A glider and flying vehicle
By designing a glider with movable, retractable wings and automatic control, the problems of inconvenient transportation and high costs caused by the complex structure of existing aircraft have been solved, achieving the goal of efficient and low-cost material delivery and improving transportation efficiency and safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- 河北通飞未来飞行器有限公司
- Filing Date
- 2025-08-29
- Publication Date
- 2026-06-26
AI Technical Summary
Existing delivery aircraft have complex structures, resulting in large size and increased weight, making them inconvenient to transport and store, difficult to fold or disassemble, reducing transportation efficiency and increasing costs. Furthermore, the complex structure increases the difficulty of assembly and maintenance, limiting large-scale deployment and rapid response missions.
Design a glider with retractable and deployable wings. The fuselage has a storage compartment for storing the wings. The wing state is changed by a drive mechanism and automatically controlled by a control module. The tail provides aerodynamic stability. The wings are stored in the storage compartment during transport and deployed to provide lift during flight.
It achieves the compactness of the glider in transport mode and the aerodynamic performance in flight mode, improves space utilization and mission adaptability, reduces transportation costs, enhances delivery efficiency and safety, adapts to complex weather conditions, and simplifies assembly and maintenance.
Smart Images
Figure CN224409598U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft technology, and more specifically, to a glider and a flight vehicle. Background Technology
[0002] With the development of the demand for timeliness in material transportation in modern warfare and emergency disaster relief, air transport has gradually become an important means of material transportation.
[0003] However, existing delivery aircraft generally suffer from complex structures. Their overall configuration typically includes multiple fixed arms, redundant support structures, and complex landing gear systems, resulting in a large size and increased weight, making them inconvenient for transportation and storage. In practical applications, the complex structural design makes the aircraft difficult to fold or disassemble, and cannot effectively adapt to the spatial layout of standard transport vehicles or containers. This limits the number of aircraft that can be carried in a single transport, significantly reducing transportation efficiency and increasing manufacturing and logistics costs. Furthermore, the complex structure also increases the difficulty of assembly, maintenance, and repair, hindering large-scale deployment and rapid response missions. Utility Model Content
[0004] The purpose of this utility model is to provide a glider and flight vehicle with a simplified structure that is easy to fold or disassemble, thereby reducing the transport volume and improving transport efficiency and economy.
[0005] The embodiments of this utility model are implemented as follows:
[0006] In a first aspect, this utility model provides a glider, comprising:
[0007] The fuselage is provided with a accommodating compartment and an installation section, the accommodating compartment being used to accommodate cargo or wings;
[0008] The wing includes a mounting shaft and two wing bodies, both of which are movably mounted on the mounting shaft. The wing bodies have an extended state and a retracted state. The mounting shaft is detachably mounted on the mounting section. The wing is used to be housed in the accommodating compartment in the retracted state, or to be mounted on the mounting section in the retracted or extended state.
[0009] In an optional embodiment, the glider further includes a drive mechanism, and the fuselage is also provided with an equipment compartment. The drive mechanism is disposed in the equipment compartment and is used to drive the wing to an extended or retracted state, or to adjust the attitude of the wing body when the wing is in the extended state.
[0010] In an optional embodiment, the glider further includes a tail fin, with the equipment bay located at one end of the fuselage and the tail fin located at the other end of the fuselage.
[0011] In an optional embodiment, there are multiple mounting parts and multiple wings, and the mounting shafts of the multiple wings are mounted on the multiple mounting parts in a one-to-one correspondence.
[0012] In an optional embodiment, a plurality of the mounting portions are located on the top of the body and are arranged at intervals along the length of the body.
[0013] In an optional embodiment, the wing bodies of the plurality of wings are all located on top of the fuselage in the retracted state.
[0014] In an optional embodiment, in the retracted state, the wings of two adjacent wings are staggered and stacked in the height direction.
[0015] In an optional embodiment, there are two mounting parts and two wings. The two mounting parts are located at the top ends of the fuselage, and the mounting shafts of the two wings are respectively disposed at the two mounting parts.
[0016] In an optional embodiment, the glider further includes a control module disposed in the equipment compartment. The control module is used to control the drive mechanism to drive the wing to the retracted state, the deployed state, or to adjust its attitude.
[0017] Secondly, this utility model provides an air vehicle, including a transport aircraft and a glider as described in any of the foregoing embodiments. The transport aircraft includes a delivery compartment, and a door is provided at the tail of the delivery compartment for opening the delivery compartment to deliver the glider.
[0018] The beneficial effects of the glider and flight vehicle provided in this embodiment include: when the glider is in the transport or delivery preparation stage, the wings can be configured to retract to reduce the space occupied in the transport; when the glider is delivered into the air, the wings can be deployed to the state required for flight, thereby achieving autonomous gliding flight; and when the glider is only in the transport state and has no delivery mission, the retracted wings can be placed in the storage compartment for storage, further reducing the volume occupied by the glider; it can be seen that the glider provided in this embodiment has a simple structure, is easy to install and maintain, and by reasonably configuring the body structure and wing shape, it not only improves the space utilization of the glider, but also enhances its mission adaptability and delivery efficiency, thereby achieving the goal of efficient and low-cost end-point material delivery; in addition, the glider flies by gliding, so there is no need to install a power unit, further reducing the manufacturing cost of the glider. Attached Figure Description
[0019] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.
[0020] Figure 1 This is a schematic diagram of the glider in its deployed state provided in an embodiment of the present invention;
[0021] Figure 2 A schematic diagram of the glider in its retracted state provided in an embodiment of this utility model;
[0022] Figure 3 This is a schematic diagram of the flight vehicle delivery state structure provided in an embodiment of the present utility model.
[0023] Icons: 1-Flight vehicle; 10-Glider; 100-Airframe; 110-Storage compartment; 120-Installation section; 130-Equipment compartment; 200-Wing; 210-Installation shaft; 220-Wing body; 300-Tail; 20-Transport aircraft; 21-Drop pod; 22-Door. Detailed Implementation
[0024] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.
[0025] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.
[0026] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.
[0027] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.
[0028] Furthermore, terms such as "horizontal" and "vertical" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.
[0029] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0030] With the development of the demand for timeliness in material transportation in modern warfare and emergency disaster relief, air transport has gradually become an important means of material transportation.
[0031] However, existing delivery aircraft generally suffer from complex structures. Their overall configuration typically includes multiple fixed arms, redundant support structures, and complex landing gear systems, resulting in a large size and increased weight, making them inconvenient for transportation and storage. In practical applications, the complex structural design makes the aircraft difficult to fold or disassemble, and cannot effectively adapt to the spatial layout of standard transport vehicles or containers. This limits the number of aircraft that can be carried in a single transport, significantly reducing transportation efficiency and increasing manufacturing and logistics costs. Furthermore, the complex structure also increases the difficulty of assembly, maintenance, and repair, hindering large-scale deployment and rapid response missions. Especially in scenarios requiring long-distance delivery or batch deployment, the inconvenience and high cost of transporting existing aircraft are particularly prominent, limiting their promotion in commercial and emergency applications.
[0032] Therefore, there is an urgent need to provide a delivery aircraft with a simplified structure that is easy to fold or disassemble, in order to reduce transportation volume, improve transportation efficiency and economy, and meet the needs of modern logistics for efficient and low-cost unmanned delivery systems.
[0033] Based on the problems existing in the current technology, please refer to Figure 1 and Figure 2 This utility model provides a glider 10, which includes a body 100 and wings 200.
[0034] The fuselage 100 is provided with a accommodating compartment 110 and a mounting section 120. The accommodating compartment 110 is used to accommodate cargo or the wing 200. The wing 200 includes a mounting shaft 210 and two wing bodies 220. Both wing bodies 220 are movably mounted on the mounting shaft 210. The wing bodies 220 have an extended state and a retracted state. The mounting shaft 210 is detachably mounted on the mounting section 120. The wing 200 is used to accommodate the accommodating compartment 110 in the retracted state, or to be mounted on the mounting section 120 in the retracted or extended state.
[0035] In this embodiment, the accommodating compartment 110 not only provides loading space for cargo, but also allows the wing 200 to be retracted into the compartment during glider 10 transport, thereby reducing the overall volume and facilitating storage and transportation. The mounting part 120 serves as the connection structure between the wing 200 and the fuselage 100, and its detachable nature allows for more flexible configuration of the wing 200 in different states.
[0036] Specifically, the wing 200 can be mounted on the mounting section 120 in a retracted state to reduce the external profile of the glider 10, or it can be mounted on the mounting section 120 in an extended state to provide the lift structure required for gliding flight. It can also be retracted into the storage compartment 110 in a retracted state. This design ensures both the compactness of the glider 10 in the non-flying state and the stability of its aerodynamic performance during flight.
[0037] Furthermore, the wing body 220 is movably mounted on the mounting shaft 210, possessing the ability to switch between an extended and retracted state, enabling the glider 10 to adapt to different transportation and flight requirements. In practical applications, when the glider 10 is in the transportation or delivery preparation stage, the wing body 220 can be configured to a retracted state to reduce its occupation of transportation space; while when the glider 10 is delivered into the air, the wing body 220 can be extended to the state required for flight, thereby achieving autonomous gliding flight; and when the glider 10 is only in the transportation state without a delivery mission, the retracted wing 200 can also be placed in the storage compartment 110 for storage, further reducing the volume occupied by the glider 10.
[0038] It should be noted that the cargo compartment 110 can hold goods including but not limited to food, medicine, ammunition, water, batteries, fuel, etc., thus enabling effective resupply of ground troops, for example, in emergency disaster relief or military deployment scenarios.
[0039] Therefore, it can be seen that the glider 10 provided in this embodiment of the present invention, through the reasonable configuration of the fuselage 100 structure and the wing 200 shape, not only improves the space utilization of the glider 10, but also enhances its mission adaptability and delivery efficiency, thereby achieving the goal of efficient and low-cost end-point material delivery. In addition, the glider 10 provided in this embodiment flies by gliding, so there is no need to install a power unit, further reducing the manufacturing cost of the glider 10.
[0040] Furthermore, the glider 10 also includes a drive mechanism (not shown), and the fuselage 100 is also provided with an equipment compartment 130. The drive mechanism is located in the equipment compartment 130 and is used to drive the wing 200 to be in an extended or retracted state, or to adjust the attitude of the wing body 220 when the wing 200 is in an extended state.
[0041] In this embodiment, the introduction of the drive mechanism eliminates the need for manual operation or passive deployment mechanisms in switching the wing 200's state. Instead, autonomous control is achieved through the built-in power unit, significantly improving the glider 10's mission response speed and flight reliability. For example, after the glider 10 is launched into the air, the drive mechanism can drive the wing 200 from a retracted state to an deployed state according to a preset program or remote command, thereby quickly entering gliding flight mode. During flight, the mechanism can also fine-tune the angle or tilt of the wing body 220 to achieve stable control of flight attitude and trajectory correction. This design enables the glider 10 to maintain good flight performance under complex weather conditions, enhancing its adaptability to terminal delivery missions.
[0042] Furthermore, the glider 10 also includes a control module (not shown), which is located in the equipment compartment 130. The control module is used to control the drive mechanism to drive the wing 200 to a retracted state, an extended state, or to adjust its attitude.
[0043] In this embodiment, the collaborative action between the control module and the drive mechanism constitutes the core mechanism for the state control of the glider 10's wing 200. For example, after the glider 10 is launched into the air from the transport aircraft 20, the control module can automatically determine and trigger the drive mechanism to perform corresponding actions based on the flight stage, airflow conditions, or mission requirements, or receive remote control signals to control the drive mechanism to perform corresponding actions, such as driving the wing 200 from a retracted state to an extended state at a predetermined time, or adjusting the wing body 220 angle in real time during gliding to optimize the flight trajectory.
[0044] Furthermore, the glider 10 also includes a tail fin 300, with the equipment bay 130 located at one end of the fuselage 100 and the tail fin 300 located at the other end of the fuselage 100.
[0045] In this embodiment, the presence of the tail fin 300 provides crucial aerodynamic stability for the glider 10. Especially during high-altitude delivery, free gliding, and landing, the tail fin 300 can effectively suppress unstable factors such as yaw and roll during flight, thereby improving flight safety and delivery accuracy.
[0046] Furthermore, there are multiple mounting sections 120 and multiple wings 200, and the mounting shafts 210 of the multiple wings 200 are mounted on the multiple mounting sections 120 in a one-to-one correspondence.
[0047] In this embodiment, the correspondence between the multiple wings 200 and the multiple mounting parts 120 ensures that each wing 200 can independently complete the deployment, retraction, and detachable connection with the fuselage 100, which has significant advantages in practical applications. For example, when the glider 10 is loaded inside the transport aircraft 20, the multiple wings 200 can be in a retracted state and fixed to their respective mounting parts 120, thereby maintaining the compact shape of the fuselage 100; after being launched into the air, each wing 200 can deploy synchronously or in stages, quickly forming a complete aerodynamic shape to support stable gliding flight.
[0048] Furthermore, multiple mounting parts 120 are located on the top of the body 100 and are arranged sequentially at intervals along the length of the body 100.
[0049] In this embodiment, the multiple mounting parts 120 are arranged at intervals along the length of the fuselage 100, so that each wing 200 can form a lifting surface distribution with a certain spacing when it is deployed. This distribution helps to optimize the airflow organization of the glider 10 during flight, reduce aerodynamic interference between adjacent wings 200, and improve the overall lift-to-drag ratio.
[0050] In detail, the wing bodies 220 of the multiple wings 200 are all located on top of the fuselage 100 in the retracted state.
[0051] In this embodiment, by uniformly setting the wing bodies 220 of multiple wings 200 on the top of the fuselage 100 in the retracted state, the spatial adaptability and operational convenience of the glider 10 during the transportation and delivery phase are effectively improved, while providing structural support for the rapid establishment of the subsequent flight state.
[0052] Furthermore, when the multiple wings 200 are in the retracted state, the wing bodies 220 of two adjacent wings 200 are staggered and stacked in the height direction.
[0053] In this embodiment, the wing bodies 220 of multiple wings 200 are staggered and stacked in the height direction. This means that when the wings 200 are in a folded state, their wing bodies 220 are not completely parallel to each other on the same plane, but are partially overlapping and staggered vertically. This arrangement effectively reduces the height profile of the glider 10 in transport mode without changing the overall volume of the wing bodies 220, making it easier to adapt to standard cargo hold sizes or loading requirements in confined spaces. Specifically, the staggered arrangement of the wing bodies 220 between adjacent wings 200 reduces the waste of vertical gaps between the wing bodies 220, while avoiding sudden increases in local thickness caused by completely flat wing bodies 220, thus achieving a flatter and more compact external shape overall.
[0054] Specifically, there are two mounting parts 120 and two wings 200. The two mounting parts 120 are located at the top ends of the fuselage 100, and the mounting shafts 210 of the two wings 200 are respectively set in the two mounting parts 120.
[0055] Furthermore, such as Figure 3 As shown, this utility model embodiment also provides a flight vehicle 1, including a transport aircraft 20 and a glider 10 as described above. The transport aircraft 20 includes a delivery compartment 21, and a door 22 is provided at the tail of the delivery compartment 21 for opening the delivery compartment 21 to deliver the glider 10.
[0056] In this embodiment, after arriving at the predetermined delivery area, the transport aircraft 20 can open the tail door 22 of the delivery compartment 21 according to the flight altitude, speed, and mission requirements, and smoothly push the glider 10 outside the compartment via an internal rail or release mechanism. After detaching from the transport aircraft 20, the glider 10 can quickly deploy its wings 200 and enter gliding flight mode, thereby achieving precise delivery to the target area. This delivery method not only avoids the transport aircraft 20 entering high-risk areas to perform landing or low-altitude delivery missions, but also significantly improves the safety and flexibility of the terminal delivery operation.
[0057] In summary, this utility model provides a glider 10 and a flight vehicle 1. When the glider 10 is in the transport or delivery preparation stage, the wing body 220 can be configured to a retracted state to reduce the occupation of transport space. When the glider 10 is delivered into the air, the wing body 220 can be deployed to the state required for flight, thereby achieving autonomous gliding flight. When the glider 10 is only in the transport state and has no delivery mission, the retracted wings 200 can be placed in the storage compartment 110 for storage, further reducing the volume occupied by the glider 10. It can be seen that the glider 10 provided in this embodiment has a simple structure, is easy to install and maintain. By reasonably configuring the structure of the fuselage 100 and the shape of the wings 200, not only is the space utilization rate of the glider 10 improved, but its mission adaptability and delivery efficiency are also enhanced, thereby achieving the goal of efficient and low-cost end-point material delivery. In addition, the glider 10 flies by gliding, so there is no need to install a power unit, further reducing the manufacturing cost of the glider 10.
[0058] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.
Claims
1. A glider, characterized in that, include: The fuselage is provided with a accommodating compartment and an installation section, the accommodating compartment being used to accommodate cargo or wings; The wing includes a mounting shaft and two wing bodies, both of which are movably mounted on the mounting shaft. The wing bodies have an extended state and a retracted state. The mounting shaft is detachably mounted on the mounting section. The wing is used to be housed in the accommodating compartment in the retracted state, or to be mounted on the mounting section in the retracted or extended state.
2. The glider according to claim 1, characterized in that, The glider also includes a drive mechanism, and the fuselage is also provided with an equipment compartment. The drive mechanism is located in the equipment compartment and is used to drive the wings to be in an extended or retracted state, or to adjust the attitude of the wing body when the wings are in an extended state.
3. The glider according to claim 2, characterized in that, The glider also includes a tail fin, the equipment compartment is located at one end of the fuselage, and the tail fin is located at the other end of the fuselage.
4. The glider according to claim 1, characterized in that, There are multiple mounting parts and multiple wings, and the mounting shafts of the multiple wings are mounted on the multiple mounting parts in a one-to-one correspondence.
5. The glider according to claim 4, characterized in that, Multiple mounting parts are located on the top of the body and are arranged at intervals along the length of the body.
6. The glider according to claim 4, characterized in that, In the retracted state, the wing bodies of all of the wings are located on top of the fuselage.
7. The glider according to claim 6, characterized in that, In the retracted state, the wings of two adjacent wings are staggered and stacked in the height direction.
8. The glider according to claim 1, characterized in that, The number of mounting parts and the number of wings are both two. The two mounting parts are located at the top ends of the fuselage, and the mounting shafts of the two wings are respectively disposed at the two mounting parts.
9. The glider according to claim 2, characterized in that, The glider also includes a control module, which is located in the equipment compartment. The control module is used to control the drive mechanism to drive the wings to the retracted state, the deployed state, or to adjust their attitude.
10. An airborne vehicle, characterized in that, The invention includes a transport aircraft and a glider as described in any one of claims 1-9, wherein the transport aircraft includes a delivery compartment with a door at the rear of the delivery compartment for opening the delivery compartment to deliver the glider.