CN-122009486-A - Variable configuration aircraft

CN122009486ACN 122009486 ACN122009486 ACN 122009486ACN-122009486-A

Abstract

The invention provides a variable configuration aircraft. The utility model provides a variable configuration aircraft, including two parallel arrangement's water conservancy diversion post, two fixed mounting has a plurality of link between the water conservancy diversion post, be equipped with folding mechanism in the water conservancy diversion post, folding mechanism's one end fixed mounting has the lift screw, two openings have all been seted up to the one side that the water conservancy diversion post kept away from each other, folding mechanism is used for with the lift screw is followed corresponding the opening withdraws the back and shifts out, the one end of water conservancy diversion post is equipped with under water propulsion screw. The variable-configuration aircraft provided by the invention has the advantages of ingenious structural design, reliable mode conversion, high space utilization rate and strong function expansibility.

Inventors

LIU FUXIANG
ZHEN HONGPO
MO BO

Assignees

北京理工大学

Dates

Publication Date: 20260512
Application Date: 20260407

Claims (10)

1. A variable configuration aircraft, comprising: Two parallel arrangement's water conservancy diversion post, two fixed mounting has a plurality of link between the water conservancy diversion post, be equipped with folding mechanism in the water conservancy diversion post, folding mechanism's one end fixed mounting has the lift screw, two openings have all been seted up to one side that the water conservancy diversion post kept away from each other, folding mechanism is used for with the lift screw is followed corresponding the opening withdraws the back and shifts out, the one end of water conservancy diversion post is equipped with the underwater propulsion screw.
2. The variable configuration aircraft of claim 1, wherein the flow post is hollow and both ends of the flow post are tapered.
3. The variable configuration aircraft of claim 1, wherein the folding mechanism comprises a rotating seat fixedly mounted in the guide post, a rotating rod is rotatably mounted at the top of the rotating seat, a rotating ring is fixedly sleeved on the outer side of the rotating rod, one end of a connecting rod is fixedly mounted on one side of the rotating ring, the lifting propeller is connected with the other end of the connecting rod, a first motor is fixedly mounted in the guide post, a first gear is fixedly mounted on an output shaft of the first motor, a second gear is fixedly sleeved on the outer side of the rotating rod, and the second gear is meshed with the first gear.
4. The variable configuration aircraft according to claim 2, wherein the other end of the connecting rod is provided with an angle adjustment mechanism for adjusting the tilt angle of the lift screw.
5. The variable configuration aircraft of claim 4, wherein the angle adjustment mechanism comprises a mounting groove formed in the other end of the connecting rod, a second motor is fixedly mounted in the mounting groove, a mounting block is fixedly mounted on an output shaft of the second motor, and one end of the mounting block, which is far away from the second motor, extends out of the mounting groove and is fixedly connected with the outer wall of the lifting propeller.
6. The variable configuration aircraft of claim 5, wherein the mounting block outer side retaining sleeve is provided with a bearing, an outer wall of the bearing being fixedly connected with an inner wall of the mounting groove.
7. The variable configuration aircraft of claim 1, wherein a blocking mechanism is provided within the flow post for blocking the opening when the lift screw is fully retracted within the flow post.
8. The variable configuration aircraft of claim 7, wherein the plugging mechanism comprises an inner gear ring rotatably mounted in the guide post, the inner gear ring is located at the center of the guide post, connecting pieces are fixedly mounted on two sides of the inner gear ring, plugging pieces are fixedly mounted on one side, away from the inner gear ring, of the connecting pieces, a third motor is fixedly mounted on the inner wall of the guide post, a third gear is fixedly mounted on an output shaft of the third motor, and the third gear is meshed with the inner gear ring.
9. The variable configuration aircraft of claim 1, wherein the blocking tab is in rotational sealing connection with an inner wall of the flow post.
10. The variable configuration aircraft of claim 1 wherein the connector frame is hollow.

Description

Variable configuration aircraft Technical Field The invention relates to the technical field of aircrafts, in particular to a variable-configuration aircraft. Background The cross-medium aircraft, namely equipment capable of flying in the air and diving under water, has wide application prospect in the fields of military reconnaissance, resource exploration, emergency rescue and the like. The craft needs to solve the contradiction between the high-efficiency flying in the air and the underwater low-resistance diving in the aspects of aerodynamic/hydrodynamic shape, propulsion mode and the like. The conventional solution often adopts a mode of combining a fixed rotor with an independent underwater propeller, and when underwater navigation is performed, the exposed rotor can increase navigation resistance and possibly become a weak point which is wound or damaged, in addition, how to ensure water tightness in the mode conversion process and prevent the cabin from water inflow is a great technical challenge. Existing partially deformable designs tend to be complex in construction, slow in conversion speed, or have shortcomings in seal reliability. Accordingly, there is a need to provide a new variable configuration aircraft that addresses the above-described technical problems. Disclosure of Invention The invention solves the technical problem of providing the variable configuration aircraft which has the advantages of ingenious structural design, reliable mode conversion, high space utilization rate and strong function expansibility. In order to solve the technical problems, the aircraft with the variable configuration comprises two parallel flow guide posts, a plurality of connecting frames are fixedly arranged between the two flow guide posts, a folding mechanism is arranged in the flow guide posts, a lifting screw is fixedly arranged at one end of the folding mechanism, two openings are formed in one sides, away from each other, of the two flow guide posts, the folding mechanism is used for retracting and moving out the lifting screw from the corresponding opening, and an underwater propulsion screw is arranged at one end of the flow guide post. Preferably, the guide post is hollow, and both ends of the guide post are tapered. Preferably, the folding mechanism comprises a rotating seat fixedly installed in the guide post, a rotating rod is installed at the top of the rotating seat in a rotating mode, a rotating ring is fixedly sleeved on the outer side of the rotating rod, one end of a connecting rod is fixedly installed on one side of the rotating ring, the lifting screw is connected with the other end of the connecting rod, a first motor is fixedly installed in the guide post, a first gear is fixedly installed on an output shaft of the first motor, a second gear is fixedly sleeved on the outer side of the rotating rod, and the second gear is meshed with the first gear. Preferably, an angle adjusting mechanism is arranged at the other end of the connecting rod, and the angle adjusting mechanism is used for adjusting the inclination angle of the lifting propeller. Preferably, the angle adjusting mechanism comprises a mounting groove formed in the other end of the connecting rod, a second motor is fixedly mounted in the mounting groove, a mounting block is fixedly mounted on an output shaft of the second motor, and one end, away from the second motor, of the mounting block extends out of the mounting groove and is fixedly connected with the outer wall of the lifting screw. Preferably, the outer side of the mounting block is fixedly sleeved with a bearing, and the outer wall of the bearing is fixedly connected with the inner wall of the mounting groove. Preferably, a blocking mechanism is arranged in the guide post and is used for blocking the opening when the lifting screw propeller is completely retracted into the guide post. Preferably, the plugging mechanism comprises an inner gear ring rotatably mounted in the guide post, the inner gear ring is positioned at the center of the guide post, connecting pieces are fixedly mounted on two sides of the inner gear ring, a plugging piece is fixedly mounted on one side, away from the inner gear ring, of the connecting pieces, a third motor is fixedly mounted on the inner wall of the guide post, a third gear is fixedly mounted on an output shaft of the third motor, and the third gear is meshed with the inner gear ring. Preferably, the blocking piece is in rotary sealing connection with the inner wall of the flow guiding column. Preferably, the connecting frame is hollow. Compared with the related art, the variable configuration aircraft provided by the invention has the following beneficial effects: The invention provides a variable-configuration aircraft, which combines a stowable lifting screw mechanism, a fixed external underwater propulsion screw and a multifunctional hollow connecting frame integrating a wiring pipeline and an equipment carrying function, so t