed assembly 122; Fuselage tail boom fixed assembly 123; First support member 1221; Center wing fixed member 1222; Second support member 1231; Fuselage tail boom fixed member 1232; Center wing fixed rod 12221; Landing gear fixed assembly 12222; First landing gear fixed member 122221; Second landing gear fixed member 122222; First landing gear fixed base 122223; First movable member 122224; Second landing gear fixed base 122225; Second movable member 122226;

[0027] Moving part 124; wing fixing base 131; first wing fixing part 132; second wing fixing part 133; first through hole 1321; engine fixing frame 141; engine fixing part 142; engine support part 143; engine fixing base 1421; engine fixing part 1422; horizontal stabilizer fixing base 151; first horizontal stabilizer fixing part 152; second horizontal stabilizer fixing part 153; second through hole 1521; third through hole 1531. Detailed Implementation

[0028] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this application will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0029] The described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a full understanding of embodiments of this disclosure. However, those skilled in the art will recognize that the technical solutions of this disclosure can be practiced without one or more of these specific details, or other methods, components, materials, devices, etc. In these cases, well-known structures, methods, devices, implementations, materials, or operations will not be shown or described in detail.

[0030] Furthermore, the terms “comprising” and “having”, and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the steps or units listed, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to such process, method, product, or apparatus.

[0031] The terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, rather than to describe a specific order.

[0032] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings of the embodiments. The described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0033] According to one aspect of this application, a fixing device for a disassembled general aviation aircraft is provided. The disassembled general aviation aircraft includes a fuselage, wings, engines, and a horizontal stabilizer. The fuselage includes a center wing and a tail boom. The center wing is equipped with landing gear, which includes a first landing gear and a second landing gear.

[0034] Figure 1 A schematic diagram of the fixing device according to an embodiment of this application is shown. According to an example embodiment, such as… Figure 1 As shown, the fixing device 1 includes a transport frame 11, a fuselage fixing assembly 12, a wing fixing assembly 13, an engine fixing assembly 14, and a horizontal stabilizer fixing assembly 15.

[0035] For example, the transport frame 11 can be an external packaging and securing device for securing the disassembled general aviation aircraft before transport. For instance, the transport frame 11 can be a frame container.

[0036] The transport frame 11 is provided with a frame base plate 111. The fuselage fixing assembly 12 includes a fuselage fixing base 121, a center wing fixing assembly 122, and a fuselage tail support fixing assembly 123. The fuselage fixing base 121 is disposed on the frame base plate 111. The center wing fixing assembly 122 includes a first support member 1221 and a center wing fixing member 1222. The first support member 1221 is disposed at one end of the fuselage fixing base 121 at a first preset angle. The center wing fixing member 1222 is disposed on the top of the first support member 1221 and is disposed at a second preset angle with the fuselage fixing base 121.

[0037] For example, the frame base plate 111 can be a rectangular metal plate. The frame base plate 111 serves as the foundational load-bearing platform for the entire fixing device. Exemplarily, the frame base plate 111 can be made of a high-strength alloy material. For example, the fuselage fixing base 121 can be detachably or fixedly connected to the frame base plate 111. Exemplarily, the fuselage fixing base 121 can be detachably mounted to the frame base plate 111 by bolts, or it can be fixedly connected to the frame base plate 111 by welding.

[0038] For example, the first preset angle can be an angle greater than 0° and less than or equal to 90°. For example, the first preset angle can be 90°, meaning the first support member 1221 and the fuselage fixing base member 121 are perpendicular to each other. For example, the second preset angle can be an angle greater than 0° and less than 90°. For example, the second preset angle can be 45°, meaning the tilt angle between the central wing fixing member 1222 and the fuselage fixing base member 121 is 45 degrees.

[0039] The fuselage tail boom fixing assembly 123 includes a second support member 1231 and a fuselage tail boom fixing member 1232. The second support member 1231 is disposed at a third preset angle at the other end of the fuselage fixing base member 121. The fuselage tail boom fixing member 1232 is disposed on the top of the second support member 1231 and is disposed at a fourth preset angle with the center wing fixing member 1222. The wing fixing assembly 13 is disposed on the frame base plate 111. The engine fixing assembly 14 is disposed on the frame base plate 111. The horizontal stabilizer fixing assembly 15 is disposed on the frame base plate 111.

[0040] For example, the third preset angle can be an angle greater than 0° and less than or equal to 90°. For example, the third preset angle can be 90°. That is, the second support member 1231 and the fuselage fixing base member 121 are perpendicular to each other. For example, the fourth preset angle can be an angle greater than 0° and less than or equal to 90°. For example, the fourth preset angle is 90°. That is, the fuselage tail support fixing member 1232 and the center wing fixing member 1222 are perpendicular to each other.

[0041] Through the above embodiments, this application achieves parallel fixing of disassembled components of a general aviation aircraft by independently designing fixing components for the fuselage, wings, engine, and horizontal stabilizer. The fixing components for different disassembled components are disassembled and maintained separately, thereby reducing the overall size, weight, and material consumption of the fixing device. The wings, engine, and horizontal stabilizer of the general aviation aircraft are fixed separately, reducing the risk of damage during transportation. The design where the angle difference between the fourth preset angle and the second preset angle is a preset angle difference reduces the horizontal space occupied by the fuselage of the general aviation aircraft.

[0042] Figure 2 A schematic diagram of the fuselage fixing assembly according to an embodiment of this application is shown. According to some embodiments of this application, such as... Figure 1 and Figure 2 As shown, the center wing fixing component 1222 includes a center wing fixing rod 12221 and a landing gear fixing assembly 12222. The two ends of the center wing fixing rod 12221 are connected to both sides of the center wing, respectively. The landing gear fixing assembly 12222 includes a first landing gear fixing component 122221 and a second landing gear fixing component 122222. The first landing gear fixing component 122221 is located at a first position on the center wing fixing rod 12221, which corresponds to the position of the first landing gear on the center wing fixing rod 12221. The second landing gear fixing component 122222 is located at a second position on the center wing fixing rod 12221, which corresponds to the position of the second landing gear on the center wing fixing rod 12221.

[0043] For example, the center wing fixing rod 12221 is the main load-bearing beam connecting the two sides of the center wing and can be made of metal. The connection between the center wing fixing rod 12221 and the center wing is a detachable connection. For example, the center wing fixing rod 12221 can be made of high-strength titanium alloy, and the center wing fixing rod 1222 can be connected to the center wing via flange bolts or a quick-release locking mechanism. For example, when the first landing gear and the second landing gear of the center wing are in the retracted state, the first landing gear fixing member 122221 can fix the first landing gear, and the second landing gear fixing member 122222 can fix the second landing gear.

[0044] Through the above embodiments, this application uses the central wing fixing rod as the main load-bearing beam to connect both sides of the central wing, forming a closed force ring. This evenly distributes the weight of the general aviation aircraft and the dynamic load during transport to the fuselage fixing components, reducing local stress concentration compared to traditional single-point fixing methods, thereby improving the overall stability of the fixing device. By setting a first landing gear fixing component to fix the first landing gear and a second landing gear fixing component to fix the second landing gear, it prevents the aircraft from accidentally ejecting due to vibration during transport.

[0045] According to some embodiments of this application, such as Figure 1 and Figure 2 As shown, the first landing gear fixing component 122221 includes a first landing gear fixing base 122223 and a first movable component 122224. The first landing gear fixing base 122223 is disposed at a first position on the center wing fixing rod 12221. The first movable component 122224 is movably disposed on the first landing gear fixing base 122223 and is used to fix the first landing gear.

[0046] For example, the first landing gear mounting base 122223 may be provided with a threaded through hole. The first movable member 122224 may be provided with a screw, and the first movable member 122224 can be movably mounted on the first landing gear mounting base 122223 through the threaded through hole and the screw.

[0047] Through the above embodiments, this application achieves adjustable fixing pressure on the first landing gear by setting a first movable member that is movably connected to the first landing gear fixing base, and by adjusting the relative position of the first movable member and the first landing gear fixing member, adjusting the interaction force between the first movable member and the first landing gear, thus realizing adjustable fixing pressure on the first landing gear.

[0048] According to some embodiments of this application, such as Figure 1 and Figure 2 As shown, the second landing gear fixing component 122222 includes a second landing gear fixing base 122225 and a second movable component 122226. The second landing gear fixing base 122225 is disposed at a second position on the center wing fixing rod 12221. The second movable component 122226 is slidably disposed on the second landing gear fixing base 122225 for fixing the second landing gear.

[0049] For example, the second landing gear mounting base 122225 may be provided with a threaded through hole. The second movable member 122226 may be provided with a screw, and the second movable member 122226 can be movably mounted on the second landing gear mounting base 122225 through the threaded through hole and the screw.

[0050] Through the above embodiments, this application achieves adjustable fixing pressure on the second landing gear by setting a second movable member that is movably connected to the second landing gear fixing base, and by adjusting the relative position of the second movable member and the second landing gear fixing member, adjusting the interaction force between the second movable member and the second landing gear, thus realizing adjustable fixing pressure on the second landing gear.

[0051] According to some embodiments of this application, such as Figure 2 As shown, the fuselage fixing assembly 12 also includes a movable member 124. The movable member 124 is disposed at the bottom of the fuselage fixing base 121.

[0052] For example, the movement key 124 can be a swivel wheel.

[0053] Through the above embodiments, this application provides a movable component at the bottom of the fuselage fixing base, which facilitates the movement of the fuselage fixing component, improves the mobility of the fuselage fixing component after fixing the fuselage, and reduces the difficulty of moving the fuselage moving component that has fixed the thick fuselage.

[0054] Figure 3 A schematic diagram of the structure of a wing fixing assembly according to an embodiment of this application is shown. According to some embodiments of this application, such as... Figure 3 As shown, the wing fixing assembly 13 includes a wing fixing base 131, a first wing fixing member 132, and a second wing fixing member 133. The first wing fixing member 132 is vertically disposed at one end of the wing fixing base 131 and has a first through hole 1321 through which one end of the wing passes. The second wing fixing member 133 is vertically disposed at the other end of the wing fixing base 131 and is used to fix the other end of the wing.

[0055] For example, the shape and size of the first through hole 1321 match the shape and size of one end of the wing.

[0056] Through the above embodiments, this application sets the first fixing member and the second fixing member of the wing to form a symmetrical clamping method. The first through hole of the first fixing member is matched with one end of the wing in shape and size, and the other end of the wing is fixed by the second fixing member. This makes the wing load evenly transferred to the wing fixing base, reduces the local stress of the wing fixing base, and thus improves the stability of the wing fixing.

[0057] Figure 4 A schematic diagram of the engine mounting assembly according to an embodiment of this application is shown. According to some embodiments of this application, such as... Figure 4 As shown, the engine mounting assembly 14 includes an engine mounting bracket 141, an engine mounting member 142, and an engine support member 143. The engine mounting bracket 141 is hollow inside. The engine mounting member 142 is positioned at a fifth preset angle on the inner bottom surface of the engine mounting bracket 141 for fixing the engine. The engine support member 143 is positioned at a sixth preset angle on the inner bottom surface of the engine mounting bracket 141 for supporting the bottom of the engine.

[0058] For example, the fifth preset angle can be an angle greater than 0° and less than or equal to 90°. For example, the fifth preset angle can be 90°. That is, the inner bottom surfaces of the engine mounting member 142 and the engine mounting bracket 141 are perpendicular to each other. For example, the sixth preset angle can be an angle greater than 0° and less than or equal to 90°. For example, the sixth preset angle can be 90°. That is, the inner bottom surfaces of the engine support member 143 and the engine mounting bracket 141 are perpendicular to each other.

[0059] For example, the engine mounting bracket 142 can be detachably connected to the engine via bolts to secure the engine.

[0060] Through the above embodiments, this application achieves engine fixation by setting engine fixing components and provides support force to the engine by using engine support components, thus achieving engine fixation together.

[0061] Figure 5 A schematic diagram of the structure of an engine mounting assembly according to an embodiment of this application is shown. According to some embodiments of this application, such as... Figure 5 As shown, the engine mounting bracket 142 includes an engine mounting base 1421 and an engine mounting portion 1422. The engine mounting base 1421 is disposed at a seventh preset angle on the inner bottom surface of the engine mounting frame 141. The engine mounting portion 1422 is disposed on the engine mounting base 1421 and at an eighth preset angle with the inner bottom surface of the engine mounting frame 141, for fixing the engine.

[0062] For example, the seventh preset angle can be an angle greater than 0° and less than or equal to 90°. For instance, the fifth preset angle can be 90°. That is, the inner bottom surfaces of the engine mounting base 1421 and the engine mounting bracket 141 are perpendicular to each other. For example, the eighth preset angle can be an angle where the engine mounting part 1422 is parallel to the contact surface of the engine.

[0063] Through the above embodiments, this application defines the engine fixing component as including an engine fixing base and an engine fixing part. The engine fixing base provides support, and the engine fixing part connects and fixes the engine. Furthermore, by using a preset angle between the engine fixing part and the inner bottom surface of the engine fixing frame, the contact area between the engine fixing part and the engine is increased, thereby improving the fixing effect.

[0064] According to some embodiments of this application, the horizontal stabilizer fixing assembly 15 includes a horizontal stabilizer fixing base 151, a first horizontal stabilizer fixing member 152, and a second horizontal stabilizer fixing member 153. The first horizontal stabilizer fixing member 152 is vertically disposed at one end of the horizontal stabilizer fixing base 151 and has a second through hole 1521 through which one end of the horizontal stabilizer passes. The second horizontal stabilizer fixing member 153 is vertically disposed at the other end of the horizontal stabilizer fixing base 151 and has a third through hole 1531 through which the other end of the horizontal stabilizer passes.

[0065] For example, the shape and size of the second through hole 1521 match the shape and size of one end of the horizontal stabilizer. The shape and size of the third through hole 1531 match the shape and size of the other end of the horizontal stabilizer.

[0066] Through the above embodiments, this application sets up a symmetrical clamping method between the first fixing member and the second fixing member of the horizontal stabilizer. The second through hole of the first fixing member matches the shape and size of one end of the horizontal stabilizer, and the second fixing member fixes the other end of the horizontal stabilizer. This allows the load of the horizontal stabilizer to be evenly transferred to the fixing base of the horizontal stabilizer, reducing the local stress of the fixing base and thus improving the stability of the horizontal stabilizer fixing.

[0067] According to another aspect of this application, a method for securing a disassembled general aviation aircraft is also provided, the method being performed based on the aforementioned securing device 1. Figure 6 A flowchart illustrating a fixing method according to an embodiment of this application is shown. According to an example embodiment, such as... Figure 6 As shown, the fixing methods include S1-S8.

[0068] In S1, the fuselage is fixed to the fuselage fixing assembly.

[0069] For example, the fuselage can be lifted to a preset height using a jacking device and then fixed to the fuselage fixing components. At the same time, the front wheels and the cabin door on the fuselage can be fixed with straps.

[0070] In S2, the fuselage fixing assembly behind the fixed fuselage is fixed to the frame base plate.

[0071] In S3, the wing is secured to the wing securing assembly.

[0072] In S4, the wing fixing assembly after fixing the wing is fixed to the frame base plate.

[0073] In S5, the engine is secured to the engine mounting assembly.

[0074] In S6, the engine mounting assembly after the engine is fixed is fixed to the frame base plate.

[0075] In S7, the horizontal stabilizer is fixed to the horizontal stabilizer fixing assembly.

[0076] In S8, the horizontal stabilizer fixing assembly, after fixing the horizontal stabilizer, is fixed to the frame base plate to complete the fixing of the disassembled general aviation aircraft.

[0077] Through the above embodiments, this application significantly improves the efficiency and reliability of aircraft disassembly and maintenance through a modular and standardized fixed process design. This application achieves parallel fixing of disassembled components of general aviation aircraft by independently designing fixing components for the fuselage, wings, engines, and horizontal stabilizer. The fixing components for different disassembled components are disassembled and maintained separately, thereby reducing the overall size, weight, and material consumption of the fixing device. The separate fixing of the wings, engines, and horizontal stabilizer of the general aviation aircraft reduces the risk of damage during transportation. The design where the angle difference between the fourth preset angle and the second preset angle is a preset angle difference value reduces the horizontal space occupied by the fuselage of the general aviation aircraft.

[0078] Finally, it should be noted that the above description is merely a preferred embodiment of this application and is 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 can still modify the technical solutions of the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A securing device for a disassembled general aviation aircraft, the disassembled general aviation aircraft comprising a fuselage, wings, engines, and a horizontal stabilizer, the fuselage comprising a center wing and a tail boom, the center wing being provided with landing gear, the landing gear comprising a first landing gear and a second landing gear, characterized in that, The fixing device includes: The transport frame is equipped with a frame base plate; The fuselage fixing components include: A fuselage fixing base is provided on the frame base plate; The central wing fixing assembly includes: The first support member is positioned at one end of the fuselage fixing base at a first preset angle; The central wing fixing component is located on top of the first support component and forms a second preset angle with the fuselage fixing base component; The fuselage tail support mounting assembly includes: The second support member is positioned at a third preset angle at the other end of the fuselage fixing base; The fuselage tail support fixing member is located on the top of the second support member and forms a fourth preset angle with the central wing fixing member; A wing fixing assembly is mounted on the base plate of the frame. An engine mounting assembly is mounted on the base plate of the frame. A horizontal stabilizer fixing component is installed on the base plate of the frame.

2. The fixing device according to claim 1, characterized in that, The central wing fixing component includes: The central wing fixing rod has its two ends connected to both sides of the central wing, respectively; Landing gear fixing components, including: The first landing gear fixing component is located at the first position of the center wing fixing rod, which is the position on the center wing fixing rod corresponding to the first landing gear. The second landing gear fixing component is located at the second position on the center wing fixing rod, which is the position on the center wing fixing rod corresponding to the second landing gear.

3. The fixing device according to claim 2, characterized in that, The first landing gear fixing component includes: The first landing gear fixing base is located at the first position of the central wing fixing rod; The first movable component is movably disposed on the first landing gear fixing base and is used to fix the first landing gear.

4. The fixing device according to claim 2 or 3, characterized in that, The second landing gear fixing component includes: The second landing gear mounting base is located at the second position of the central wing mounting rod; The second movable component is slidably disposed on the second landing gear fixing base and is used to fix the second landing gear.

5. The fixing device according to claim 1, characterized in that, The fuselage fixing assembly also includes: The movable component is located at the bottom of the fixed base of the fuselage.

6. The fixing device according to claim 1, characterized in that, The wing fixing assembly includes: Wing mounting base; A first wing fixing member is vertically disposed at one end of the wing fixing base member. The first wing fixing member is provided with a first through hole, through which one end of the wing passes. The second wing fixing component is vertically disposed at the other end of the wing fixing base component and is used to fix the other end of the wing.

7. The fixing device according to claim 1, characterized in that, The engine mounting assembly includes: Engine mounting frame, hollow inside; An engine mounting component is positioned at a fifth preset angle on the inner bottom surface of the engine mounting frame for fixing the engine. An engine support component is positioned at a sixth preset angle on the inner bottom surface of the engine mounting frame to support the bottom of the engine.

8. The fixing device according to claim 7, characterized in that, The engine mounting component includes: The engine mounting base is positioned at a seventh preset angle on the inner bottom surface of the engine mounting frame; An engine fixing part is disposed on the engine fixing base and forms an eighth preset angle with the inner bottom surface of the engine fixing frame, and is used to fix the engine.

9. The fixing device according to claim 1, characterized in that, The horizontal stabilizer fixing assembly includes: Horizontal stabilizer fixing base; A first fixing member for a horizontal stabilizer is vertically disposed at one end of the fixing base for the horizontal stabilizer. The first fixing member for the horizontal stabilizer is provided with a second through hole, through which one end of the horizontal stabilizer passes. A second fixing member for the horizontal stabilizer is vertically disposed at the other end of the fixing base of the horizontal stabilizer. The second fixing member for the horizontal stabilizer is provided with a third through hole, through which the other end of the horizontal stabilizer passes.

10. A method for securing a disassembled general aviation aircraft, said method being performed based on a securing device as described in any one of claims 1-9, characterized in that, The fixing method includes: Secure the fuselage to the fuselage securing assembly; The body fixing assembly behind the fixed body is fixed to the frame base plate; Secure the wing to the wing fixing assembly; Secure the wing fixing assembly to the frame base plate after fixing the wing; Secure the engine to the engine mounting assembly; Secure the engine mounting assembly to the frame base plate after fixing the engine; The horizontal stabilizer is fixed to the horizontal stabilizer fixing assembly; The horizontal stabilizer fixing assembly is then fixed to the frame base plate to complete the fixing of the disassembled general aviation aircraft.

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