CN-121990201-A - Aircraft and aircraft cluster thereof

Abstract

The invention relates to an aircraft and an aircraft cluster thereof, belonging to the technical field of aircrafts, and comprising an engine body, a tilting duct, an engine mechanism and a connecting device, wherein the connecting device comprises a male buckle and a female buckle which are arranged on a frame, and the male buckle and the female buckle on adjacent aircrafts realize the butt joint of the adjacent aircrafts through buckling; the invention realizes the high-efficiency conversion of the vertical take-off and landing of the aircraft and the horizontal cruising through the tilting duct arranged on the engine body and the engine mechanism arranged on the duct, has the maneuvering flexibility of the helicopter and the high-speed cruising capability of the fixed-wing aircraft, simultaneously, ensures that the adjacent aircraft can quickly and stably realize mechanical butt joint through the connecting device formed by the pin buckle and the box buckle arranged on the engine body, is convenient for the grouping connection and separation during the multi-engine collaborative operation, can also form a combined flying mode, effectively improves the load capacity, the course and the task adaptability, and provides a reliable structural basis for the modularized expansion and the cluster application.

Inventors

• ZHAO QIJUN
• LIN MUYANG
• CHEN ZHE
• SHI XIAOCHUN

Assignees

• 南京启直航空科技有限公司

Dates

Publication Date

20260508

Application Date

20260408

Claims (10)

1. 1. The utility model provides an aircraft, its characterized in that includes the organism, sets up tilting duct on the organism, set up engine mechanism on the duct and set up be used for with the connecting device of adjacent aircraft butt joint on the organism, connecting device is including setting up pin thread and the box on the frame, on the adjacent aircraft pin thread and box realize the butt joint of adjacent aircraft through the lock.
2. 2. The aircraft according to claim 1, wherein the body comprises side boxes arranged at intervals, the side boxes are connected through at least two groups of connecting rods, the side boxes and the connecting rods form a mounting cavity for mounting the duct in a surrounding mode, at least one group of male buckles and female buckles are arranged on the side portions of the side boxes, and male buckles and female buckles are respectively arranged on the end portions of the two side boxes in the same direction.
3. 3. The aircraft according to claim 1, wherein the male buckle is a protrusion with an end cambered surface, a clamping hole is formed in a side wall of the protrusion, the female buckle is a groove for the protrusion to be inserted into, a storage bin is formed in the side wall of the groove, a driving motor and a spring buckle are arranged in the storage bin, a baffle is arranged on the spring buckle, the baffle can enter and exit the groove and is clamped in the clamping hole, one surface of the baffle, which is used for being in contact with the protrusion, is a wedge-shaped surface, and the driving motor is used for driving the baffle to be separated from the clamping hole and completely separated from the groove.
4. 4. The aircraft of claim 2 wherein the duct comprises a duct body, a tilting shaft with two ends respectively disposed on the side tanks and penetrating the duct body, a transmission mechanism disposed in the side tanks and in driving connection with the tilting shaft, and a driving mechanism for driving the transmission mechanism and driving the tilting shaft to rotate.
5. 5. The vehicle of claim 4, wherein the drive mechanism is a stepper motor to effect control of the angle of rotation of the pitch shaft.
6. 6. The aircraft of claim 4, wherein the engine mechanism comprises an engine compartment, a reverser rotor and a counter rotor disposed outside the engine compartment, and an engine disposed inside the engine compartment for driving rotation of the reverser rotor and the counter rotor, the tilt shaft extending through the engine compartment.
7. 7. The aircraft of claim 6, wherein two engines are provided for controlling the counter rotor and the counter rotor, respectively, the counter rotor being located above the counter rotor.
8. 8. The aircraft of claim 6, wherein a top of the nacelle is provided with a fairing.
9. 9. The aircraft of claim 1, wherein the body is provided with a positioning sensor.
10. 10. An aircraft cluster, characterized in that an aircraft according to any one of claims 1 to 9 is applied, comprising a control system for controlling the connection and disconnection of the aircraft, and at least two aircraft.

Description

Aircraft and aircraft cluster thereof Technical Field The invention belongs to the technical field of aircrafts, and particularly relates to an aircraft and an aircraft cluster thereof. Background With the continuous development of aviation technology, the aircraft forms are increasingly diversified, and particularly in the field of vertical take-off and landing aircrafts, how to combine hover operation efficiency and high-speed cruising performance is always one of the core problems focused by the technicians in the field. Although the traditional helicopter has excellent vertical take-off and landing and hovering capabilities, the front flying speed is limited, the pneumatic efficiency is low, and the range and the endurance time are difficult to meet the requirements of quick response and long-distance operation. While the fixed wing aircraft has the advantages of high speed and long endurance, the fixed wing aircraft depends on runway take-off and landing and cannot be flexibly deployed in complex terrains or narrow spaces. Therefore, configurations such as a tilting rotor wing, a tilting duct and the like are generated, and the power system is switched between a vertical lift mode and a horizontal thrust mode to achieve unification of vertical lifting and efficient cruising. However, with the rapid development of unmanned aerial vehicle cluster technology and cooperative control strategy, multi-machine cooperative operation shows a wide application prospect. The multi-aircraft collaborative coordination can remarkably improve the overall task capacity, for example, in the material transportation, the multi-aircraft collaborative coordination can share load and mutually back up, the transportation efficiency and the system redundancy are improved, and in the reconnaissance monitoring task, the multi-aircraft collaborative coordination can expand the coverage area and construct a three-dimensional perception network. However, most of the current multi-machine cooperation adopts a formation flight mode, a certain safety distance is kept between aircrafts, and information interaction and task allocation are realized by means of wireless communication. The method has higher flexibility, but the aircrafts lack of physical connection, and structural combination and strength integration cannot be realized, so that the integration advantages of the multi-machine system are difficult to fully develop when the method faces the scenes of centralized power and combined bearing, such as heavy material transportation, long-endurance accompanying flight and the like. In addition, although some aircrafts in the prior art attempt to realize multi-machine combination by adopting a mechanical connection mode, the connection structure is often complicated in design, high in requirement on docking precision and complex in separation process, and the connected combination has great challenges in the aspects of pneumatic characteristics, gravity center distribution and flight control. Especially in the design of the connecting device, if the unified and reliable interface form is lacking, quick exchange and modularized combination are difficult to realize among different aircrafts, and the flexibility and the practicability of multi-machine cooperation are limited. The part scheme adopts the butt joint structure of single direction, easily leads to connecting looseness because of the atress is uneven or vibration in the assembly flight, influences flight safety. In summary, how to realize quick, stable and reliable mechanical butt joint among multiple aircrafts on the basis of guaranteeing that a single machine has vertical take-off and landing and high-efficiency cruising capability, and further improve the overall load capability, voyage and task adaptability through combined flying, and meanwhile, consider the simplicity, interchangeability and separation convenience of a connecting structure, and become a technical problem to be solved urgently in the field. Based on the design, an improved aircraft design scheme is provided, and the design of reasonable power layout and docking devices is adopted to provide more reliable structural foundation and expansion capability for multi-machine collaborative operation. Disclosure of Invention In order to solve the problems, the invention provides an aircraft and an aircraft cluster thereof, and the purposes of stable docking of the aircraft and convenience are achieved. In order to achieve the above object, the present invention provides the following solutions: The utility model provides an aircraft, includes the organism, sets up tilting duct on the organism, set up engine mechanism on the duct and set up be used for with the connecting device of adjacent aircraft butt joint on the organism, connecting device is including setting up pin thread and the box on the frame, on the adjacent aircraft pin thread and box realize the butt joint of adjacent through the lock the aircraft. P