Novel composite-configuration tilting rotorcraft
By designing a locking structure in the compound configuration tiltrotor aircraft, including a U-shaped fixed base, fixed guide column, fixed block, sealing connector plug and connecting sleeve, the problem of unstable tail fin connection is solved, and higher flight stability and service life are achieved.
Patent Information
- Application Number
- CN202520082675.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-14
- Publication Date
- 2025-12-05
- Estimated Expiration
- 2035-01-14
AI Technical Summary
During flight, the tail section of existing compound tiltrotor aircraft is not securely connected and is easily affected by air resistance, inertial forces and fuselage vibration, resulting in severe vibration and affecting flight stability.
Design a locking structure including a U-shaped fixing seat, a fixing guide post, a fixing block, a sealing connector, a connecting sleeve, and a connecting post. Through the combination of these components, a stable connection between the vertical tail fin and the horizontal tail fin is ensured, and the sealing connector made of highly elastic rubber material provides a buffering and vibration reduction effect.
It improves the flight stability and service life of tiltrotor aircraft. The locking structure design reduces vibration of the tail connection, enhancing overall flight stability and structural robustness.
Smart Images
Figure CN223631790U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to rotorcraft technical field, concretely is a novel compound configuration tilting rotorcraft. BACKGROUND
[0002] Rotorcraft is a kind of special aircraft, it utilizes the relative airflow of forward flight to blow the rotor self-rotation to generate lift, has the characteristics such as short take-off and landing distance, low-speed low-altitude flight capability, easy to conceal, has wide application prospect in military field.
[0003] Compound configuration tilting rotorcraft is a kind of new aircraft that combines fixed-wing aircraft and helicopter, and the key lies in the conversion of rotor tilting system components, and different flight attitudes are realized by adjusting the vertical or parallel of side wing to ground.
[0004] The vertical tail of compound configuration tilting rotorcraft is mainly used to control the yaw attitude of aircraft, provides directional stability, and the horizontal tail is mainly used to control the pitch attitude of aircraft, provides stability during flight.
[0005] Therefore, the application provides a novel compound configuration tilting rotorcraft, which ensures the connection stability of vertical tail and horizontal tail by setting locking structure, optimizes the structure design to reduce vibration, and improves the flight stability and service life of the whole compound configuration tilting rotorcraft. Utility model content
[0006] In order to make up for the deficiency of prior art, solve the technical problem that the rotorcraft in the background art is usually subjected to air resistance, inertia force and fuselage vibration and other loads during flight, the connection between the vertical tail and the horizontal tail is easily affected and unstable under the impact of multiple loads, even serious vibration occurs, which affects the flight stability of the tilting rotorcraft, the utility model provides a novel compound configuration tilting rotorcraft.
[0007] The utility model discloses a novel composite configuration tilting rotorcraft, including rotorcraft main part, the both sides of rotorcraft main part are installed with rotor tilting device main part, the tail of rotorcraft main part is installed with tail shaft, the one end of tail shaft is installed with horizontal tail, the top of horizontal tail is provided with fixed groove and mounting groove, the top of horizontal tail is provided with vertical tail, the inside of vertical tail is provided with locking structure, the locking structure includes U-shaped fixed seat, fixed guide column, fixed block, sealed connecting plug, connecting sleeve and connecting column, the locking structure is used for cooperation fixed groove installation vertical tail.
[0008] Preferably, the U-shaped fixed seat is installed in the inner cavity bottom wall of the vertical tail, two groups of the fixed guide columns are integrally formed and symmetrically arranged on the top of the U-shaped fixed seat, two groups of the fixed blocks are provided with guide grooves in the inside, and the two groups of fixed blocks are respectively clamped and installed on the outer periphery of the two groups of fixed guide columns through the guide grooves, the sealed connecting plug is installed on the opposite inner sides of the two groups of fixed blocks, the connecting sleeve is installed on the bottom of the vertical tail, and the connecting column is located in the inner cavity of the sealed connecting plug, and the bottom end of the connecting column penetrates the U-shaped fixed seat, the vertical tail and the bottom of the connecting sleeve.
[0009] Preferably, the top of the U-shaped fixed seat is provided with two groups of webs, and the inside of the mounting groove is fixedly provided with a support.
[0010] Preferably, the bottom end of the vertical tail is provided with wing protection plates on the both sides, and the outer periphery of the two side round plates of the U-shaped fixed seat is provided with a sealing cover.
[0011] Preferably, the bottom of the vertical tail is provided with a short column, and the short column is embeddedly installed in the top fixed cylinder of the support.
[0012] Preferably, a fixing sleeve is installed in the fixed groove, and the bottom end of the connecting column is installed in the fixing sleeve.
[0013] The utility model discloses the beneficial effect lies in:
[0014] 1, the utility model discloses being provided with locking structure, wherein, the web is used for reinforcing the both sides round plate of U-shaped fixed seat, and the fixed guide column is fixed with the fixed block cooperation, and the connecting column penetrates the bottom wall of vertical tail and the inside of connecting sleeve through sealed connecting plug, and the sealed connecting plug is located in the opposite inner side of two groups of symmetric fixed blocks, thereby through the installation of sealed connecting plug, for the upper part of connecting column is firm, and the sealed connecting plug selects the rubber material of high elasticity, has certain buffering effect, for the upper installation position of connecting column is protected, and the middle position of connecting column is reinforced simultaneously by using connecting sleeve, improves the flight stability and service life of the whole composite configuration tilting rotorcraft.
[0015] 2, The utility model discloses a locking structure is located inside vertical tail, is used for installing vertical tail with fixed groove cooperation, and the bottom end of the connecting column on the vertical tail is installed in the fixed groove on the horizontal tail through the fixed sleeve, and the stub on the bottom of the vertical tail is fixedly installed in the installation slot on the horizontal tail through the support, and through the cooperation and connection of the connecting column and the stub, the stability of the installation of the vertical tail is ensured. BRIEF DESCRIPTION OF DRAWINGS
[0016] The drawings described herein are used to provide further understanding of the utility model and constitute a part of the application. The illustrative embodiments of the utility model and their descriptions are used to explain the utility model and do not constitute improper limitation on the utility model.
[0017] In the drawings:
[0018] Figure 1 It is the three-dimensional structure schematic diagram of the rotorcraft main body of the utility model;
[0019] Figure 2 It is the tail wing three-dimensional structure split schematic of the utility model Figure One ;
[0020] Figure 3 It is the tail wing three-dimensional structure split schematic of the utility model Figure Two ;
[0021] Figure 4 It is the tail wing inside locking structure schematic of the utility model;
[0022] Figure 5 It is the locking structure split schematic of the utility model;
[0023] Figure 6 It is the locking structure split schematic of the utility model;
[0024] In the drawing: 1, rotorcraft main body; 101, rotor tilt device main body; 2, tail shaft; 3, horizontal tail; 301, fixed groove; 302, installation slot; 4, vertical tail; 401, stub; 402, U-shaped fixed seat; 403, fixed guide column; 404, fixed block; 405, sealed connecting plug; 406, connecting sleeve; 407, connecting column; 408, web; 409, wing board; 410, sealing cover; 5, fixed sleeve; 6, support. DETAILED DESCRIPTION
[0025] With reference to the drawings and embodiments of the present application, the technical solutions in the embodiments of the present application will be described clearly and completely. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.
[0026] As shown in the accompanying drawings Figures 1-6 A novel composite configuration tilt rotor aircraft, comprising a rotor aircraft body 1, a rotor tilt device body 101 is installed on both sides of the rotor aircraft body 1, a tail shaft 2 is installed at the tail of the rotor aircraft body 1, a horizontal tail 3 is installed at one end of the tail shaft 2, a vertical tail 4 is arranged at the top of the horizontal tail 3, the rotor aircraft body 1 is driven to start working by a driving machine, the attitude of the rotor tilt device body 101 is adjusted to change the flight attitude, and the horizontal tail 3 and the vertical tail 4 cooperate to control the stability of the aircraft during flight;
[0027] Further, the top of the horizontal tail 3 is provided with a fixing groove 301 and a mounting groove 302, and the inside of the vertical tail 4 is provided with a locking structure, which is composed of a U-shaped fixing seat 402, a fixing guide column 403, a fixing block 404, a sealing connecting plug 405, a connecting sleeve 406 and a connecting column 407, and is used for mounting the vertical tail 4 in cooperation with the fixing groove 301;
[0028] Further, the U-shaped fixing seat 402 is installed in the inner cavity bottom wall of the vertical tail 4, two groups of fixing guide columns 403 are integrally formed and symmetrically arranged at the top of the U-shaped fixing seat 402, two groups of fixing blocks 404 are provided with guide grooves in the inside, and the two groups of fixing blocks 404 are respectively fixedly installed in the outer periphery of the two groups of fixing guide columns 403 through the guide grooves, the sealing connecting plug 405 is installed on the opposite inner side of the two groups of fixing blocks 404, the connecting sleeve 406 is installed at the bottom of the vertical tail 4, the connecting column 407 is located in the inner cavity of the sealing connecting plug 405, and the bottom end of the connecting column 407 penetrates the U-shaped fixing seat 402, the vertical tail 4 and the bottom of the connecting sleeve 406, and two groups of web plates 408 are installed on both sides of the top of the U-shaped fixing seat 402;
[0029] Further, the web plate 408 is used for reinforcing the two side plates of the U-shaped fixing seat 402, the fixing guide column 403 and the fixing block 404 are fixedly connected, the connecting column 407 penetrates the sealing connecting plug 405 and the bottom wall of the vertical tail 4 and penetrates the inside of the connecting sleeve 406, and the sealing connecting plug 405 is located on the opposite inner side of the two groups of symmetrically arranged fixing blocks 404. Thus, through the installation of the sealing connecting plug 405, the upper part of the connecting column 407 is stabilized, the sealing connecting plug 405 is made of high-elastic rubber material, has a certain buffering and damping effect, is used for protecting the installation position of the upper part of the connecting column 407, and simultaneously reinforces the middle position of the connecting column 407 by using the connecting sleeve 406.
[0030] Further, the inside of the mounting groove 302 is fixedly mounted with a support 6, the bottom end of the vertical tail wing 4 is mounted with a wing guard plate 409, the outer periphery of the two circular plates on both sides of the U-shaped fixing seat 402 is mounted with a sealing cover 410, the bottom of the vertical tail wing 4 is mounted with a short column 401, the short column 401 is embeddedly mounted in the top fixing cylinder of the support 6, the fixing groove 301 is mounted with a fixing sleeve 5, and the bottom end of the connecting column 407 is mounted in the fixing sleeve 5;
[0031] Further, the fixing groove 301 and the mounting groove 302 are located on the horizontal center axis on the top of the horizontal tail wing 3, the bottom end of the connecting column 407 on the vertical tail wing 4 is mounted in the fixing groove 301 on the horizontal tail wing 3 through the fixing sleeve 5, the short column 401 at the bottom of the vertical tail wing 4 is fixedly mounted in the mounting groove 302 on the horizontal tail wing 3 through the support 6, and the stability of the installation of the vertical tail wing 4 is ensured through the cooperative connection of the connecting column 407 and the short column 401.
[0032] Working principle: the inside of the rotorcraft main body 1 is driven to start working through a driving machine, the attitude of the rotor tilt device main body 101 is adjusted to change the flight attitude, and the horizontal tail wing 3 and the vertical tail wing 4 cooperate to control the stability of the flight process of the aircraft; the fixing groove 301 and the mounting groove 302 are located on the horizontal center axis on the top of the horizontal tail wing 3, the locking structure is located in the inside of the vertical tail wing 4, is used for cooperating with the fixing groove 301 to install the vertical tail wing 4, the bottom end of the connecting column 407 on the vertical tail wing 4 is mounted in the fixing groove 301 on the horizontal tail wing 3 through the fixing sleeve 5, the short column 401 at the bottom of the vertical tail wing 4 is fixedly mounted in the mounting groove 302 on the horizontal tail wing 3 through the support 6, and the stability of the installation of the vertical tail wing 4 is ensured through the cooperative connection of the connecting column 407 and the short column 401.
[0033] In addition, the web plate 408 is used for reinforcing the two circular plates on both sides of the U-shaped fixing seat 402, the fixing guide column 403 cooperates with the fixing block 404 to be clamped and fixed, the connecting column 407 penetrates through the sealing connection plug 405 and the bottom wall of the vertical tail wing 4 and penetrates through the inside of the connecting sleeve 406, the sealing connection plug 405 is located on the opposite inner side of the two groups of symmetrically arranged fixing blocks 404, the upper part of the connecting column 407 is thus stabilized through the installation of the sealing connection plug 405, the sealing connection plug 405 is made of high-elastic rubber material and has a certain buffering and damping effect, is used for protecting the installation position of the upper part of the connecting column 407, and the middle position of the connecting column 407 is reinforced by using the connecting sleeve 406;
[0034] Therefore, the connection stability of the vertical tail wing 4 and the horizontal tail wing 3 is ensured through the setting of the locking structure, the structure design is optimized to reduce vibration, and the flight stability and service life of the whole composite configuration tilt rotorcraft are improved.
[0035] The basic principle, main features and advantages of the present application are shown and described above. Those skilled in the art should understand that the present application is not limited by the above examples, and the above examples and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application.
Claims
1. A novel compound configuration tilt-rotor aircraft, comprising a rotorcraft body (1), both sides of which are provided with a rotor tilting device body (101), characterized in that: The tail of the rotorcraft body (1) is provided with a tail shaft (2), one end of the tail shaft (2) is provided with a horizontal tail (3), the top of the horizontal tail (3) is provided with a fixed groove (301) and a mounting groove (302), the top of the horizontal tail (3) is provided with a vertical tail (4), the inside of the vertical tail (4) is provided with a locking structure, the locking structure comprises a U-shaped fixing seat (402), a fixing guide column (403), a fixing block (404), a sealing connecting plug (405), a connecting sleeve (406) and a connecting column (407), and the locking structure is used for cooperating with the fixed groove (301) to mount the vertical tail (4).
2. A novel compound configuration gyrodyne as claimed in claim 1, wherein: The U-shaped fixing seat (402) is installed in the inner cavity bottom wall of the vertical tail (4), two groups of the fixing guide column (403) are integrally formed and symmetrically arranged on the top of the U-shaped fixing seat (402), two groups of the fixing block (404) are internally provided with a guide groove, and two groups of the fixing block (404) are respectively clamped and mounted on the outer periphery of two groups of the fixing guide column (403) through the guide groove, the sealing connecting plug (405) is installed on the opposite inner side of the two groups of the fixing block (404), the connecting sleeve (406) is installed on the bottom of the vertical tail (4), and the connecting column (407) is located in the inner cavity of the sealing connecting plug (405), and the bottom end of the connecting column (407) penetrates the U-shaped fixing seat (402), the vertical tail (4) and the bottom of the connecting sleeve (406).
3. A novel compound configuration gyrodyne as claimed in claim 1, wherein: The top of the U-shaped fixing seat (402) is provided with two groups of web plates (408), and the inside of the mounting groove (302) is fixedly provided with a support (6).
4. A novel compound configuration gyrodyne as claimed in claim 1, wherein: The bottom of the vertical tail (4) is provided with a wing protection plate (409), and the outer periphery of the two side round plates of the U-shaped fixing seat (402) is provided with a sealing cover (410).
5. A novel compound configuration gyrodyne as claimed in claim 1, wherein: The bottom of the vertical tail (4) is provided with a short column (401), and the short column (401) is embeddedly installed in the top fixed cylinder of the support (6).
6. A novel compound configuration gyrodyne as claimed in claim 1, wherein: The fixed groove (301) is provided with a fixing sleeve (5), and the bottom end of the connecting column (407) is installed in the fixing sleeve (5).