Aircraft capable of adjusting gravity center and adjusting method
By setting up center of gravity adjustment mechanisms at the nose and tail of the aircraft and using components such as hydraulic push rods and electric telescopic rods, dynamic adjustment of the aircraft's center of gravity can be achieved, solving the problem of insufficient flexibility of traditional aircraft center of gravity adjustment methods and improving flight stability and safety.
Patent Information
- Application Number
- CN202511107620.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-08
- Publication Date
- 2025-10-17
AI Technical Summary
The center of gravity adjustment method of traditional aircraft is difficult to adapt to complex and changeable flight scenarios, resulting in the risk of center of gravity shift and extremely low flexibility, affecting flight stability and safety.
A center of gravity adjustment mechanism is set between the nose and the tail, including components such as a hydraulic push rod and an electric telescopic rod. The dynamic balance of the center of gravity of the aircraft is achieved through the telescopic adjustment of the nose and the tail.
It improves the flexibility and response speed of center of gravity adjustment, enhances the stability and safety of the aircraft under different load conditions, expands the freedom of load configuration, and improves the versatility and design compatibility of the aircraft.
Smart Images
Figure CN120793150A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application belongs to the technical field of aircraft, and particularly relates to an aircraft with adjustable center of gravity and a method for adjusting the center of gravity of the aircraft. BACKGROUND
[0002] The position of the center of gravity of an aircraft has a crucial influence on flight stability, control performance and mission adaptability. Whether it is a fixed-wing aircraft, a multi-rotor aircraft or a hybrid aircraft, the center of gravity distribution needs to be matched with the aerodynamic layout and power output characteristics to ensure balance during different flight stages such as cruising, taking off and landing, and maneuvering, and to avoid risks such as stalling, rolling over or control failure.
[0003] The traditional center of gravity adjustment of an aircraft mostly relies on preset counterweight structures or fixed component layouts. The positions of key components are calculated and fixed during the design stage to achieve static balance of the center of gravity. However, this static center of gravity design is difficult to adapt to complex and variable scenarios. When the load state changes, such as uneven distribution of passengers, differences in the amount of cargo, and changes in weight due to fuel consumption, the center of gravity is easy to deviate from the design range. However, the center of gravity adjustment method is limited, and manual redistribution of cargo or restriction of passenger seating areas is required, which has very low flexibility. To avoid the center of gravity deviating beyond the safe range, the traditional aircraft needs to strictly limit the positions of passengers, cargo and fuel tanks, such as allowing the cargo compartment to be located only in a specific area and fixing the capacity and position of the fuel tank, which results in poor compatibility of the aircraft and the inability to adjust the center of gravity according to the situation.
[0004] Therefore, the present application is proposed. SUMMARY
[0005] To solve the problem that the current static center of gravity design of an aircraft is difficult to adapt to complex and variable flight scenarios and cannot flexibly change the center of gravity according to the situation, the basic idea of the technical solution of the present application is as follows: An aircraft with an adjustable center of gravity, wherein a center of gravity adjustment mechanism is arranged between the nose and the fuselage and between the fuselage and the tail of the aircraft, the center of gravity adjustment mechanism is a telescopic mechanism, and the telescopic mechanism can lengthen and shorten the distance between the nose and the fuselage and the distance between the fuselage and the tail.
[0006] As a preferred embodiment of the present application, the center of gravity adjustment mechanism comprises a nose adjustment assembly and a tail adjustment assembly; The nose adjustment assembly is connected between the engine and the fuselage and comprises a first mounting plate for mounting the engine, a hydraulic push rod for driving the first mounting plate to move, a second mounting plate for bearing the hydraulic push rod, and a linkage assembly comprising a first connecting rod and a second connecting rod. The tail adjustment assembly is connected between the fuselage and the tail and comprises an electric telescopic rod for driving the tail to move and a plurality of telescopic assemblies.
[0007] As a preferred embodiment of the present invention, the head adjustment assembly is arranged at the front of the fuselage, and a mounting groove is opened at the front of the fuselage, in which a first mounting plate, a second mounting plate, a hydraulic push rod and a connecting rod assembly are installed.
[0008] As a preferred embodiment of the present invention, a hydraulic push rod is provided between the first mounting plate and the second mounting plate, the tail of the hydraulic push rod is rotatably connected to the second mounting plate, and the output end of the hydraulic push rod is rotatably connected to the first mounting plate.
[0009] As a preferred embodiment of the present invention, sliding grooves are provided on both sides of the first mounting plate and the second mounting plate, and first connecting rods and second connecting rods are correspondingly provided on both sides of the first mounting plate and the second mounting plate, one end of the first connecting rod is rotatably mounted on the first mounting plate, and the other end is slidably arranged in the sliding groove of the second mounting plate, and one end of the second connecting rod is rotatably mounted on the second mounting plate, and the other end is slidably arranged in the sliding groove of the first mounting plate.
[0010] As a preferred embodiment of the present invention, a rotation shaft is installed between the first connecting rod and the second connecting rod, and the first connecting rod and the second connecting rod are hinged through the rotation shaft.
[0011] As a preferred embodiment of the present invention, the tail is arranged at the rear part of the fuselage, and the electric telescopic rod and multiple telescopic components of the tail adjustment component are installed between the tail and the fuselage.
[0012] A method for adjusting the center of gravity of an aircraft, Automatically or manually determine whether the aircraft's center of gravity needs to be adjusted forward or backward; Adjusting the center of gravity of the aircraft forward and backward by extending or retracting the distance between the nose and / or tail and the fuselage; The nose extends to move the center of gravity forward; the nose retracts to move the center of gravity backward; The tail is extended to move the center of gravity backward; the tail is retracted to move the center of gravity forward; The nose of the aircraft is extended and the tail is retracted, which moves the center of gravity forward and increases the maximum forward center of gravity shift; The nose of the aircraft is retracted and the tail of the aircraft is extended, which moves the center of gravity backward and increases the maximum value of the center of gravity backward; The nose extends and the tail extends, the nose retracts and the tail retracts, precisely adjusting the center of gravity.
[0013] Compared with the prior art, the present invention has the following beneficial effects: The application realizes the gravity center adaptation through the cooperation of the head and tail double-path adjustment assembly, and the cooperation of the hydraulic push rod, connecting rod, sliding groove, telescopic assembly, connecting rod assembly and other components ensures the smooth adjustment process, reduces the deviation and jamming, and the overall structure is compact and simple, the mature power components and connecting rod mechanism are adopted, the weight is light and the adjustment is efficient, and different flight stages and environmental changes can be flexibly adapted.
[0014] The application improves the gravity center adjustment flexibility, does not need to rely on external trimming device, such as rudder surface and fuel transfer, directly changes the fuselage mass distribution through the telescopic change of the head and tail, quickly responds to the gravity center deviation under different load states, such as the load of people, goods and the oil quantity change of the fuel tank, and realizes the dynamic trimming.
[0015] The application expands the load configuration freedom degree, does not need to strictly limit the positions of passengers, goods and fuel tanks during the design of the aircraft, can flexibly adjust the front and rear positions of the cargo compartment, increases the layout options of the fuel tank, makes the same model adapt to various scenes, and improves the universality and design compatibility of the aircraft.
[0016] The application enhances the flight safety and stability, the gravity center of the aircraft can be quickly trimmed in a wider range, the gravity center imbalance caused by the sudden change of the load, such as the sliding of goods and the rapid consumption of fuel, is avoided, and the risks of stall and control failure are reduced.
[0017] The specific embodiments of the application will be further described in detail in combination with the drawings. DESCRIPTION OF DRAWINGS
[0018] In the drawings: Figure 1 It is a partial sectional view of an aircraft capable of adjusting the gravity center; Figure 2 It is a partial sectional view of an aircraft capable of adjusting the gravity center; Figure 1 It is an enlarged view of A in the middle; Figure 3 It is a schematic view of the internal structure of an aircraft capable of adjusting the gravity center; Figure 4 It is a schematic view of the internal structure of an aircraft capable of adjusting the gravity center; Figure 3 It is an enlarged view of B in the middle; Figure 5 It is a connection schematic view of an aircraft capable of adjusting the gravity center; Figure 6 It is a connection schematic view of an aircraft capable of adjusting the gravity center; Figure 5 It is an enlarged view of C in the middle.
[0019] In the drawings: 1, fuselage; 2, tail; 3, electric telescopic rod; 4, telescopic assembly; 5, mounting groove; 6, first mounting plate; 7, second mounting plate; 8, hydraulic push rod; 9, first connecting rod; 10, second connecting rod; 11, rotating shaft; 12, sliding groove. DETAILED DESCRIPTION
[0020] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments will be described clearly and completely below with reference to the drawings in the embodiments of the present application. The following embodiments are used to explain the present application.
[0021] As shown in Figures 1 to 6 , a center of gravity adjustable aircraft includes a fuselage 1, a tail 2, an engine and a center of gravity adjusting mechanism arranged on the fuselage 1, the center of gravity adjusting mechanism comprising a nose adjusting assembly and a tail adjusting assembly; The nose adjusting assembly comprises a first mounting plate 6 for mounting the engine, a hydraulic push rod 8 for driving the first mounting plate 6 to move, a second mounting plate 7 for bearing the hydraulic push rod 8 and a linkage assembly comprising a first connecting rod 9 and a second connecting rod 10.
[0022] The tail adjusting assembly comprises an electric telescopic rod 3 for driving the tail 2 to move and a plurality of telescopic assemblies 4; In the present arrangement, a double-path center of gravity adjusting structure is constructed by the combination of the nose adjusting assembly and the tail adjusting assembly, the tail adjusting assembly provides structural support for the relative displacement of the tail 2 and the fuselage 1, and the nose adjusting assembly lays the foundation for the movement of the nose components through the cooperation of the first mounting plate 6, the second mounting plate 7 and the linkage assembly, together forming the core structural framework of the center of gravity adjustment.
[0023] As shown in Figures 1 to 6 , in the specific embodiment, the tail 2 is arranged at the rear of the fuselage 1, and the electric telescopic rod 3 and the plurality of telescopic assemblies 4 are mounted between the tail 2 and the fuselage 1. In the present arrangement, the electric telescopic rod 3 is connected to the tail 2 and the fuselage 1 at both ends as a power component to directly drive the tail 2 to produce forward and backward displacement relative to the fuselage 1, and the plurality of telescopic assemblies 4 are symmetrically distributed around the electric telescopic rod 3 to assist in connecting the tail 2 and the fuselage 1, for maintaining the structural stability of the tail 2 during movement to prevent the tail 2 from deviating or shaking.
[0024] As shown in Figures 1 to 6 , further, the nose adjusting assembly is arranged at the nose position of the front of the fuselage 1, and the first mounting plate 6 and the second mounting plate 7 are mounted in the mounting groove 5. In the present arrangement, the mounting groove 5 provides a mounting space for the nose adjusting assembly, the second mounting plate 7 is fixed in the mounting groove 5 as a bearing base, and the first mounting plate 6 and the second mounting plate 7 are arranged opposite to each other in the mounting groove 5 to form a structural framework for the movement of the nose components, providing a support carrier for the installation of the hydraulic push rod 8 and the linkage assembly.
[0025] As shown in Figures 1 to 6As shown, further, a hydraulic push rod 8 is arranged between the first mounting plate 6 and the second mounting plate 7, the tail of the hydraulic push rod 8 is rotatably connected with the second mounting plate 7, and the output end of the hydraulic push rod 8 is rotatably connected with the first mounting plate 6. In this arrangement, the hydraulic push rod 8 is rotatably connected at both ends, so that it can adapt to the angle change between the first mounting plate 6 and the second mounting plate 7 during the extension and retraction process, and convert the hydraulic power into a driving force for pushing the first mounting plate 6 to move horizontally relative to the second mounting plate 7, thereby realizing displacement adjustment of the first mounting plate 6.
[0026] As shown in Figures 1 to 6 further, sliding grooves 12 are formed on both sides of the first mounting plate 6 and the second mounting plate 7, and first connecting rods 9 and second connecting rods 10 are arranged in cross distribution on both sides, one end of the first connecting rod 9 is rotatably mounted on the first mounting plate 6, and the other end is slidably arranged in the sliding groove 12 of the second mounting plate 7, one end of the second connecting rod 10 is rotatably mounted on the second mounting plate 7, and the other end is slidably arranged in the sliding groove 12 of the first mounting plate 6. In this arrangement, the sliding grooves 12 provide sliding guide paths for the ends of the first connecting rods 9 and the second connecting rods 10, and the first connecting rods 9 and the second connecting rods 10 are connected by one end rotation and one end sliding, forming a linkage structure of the first mounting plate 6 and the second mounting plate 7, limiting the movement direction of the first mounting plate 6, and ensuring stable movement of the first mounting plate 6 in the horizontal direction.
[0027] As shown in Figures 1 to 6 further, a rotating shaft 11 is mounted between the first connecting rod 9 and the second connecting rod 10, and the first connecting rod 9 and the second connecting rod 10 are hinged through the rotating shaft 11. In this arrangement, the rotating shaft 11 connects the cross-shaped first connecting rod 9 and the second connecting rod 10 to form a hinge structure that can rotate relative to each other, so that the connecting rod assembly can flexibly deform when moving with the first mounting plate 6, ensuring the support strength of the first mounting plate 6 and providing structural flexibility for its horizontal displacement.
[0028] The implementation principle of the center of gravity adjustable aircraft of the embodiment is as follows: when it is judged according to the prior art automatic or manual mode that the center of gravity of the aircraft needs to be adjusted forward and backward, the center of gravity is dynamically adjusted through the coordinated operation of the nose adjusting assembly and the tail adjusting assembly. In the tail adjusting assembly, the tail 2 connected to the rear of the fuselage 1 is provided with an electric telescopic rod 3 and a plurality of telescopic assemblies 4 between the tail 2 and the fuselage. The telescopic action of the electric telescopic rod 3 drives the tail 2 to displace forward and backward relative to the fuselage 1, and the telescopic assemblies 4 are synchronously matched to ensure the stability of the movement. The weight distribution of the rear of the aircraft is changed through the change of the tail position to adjust the center of gravity. The nose adjusting assembly is arranged in the installation slot 5 at the front of the fuselage 1. The first installation plate 6 and the second installation plate 7 in the installation slot 5 are provided with a hydraulic push rod 8. The tail of the hydraulic push rod 8 is rotatably connected with the second installation plate 7, and the output end is rotatably connected with the first installation plate 6. The telescopic action of the hydraulic push rod 8 can push the first installation plate 6 to move horizontally relative to the second installation plate 7. Meanwhile, the first installation plate 6 and the second installation plate 7 are provided with sliding grooves 12 on the two sides. The first connecting rod 9 and the second connecting rod 10 distributed in cross are rotatably arranged at one end of the corresponding installation plate and slidably arranged at the other end of the sliding groove 12 of the other installation plate, and are hingedly connected through the rotating shaft 11 to form a stable support guide structure to ensure the stability of the horizontal movement of the first installation plate 6. Since the first installation plate 6 is used for installing the engine, the movement of the first installation plate 6 will change the weight distribution of the nose position to realize the adjustment of the front center of gravity. Finally, the rear center of gravity is changed through the tail adjusting assembly, and the front center of gravity is changed through the nose adjusting assembly. The two are cooperated to form a multi-dimensional adjustment mechanism to realize the accurate dynamic adjustment of the overall center of gravity of the aircraft.
[0029] The above and the drawings are only embodiments, which make a detailed description of the present application in a general way, but some modifications or improvements can be made on the basis of the embodiments of the present application, which are obvious to those skilled in the art. Therefore, the modifications or improvements without departing from the spirit of the present application are within the protection scope of the present application.
Claims
1. An aircraft with adjustable center of gravity, characterized in that: A center of gravity adjustment mechanism is respectively provided between the nose and fuselage, and between the fuselage and tail of the aircraft. The center of gravity adjustment mechanism is a telescopic mechanism that can extend and shorten the distance between the nose and fuselage, and the distance between the fuselage and tail.
2. The aircraft with adjustable center of gravity according to claim 1, characterized in that: The center of gravity adjustment mechanism includes a nose adjustment component and a tail adjustment component; The nose adjustment assembly is connected between the engine and the fuselage (1), and includes a first mounting plate (6) for mounting the engine, a hydraulic push rod (8) for driving the first mounting plate (6) to move, a second mounting plate (7) for carrying the hydraulic push rod (8), and a connecting rod assembly, wherein the connecting rod assembly includes a first connecting rod (9) and a second connecting rod (10); The tail adjustment assembly is connected between the fuselage (1) and the tail (2), and comprises an electric telescopic rod (3) for driving the tail (2) to move and a plurality of telescopic assemblies (4).
3. The aircraft with adjustable center of gravity according to claim 2, characterized in that: The head adjustment assembly is arranged at the front of the fuselage (1). The front of the fuselage (1) is provided with a mounting groove (5), and a first mounting plate (6), a second mounting plate (7), a hydraulic push rod (8) and a connecting rod assembly are installed in the mounting groove (5).
4. The aircraft with adjustable center of gravity according to claim 3, characterized in that: A hydraulic push rod (8) is provided between the first mounting plate (6) and the second mounting plate (7), the tail of the hydraulic push rod (8) is rotatably connected to the second mounting plate (7), and the output end of the hydraulic push rod (8) is rotatably connected to the first mounting plate (6).
5. The aircraft with adjustable center of gravity according to claim 3, characterized in that: Both sides of the first mounting plate (6) and the second mounting plate (7) are provided with sliding grooves (12), and the first mounting plate (6) and the second mounting plate (7) are provided with cross-distributed first connecting rods (9) and second connecting rods (10) on both sides, one end of the first connecting rod (9) is rotatably mounted on the first mounting plate (6), and the other end is slidably arranged in the sliding groove (12) of the second mounting plate (7), and one end of the second connecting rod (10) is rotatably mounted on the second mounting plate (7), and the other end is slidably arranged in the sliding groove (12) of the first mounting plate (6).
6. The aircraft with adjustable center of gravity according to claim 5, characterized in that: A rotation shaft (11) is installed between the first connecting rod (9) and the second connecting rod (10), and the first connecting rod (9) and the second connecting rod (10) are hinged via the rotation shaft (11).
7. The aircraft with adjustable center of gravity according to claim 2, characterized in that: The tail (2) is arranged at the rear of the fuselage (1), and the electric telescopic rod (3) and multiple telescopic components (4) of the tail adjustment component are installed between the tail (2) and the fuselage (1).
8. A method for adjusting the center of gravity of an aircraft, characterized in that: Automatically or manually determine if the aircraft's center of gravity needs to be adjusted forward or backward; Adjusting the center of gravity of the aircraft forward and backward by extending or retracting the distance between the nose and / or tail and the fuselage; The nose of the aircraft is extended, which moves the center of gravity forward; The nose of the aircraft is retracted, causing the center of gravity to move rearward; The tail is extended to move the center of gravity rearward; The tail is retracted to move the center of gravity forward; The nose is extended and the tail is retracted, which moves the center of gravity forward and increases the maximum forward center of gravity shift; The nose of the aircraft is retracted and the tail of the aircraft is extended, which moves the center of gravity backward and increases the maximum value of the center of gravity backward; The nose extends and the tail extends, the nose retracts and the tail retracts, precisely adjusting the center of gravity.