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CN-122009483-A - Vertical take-off and landing aircraft with adjustable duct

CN122009483ACN 122009483 ACN122009483 ACN 122009483ACN-122009483-A

Abstract

The invention provides a vertical take-off and landing aircraft with an adjustable duct, which comprises the duct arranged on front wings at two sides of the aircraft, wherein a fan is arranged at the lower part of the duct, an opening and closing assembly is arranged at the top of the duct, and the vertical take-off and landing aircraft further comprises a vertical flight mechanism arranged at the tail part of the aircraft. Through setting up the duct, can provide better lift in the vertical take off and land stage, guarantee that the control accuracy of aircraft is high effectual, guaranteed holistic lift-drag ratio simultaneously in the level flight stage of cruising.

Inventors

  • LONG YAOSONG

Assignees

  • 新域(太仓)动力科技有限公司

Dates

Publication Date
20260512
Application Date
20260228

Claims (10)

  1. 1. The vertical take-off and landing aircraft with the adjustable duct is characterized by comprising the duct (3) arranged on front wings (1) on two sides of the aircraft, a fan (301) is arranged at the lower part of the duct (3), an opening and closing assembly (2) is arranged at the top of the duct (3), and a vertical flight mechanism (5) arranged at the tail of the aircraft.
  2. 2. The vertical take-off and landing aircraft with the adjustable duct according to claim 1, wherein the opening and closing assembly (2) comprises a plurality of fan-shaped blades (6) which are uniformly arranged along the circumferential direction of the axis of the duct (3), and an arc buffer bin (4) for adjusting the state of the opening and closing assembly (2) is arranged at the upper part of the opening and closing assembly (2).
  3. 3. The vertical take-off and landing aircraft with the adjustable duct according to claim 1, wherein the circular arc buffer bin (4) comprises a bottom plate (401) and a top cover (402), the bottom plate (401) is connected with the top of the front wing (1), a second annular plate (407) is arranged in the middle of the upper side of the bottom plate (401), the fan-shaped blades (6) are hinged with the second annular plate (407), and the top cover (402) is used for providing a stable lifting space for the front wing (1).
  4. 4. The vertical take-off and landing aircraft with the adjustable duct according to claim 3, wherein a first annular plate (404) opposite to a second annular plate (407) is arranged in the middle of the lower side of the top cover (402), the inner diameter of the first annular plate (404) is larger than that of the second annular plate (407), the second annular plate (407) is hinged with the fan-shaped blade (6) through an adjusting ring (7), a locking ring (8) and an ejector rod (11), a vertical plate (603) is arranged at the lower part of the fan-shaped blade (6), a second through groove (408) is formed in the top of the second annular plate (407), mounting holes (409) are formed in two sides of the second through groove (408), and a first inserting rod (9) is arranged in the vertical plate (603) in the mounting holes (409) in a penetrating mode.
  5. 5. The vertical take-off and landing aircraft with the adjustable duct according to claim 4, wherein the first annular plate (404) is in threaded connection with the adjusting ring (7), the adjusting ring (7) comprises a toothed ring (701), a transition ring (702) and a clamping ring (703) which are arranged from top to bottom, the locking ring (8) is rotatably arranged on the clamping ring (703), and two sides of the ejector rod (11) are respectively hinged with the locking ring (8) and the fan-shaped blades (6).
  6. 6. The vertical take-off and landing aircraft with the adjustable duct according to claim 5, wherein a limiting opening (704) is formed between the transition ring (702) and the clamping ring (703), and matched external threads (405) and internal threads (705) are respectively arranged on the inner sides of the first annular plate (404) and the toothed ring (701).
  7. 7. The vertical take-off and landing aircraft with the adjustable duct according to claim 5, wherein the lock ring (8) comprises two opposite clamping ring plates (801) which are arranged oppositely, clamping grooves (802) are formed in the inner sides of the opposite clamping ring plates (801), the clamping grooves (802) are sleeved on the outer sides of the transition rings (702), vertical plates (803) are arranged at the end parts of the opposite clamping ring plates (801), and the two vertical plates (803) are connected through the second inserting rod (10).
  8. 8. The vertical take-off and landing aircraft with the adjustable duct according to claim 5, wherein a plurality of hinge seats (804) are arranged at the lower part of the lock ring (8) along the circumferential direction, mounting ports (805) are arranged in the middle of the hinge seats (804), avoidance grooves (601) are formed in one side of the fan-shaped blades (6), straight extension plates (602) are symmetrically arranged at two sides of the avoidance grooves (601), the hinge seats (804) and the straight extension plates (602) are hinged with the ejector rods (11) through first inserting rods (9), and first through grooves (406) for avoiding the ejector rods (11) are further formed in the first annular plate (404).
  9. 9. The vertical take-off and landing aircraft with the adjustable culvert as claimed in claim 5, wherein the inner side of the bottom plate (401) is provided with a ring groove (403), the ring groove (403) is provided with a motor (12), the output shaft of the motor (12) is provided with a gear (13), and the gear (13) is in meshed connection with the toothed ring (701).
  10. 10. The vertical take-off and landing aircraft with the adjustable duct according to claim 8, wherein a plurality of adjusting grooves (410) are formed in the top cover (402) in a penetrating mode along the circumferential direction, sealing elastic pieces (14) are arranged on the inner sides of the adjusting grooves (410), the sealing elastic pieces (14) are wrapped on fixing portions (1401) on two sides, the fixing portions (1401) are fixed on the inner sides of the top cover (402), elastic portions (1402) are arranged between the two fixing portions (1401) and used for shielding the adjusting grooves (410), hook plates (1403) are arranged on the inner sides of the elastic portions (1402), third bolts (16) are further arranged on the straight extending plates (602) in a penetrating mode, and the hook plates (1403) are connected with the third bolts (16) through pull ropes (15).

Description

Vertical take-off and landing aircraft with adjustable duct Technical Field The invention relates to the technical field of aircrafts, in particular to a vertical take-off and landing aircraft with an adjustable duct. Background In aircraft (particularly eVTOL) employing ducted fans as lift or propulsion components, the open inlet of the duct during non-operational periods (e.g., cruising) can create significant additional drag (parasitic drag) and disrupt the airflow continuity across the body surface, severely impacting cruising efficiency. The current mainstream solution to this problem includes mechanical hatches, which employ an integral or split hatch for physical shielding. However, the structure is heavy, the space occupied by the actuating mechanism is large, and a pure fairing is formed after the actuating mechanism is closed, so that only passive drag reduction can be realized, and active beneficial influence on air flow cannot be generated; the shutter type adopts a plurality of rotatable blades. Although the air inflow can be regulated, the blades are usually flat plates, the pneumatic efficiency is low, the sealing performance is poor, the surface smoothness cannot be guaranteed when the blades are completely closed, and the telescopic/retractable duct can fundamentally solve the problems, but the system is extremely complex, and the challenges of weight and reliability are huge. The common problem with the prior art is that the functionality is single (only "on" and "off" are implemented), the aerodynamic benefits are limited, and the balance between mechanical complexity, weight and reliability is difficult. Therefore, there is a need for a bypass intelligent shelter that is lightweight, highly reliable, and has both passive drag reduction and active flow control capabilities. A ducted fan is a component that provides an effective lift for an aircraft, but if it is desired to ensure that a large upward pull is provided to achieve a hover function, the length of the duct will be long enough while still ensuring pressure stability. The Chinese patent document CN 101857086A describes a double-duct vertical take-off and landing unmanned aerial vehicle, but the structure still has the problem that the duct can not be opened or closed according to the requirement and is limited in length, and the lift force is limited during flight. Disclosure of Invention The invention provides a vertical take-off and landing aircraft with an adjustable duct, which solves the technical problems of limited lift force and unstable lift force of the aircraft. In order to solve the technical problems, the vertical take-off and landing aircraft with the adjustable duct comprises the duct arranged on the front wings at two sides of the aircraft, a fan is arranged at the lower part of the duct, an opening and closing assembly is arranged at the top of the duct, and the vertical take-off and landing aircraft further comprises a vertical flight mechanism arranged at the tail part of the aircraft. In the preferred scheme, open and close the subassembly and include a plurality of fan-shaped blades that evenly set up along the axis circumference of duct, open and close the upper portion of subassembly and be provided with the circular arc surge bin that is used for adjusting the subassembly state of opening and close. In the preferred scheme, the circular arc surge bin comprises a bottom plate and a top cover, the bottom plate is connected with the top of the front wing, a second annular plate is arranged in the middle of the upper side of the bottom plate, the fan-shaped blades are hinged with the second annular plate, and the top cover is used for providing a stable lifting space for the front wing. In the preferred scheme, the downside middle part of top cap is provided with the first annular plate relative with the second annular plate, and the internal diameter of first annular plate is greater than the second annular plate, and the second annular plate passes through adjusting ring, lock ring and ejector pin and fan-shaped blade and articulates, and fan-shaped blade's lower part is provided with the riser, and second annular plate top is provided with the second through groove, and second through groove both sides are provided with the mounting hole, and first inserted bar wears to establish in riser and mounting hole. In the preferred scheme, first annular plate and adjusting ring threaded connection, the adjusting ring includes ring gear, transition ring and the snap ring that from the top down set up, and the rotatable setting of lock ring is on the snap ring, and the both sides of ejector pin are articulated with lock ring and fan-shaped blade respectively. In the preferred scheme, form spacing mouth between transition ring and the snap ring, the inboard of first crown plate and ring gear is provided with assorted external screw thread and internal screw thread respectively. In the preferred scheme, the lock ring i