Freight unmanned aerial vehicle control surface rotation limiting structure
By designing the limit plane of the limit rib strip in the rotation limit structure of the cargo unmanned aerial vehicle rudder surface, the structural impact damage, weight increase and structural complexity problems in the existing aircraft rudder surface limit mode are solved, and simplification is achieved Structure, damage reduction and cost reduction effects.
Patent Information
- Application Number
- CN202421128075.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-22
- Publication Date
- 2025-02-11
- Estimated Expiration
- 2034-05-22
AI Technical Summary
The existing aircraft rudder surface limiting method has problems such as structural impact damage, weight increase and structural complexity, resulting in high processing costs.
Design a rotating limit structure of the rudder surface of the freight unmanned aerial vehicle. By setting limit bars on the elevator joint and the horizontal stabilization surface support joint, the limit plane of the limit bars faces between the rudder surface and the horizontal stabilization surface The rotation limits the position, simplifying the structure and realizing the rotation limit function of the rudder surface.
The structure achieves limiting through the rudder joint itself, improves the stress form, reduces structural damage, simplifies the structure, reduces the number and cost of parts, and improves the limiting capacity.
Smart Images
Figure CN222452519U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the field of aviation aircraft structure design, in particular to a cargo unmanned aerial vehicle rudder surface rotation limiting structure. Background Art
[0002] Generally, there are two main ways to limit the movement of aircraft rudders. One is to install a limit screw at the rotation position of the rudder and to cooperate with the limit bracket installed at the corresponding position of the fuselage. In the actual limiting process, the screw touches the limit bracket through point contact to achieve the purpose of limiting. The other is to install a limit support on the tail wing and a limit block at the position corresponding to the rudder beam. In the actual limiting process, the position is limited by the impact of the support and the limit block. The above two methods are prone to cause certain impact damage to the structure after long-term use. At the same time, whether it is a limit screw installed on a specific mounting seat, a separate limit support, or a limit bracket and limit block installed at the corresponding position of the fuselage, such a large number of parts will lead to an increase in weight. At the same time, the structure is more complicated and the processing cost is higher. Utility Model Content
[0003] In view of the above technical problems, the utility model provides a cargo drone rudder rotation limiting structure. The cargo drone rudder rotation limiting structure has a simplified structure and can realize the rudder rotation limiting function.
[0004] In order to achieve the above technical objectives, the utility model provides the following technical solutions:
[0005] A cargo UAV rudder rotation limiting structure, the limiting structure comprising: an elevator right joint, an elevator left joint, a horizontal stabilizer right support joint, and a horizontal stabilizer left support joint;
[0006] The right elevator joint and the left elevator joint are respectively arranged at two ends of the front beam of the elevator; the right horizontal stabilizer support joint and the left horizontal stabilizer support joint are both connected to the horizontal stabilizer of the aircraft;
[0007] The right joint of the elevator and the right support joint of the horizontal stabilizer are rotatably connected, and the left joint of the elevator and the left support joint of the horizontal stabilizer are rotatably connected;
[0008] Limiting ribs are arranged on the elevator right joint and the elevator left joint, and limiting planes are arranged on the limiting ribs; the limiting ribs limit the rotation between the elevator and the horizontal stabilizer based on the limiting planes.
[0009] Furthermore, the right elevator joint and the left elevator joint have the same structure, both comprising a base, a connecting ear piece arranged on the top of the base, and two limiting ribs respectively arranged on both sides of the connecting ear piece.
[0010] Furthermore, the two limiting ribs have the same structure and are symmetrically arranged on both sides of the connecting ear piece; each limiting rib includes an arc-shaped groove and a first limiting plane and a second limiting plane respectively connected to the upper and lower sides of the arc-shaped groove.
[0011] Furthermore, the right elevator joint and the left elevator joint are integrally machined, and the limiting ribs are ribs retained during the machining process of the right elevator joint / the left elevator joint.
[0012] Furthermore, the structures of the right support joint of the horizontal stabilizer and the left support joint of the horizontal stabilizer are the same, and both include a stabilizer connection unit for connecting to the horizontal stabilizer of the aircraft and a rotation connection unit.
[0013] Furthermore, the rotating connection unit includes two connecting ears arranged in parallel; the two connecting ears have the same shape, both including an arc-shaped protruding rotating head and a first bevel and a second bevel connected to the upper and lower sides of the arc-shaped protruding rotating head.
[0014] Furthermore, the right joint of the elevator and the left joint of the elevator are connected to the front beam of the elevator through rivets.
[0015] Furthermore, the horizontal stabilizer right support joint and the horizontal stabilizer left support joint are both connected to the aircraft horizontal stabilizer through rivets.
[0016] Furthermore, the right joint of the elevator and the right support joint of the horizontal stabilizer as well as the left joint of the elevator and the left support joint of the horizontal stabilizer are connected by a rotating pin.
[0017] The beneficial effects of the utility model are:
[0018] In the cargo UAV rudder rotation limiting structure provided by the utility model, the limiting ribs used are the ribs retained in the elevator right joint / elevator left joint during the machining process; this structure can realize the rudder rotation limiting through the rudder joint's own structure, improve the force form, reduce structural damage, and has a simple structure without requiring too many parts. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of the rotation limiting structure of the rudder surface of the cargo UAV in the embodiment of the utility model.
[0020] Figure 2 It is a partial schematic diagram of the rotation limiting structure of the rudder surface of the cargo UAV in the embodiment of the utility model.
[0021] Figure 3aIt is a schematic diagram of the rotation limiting structure when the upward deflection of the elevator reaches the limit deflection angle in the embodiment of the utility model;
[0022] Figure 3b It is a schematic diagram of the rotation limiting structure when the elevator deflects downward to a limit deflection angle in an embodiment of the utility model;
[0023] Reference numerals: 1. right joint of elevator, 2. left joint of elevator, 3. front beam of elevator, 4. right support joint of horizontal stabilizer, 5. left support joint of horizontal stabilizer, 6. rotating pin, 7. limiting rib. DETAILED DESCRIPTION
[0024] The technical solution of the utility model is further described below in conjunction with specific embodiments and drawings.
[0025] The utility model provides an embodiment of a rotation limiting structure of a rudder surface of a cargo UAV, such as Figure 1-Figure 2 As shown, the limiting structure includes: a right elevator joint 1, a left elevator joint 2, a right horizontal stabilizer support joint 4, and a left horizontal stabilizer support joint 5;
[0026] The elevator right joint 1 and the elevator left joint 2 are respectively arranged at the two ends of the elevator front beam 3; the horizontal stabilizer right support joint 4 and the horizontal stabilizer left support joint 5 are both connected to the aircraft horizontal stabilizer (not shown in the figure);
[0027] The elevator right joint 1 and the horizontal stabilizer right support joint 4 are rotatably connected, and the elevator left joint 2 and the horizontal stabilizer left support joint 5 are rotatably connected;
[0028] Limiting ribs are arranged on the elevator right joint 1 and the elevator left joint 2, and limiting planes are arranged on the limiting ribs; the limiting ribs limit the rotation between the elevator and the horizontal stabilizer based on the limiting planes.
[0029] In this embodiment, the elevator right joint 1 and the elevator left joint 2 have the same structure, and both include a base, a connecting ear piece arranged on the top of the base, and two limiting ribs respectively arranged on both sides of the connecting ear piece;
[0030] The two limiting ribs have the same structure and are symmetrically arranged on both sides of the connecting ear; each limiting rib includes an arc-shaped groove and a first limiting plane and a second limiting plane respectively connected to the upper and lower sides of the arc-shaped groove. The connecting ear is provided with a connecting hole for connecting to the horizontal stabilizer support joint.
[0031] In this embodiment, the right elevator joint 1 and the left elevator joint 2 are integrally processed, and the limiting ribs are ribs retained during the machining process of the right elevator joint / the left elevator joint.
[0032] In this embodiment, the horizontal stabilizer right support joint 4 and the horizontal stabilizer left support joint 5 have the same structure, and both include a stabilizer connection unit for connecting with the aircraft horizontal stabilizer and a rotation connection unit;
[0033] The rotating connection unit comprises two parallel connecting lugs; the two connecting lugs have the same shape and both comprise a circular arc-shaped protruding rotating head and a first bevel and a second bevel connected to the upper and lower sides of the circular arc-shaped protruding rotating head;
[0034] The limiting rib 7 in the utility model has two limiting planes on the left and right. Since the elevator swings up and down, the angle of the limiting plane of the rib can be set according to the different limit deflection angles of the elevator swinging up and down; when the elevator rotates to the limit angle, the limiting plane of the limiting rib 7 fits with the first beveled edge / the second beveled edge of the ear piece in the horizontal stabilizer support joint, thereby realizing the limiting function of the elevator rudder surface.
[0035] The two connecting ears of the rotating connection unit are penetrated with connecting holes; when connecting, the rotating pin 6 passes through the connecting hole on the connecting ear of the horizontal stabilizer support joint and the connecting hole on the connecting ear of the elevator joint, so that the horizontal stabilizer support joint and the elevator joint can be rotatably connected.
[0036] In this embodiment, the right elevator joint 1 and the left elevator joint 2 are connected to the elevator front beam 3 through rivets; specifically, the web of the elevator front beam provides a countersunk hole for the elevator joint, which is connected and fixed to the elevator joint through fasteners.
[0037] In this embodiment, the horizontal stabilizer right support joint 4 and the horizontal stabilizer left support joint 5 are both connected to the aircraft horizontal stabilizer through rivets.
[0038] In this embodiment, the elevator right joint 1 and the horizontal stabilizer right support joint 4, as well as the elevator left joint 2 and the horizontal stabilizer left support joint 5 are connected via a rotating pin 6. Specifically, the elevator right joint 1 and the horizontal stabilizer right support joint 4 are connected via a first rotating pin; the elevator left joint 2 and the horizontal stabilizer left support joint 5 are connected via a first rotating pin.
[0039] In the cargo drone rudder rotation limiting structure provided by the utility model, the elevator joint is a single-ear joint structure, and the limiting plane of the limiting rib and the ear of the horizontal stabilizer support joint produce surface contact when the elevator rotates to a certain angle, producing a limiting effect. In the cargo drone rudder rotation limiting structure provided by the utility model, the horizontal stabilizer support joint is a double-ear joint structure that cooperates with the elevator joint.
[0040] The cargo drone rudder rotation limiting structure provided by the utility model utilizes the self-ribs of the elevator joint connected to the horizontal stabilizer support joint to achieve the limiting purpose. The limiting ribs of the elevator joint can improve its own strength and stiffness characteristics on the one hand, and on the other hand, the limiting plane of the ribs rotates synchronously with the elevator. When the elevator rotates to the limit angle, it contacts the ear piece of the horizontal stabilizer support joint to complete the limiting; wherein, the angle between the limiting plane of the elevator joint and the hypotenuse of the ear piece of the horizontal stabilizer joint is the elevator limit deflection angle. The elevator joint is fixed on the front beam of the elevator, and the horizontal stabilizer support joint is fixed at the corresponding position of the horizontal stabilizer of the aircraft. The two joints are connected by a rotating pin, and the center line of the rotating pin coincides with the rotation axis of the elevator. The elevator joint is a single-ear joint, which has two left and right reinforcing ribs that are symmetrical to each other. The vertical surfaces of the two left and right ribs correspond one by one to the two ears of the horizontal stabilizer support joint. When rotating upward or downward to the extreme angles, there are two limit surfaces that fit with the ears, and the limiting ability is strong.
[0041] The cargo UAV rudder rotation limit structure provided by the utility model cleverly designs the limit surface on the side of the single ear of the rudder joint, so that the limiting mode is changed from point contact to surface contact between the horizontal stabilizer joint and the rudder joint, and the structural characteristics of the joint itself are used to achieve the limiting purpose. There is no need to design other supports or limit blocks, which reduces the number of parts, improves the limiting capacity and reduces the cost; the limiting contact area is large, the limiting capacity is strong, and the structure can be integrated into an integrated machine, which is convenient for subsequent disassembly and maintenance.
[0042] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. For ordinary technicians in this field, they can still modify or transform the technical solutions described above, which all fall within the scope of protection of the present invention.
Claims
1. A cargo drone rudder rotation limit structure, characterized in that: The limiting structure comprises: a right elevator joint (1), a left elevator joint (2), a right horizontal stabilizer support joint (4), and a left horizontal stabilizer support joint (5); The elevator right joint (1) and the elevator left joint (2) are respectively arranged at two ends of the elevator front beam (3); the horizontal stabilizer right support joint (4) and the horizontal stabilizer left support joint (5) are both connected to the horizontal stabilizer of the aircraft; The elevator right joint (1) and the horizontal stabilizer right support joint (4) are rotatably connected, and the elevator left joint (2) and the horizontal stabilizer left support joint (5) are rotatably connected; Limiting ribs are arranged on the elevator right joint (1) and the elevator left joint (2), and limiting planes are arranged on the limiting ribs; the limiting ribs limit the rotation between the elevator and the horizontal stabilizer based on the limiting planes.
2. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The elevator right joint (1) and the elevator left joint (2) have the same structure, both comprising a base, a connecting ear piece arranged on the top of the base, and two limiting ribs respectively arranged on both sides of the connecting ear piece.
3. According to claim 2, a cargo drone rudder rotation limiting structure is characterized in that: The two limiting ribs have the same structure and are symmetrically arranged on both sides of the connecting ear piece; each limiting rib includes an arc-shaped groove and a first limiting plane and a second limiting plane respectively connected to the upper and lower sides of the arc-shaped groove.
4. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The right elevator joint (1) and the left elevator joint (2) are integrally machined, and the limiting ribs are ribs retained during the machining process of the right elevator joint / the left elevator joint.
5. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The horizontal stabilizer right support joint (4) and the horizontal stabilizer left support joint (5) have the same structure, and both comprise a stabilizer connection unit for connecting with the aircraft horizontal stabilizer and a rotation connection unit.
6. According to claim 5, a cargo drone rudder rotation limiting structure is characterized in that: The rotating connection unit includes two parallel connecting ears; the two connecting ears have the same shape, and both include an arc-shaped protruding rotating head and a first bevel and a second bevel connected to the upper and lower sides of the arc-shaped protruding rotating head.
7. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The elevator right joint (1) and the elevator left joint (2) are connected to the elevator front beam (3) through rivets.
8. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The horizontal stabilizer right support joint (4) and the horizontal stabilizer left support joint (5) are both connected to the aircraft horizontal stabilizer via rivets.
9. According to claim 1, a cargo drone rudder rotation limiting structure is characterized in that: The elevator right joint (1) and the horizontal stabilizer right support joint (4) as well as the elevator left joint (2) and the horizontal stabilizer left support joint (5) are all connected via a rotating pin (6).