CN220315290U

CN220315290U - Propeller mounting frame for aircraft

Info

Publication number: CN220315290U
Application number: CN202321527546.3U
Authority: CN
Inventors: 谢恩利; 孙恒霞; 范兴国
Original assignee: Flying Space Huizhou Technology Co ltd
Current assignee: Flying Space Huizhou Technology Co ltd
Priority date: 2023-06-15
Filing date: 2023-06-15
Publication date: 2024-01-09
Anticipated expiration: 2033-06-15

Abstract

The utility model relates to the technical field of aircrafts, in particular to a propeller mounting rack for an aircrafts, which comprises a middle rod, an inner rod, an outer rod and a connecting rod, wherein the inner rod and the outer rod are respectively arranged on two sides of the middle rod; the two ends of the inner rod are connected with the middle rod by connecting rods; the both ends of outer pole all adopt the connecting rod to be connected with the middle pole. When in actual use, the plurality of lift propeller mechanisms are arranged on the propeller mounting frame for the aircraft, so that the aircraft can realize vertical take-off and landing and large-load transportation. This screw mounting bracket for aircraft adopts the middle pole to be connected with front wing and rear fin respectively to both sides at the middle pole distribute have interior pole and outer pole, adopt the connecting rod with interior pole, outer pole with the middle pole is connected as an organic whole structure, makes the aircraft stationarity good when flight, has reduced front wing atress and atress comparatively balanced simultaneously, improves the life of use.

Description

Propeller mounting frame for aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a propeller mounting frame for an aircrafts.

Background

Chinese patent publication No. CN115723948A discloses a V-tail single-thrust electric vertical take-off and landing composite wing aircraft, which comprises a fuselage, wings are installed on two sides of the fuselage, a motor arm is installed on the wings, winglets are installed at the ends of the wings, lift paddles are installed on the motor arm, a single V-tail and a thrust paddle are installed at the tail of the fuselage, the thrust paddle is located at the rear end of the single V-tail, and a tail thrust fairing is installed at the rear end of the thrust paddle. The aircraft has the advantages of both a helicopter and a fixed-wing aircraft, and has better terrain adaptability and cruising performance. The aircraft can take off and land vertically without runway, can adapt to complex urban traffic environment, and has strong safety and adaptability.

According to the aircraft, the two motor arms are arranged on the wings, and the lifting paddles and the motors are arranged on the motor arms, so that the vertical take-off and landing function is realized, and the bearing capacity of the aircraft is improved to a certain extent. However, when the load is heavy, the aircraft is poor in stability, and meanwhile, the two motor arms and the lifting paddles and the motors arranged on the two motor arms are arranged on the wing at one side of the aircraft body, so that the wing is stressed unevenly, the balance is poor, the wing is damaged when the aircraft is used for a long time, the use requirement cannot be met, and an improved technical scheme is needed to be provided.

Disclosure of Invention

Aiming at the defects of the prior art, the utility model provides the propeller mounting frame for the aircraft, which enables the aircraft to bear balanced force and fly stably and can realize high-load flight.

In order to solve the technical problems, the utility model adopts the following technical scheme:

the utility model provides a propeller mounting rack for an aircraft, which comprises a middle rod, an inner rod, an outer rod and a connecting rod, wherein the inner rod and the outer rod are respectively arranged on two sides of the middle rod; the two ends of the inner rod are connected with the middle rod by connecting rods; the two ends of the outer rod are connected with the middle rod by connecting rods;

the inner rod and the outer rod are both connected with the front wing of the aircraft, and the tail end of the middle rod is connected with the tail wing of the aircraft.

The inner rod, the outer rod and the four connecting rods in the propeller installation frame enclose a parallel hexagonal frame, the middle rod is positioned at the center line position of the length direction of the parallel hexagonal frame, and the front wing is connected with the middle position of the parallel hexagonal frame.

Wherein, all install lift screw mechanism on middle pole, interior pole and the outer pole.

Wherein, the lift propeller mechanisms are arranged at both ends of the inner rod and both ends of the outer rod; the lifting propeller mechanisms are arranged at the joints of the two ends of the middle rod and the connecting rods.

The lifting propeller mechanism comprises a propeller and a motor for driving the propeller to rotate.

The tail of the middle rod is provided with a second thrust propeller mechanism.

The utility model has the beneficial effects that:

the utility model provides a propeller mounting frame for an aircraft, which is provided with a plurality of lifting propeller mechanisms when in actual use, so that the aircraft can realize vertical take-off and landing and large-load transportation. This screw mounting bracket for aircraft adopts the middle pole to be connected with front wing and rear fin respectively to both sides at the middle pole distribute have interior pole and outer pole, adopt the connecting rod with interior pole, outer pole with the middle pole is connected as an organic whole structure, makes the aircraft stationarity good when flight, has reduced front wing atress and atress comparatively balanced simultaneously, improves the life of use.

Drawings

Fig. 1 is a schematic perspective view of the present utility model.

Fig. 2 is a schematic perspective view of a shape body used in the present utility model.

Fig. 3 is a schematic perspective view of another perspective view of the body of the present utility model.

Fig. 4 is a schematic perspective view of another perspective view of the body of the present utility model.

Fig. 5 is a schematic perspective view of another perspective view of the body of the present utility model.

Fig. 6 is a top view of a form body used in the present utility model.

Fig. 7 is a bottom view of the use body of the present utility model.

Detailed Description

The utility model will be further described with reference to examples and drawings, to which reference is made, but which are not intended to limit the scope of the utility model. The present utility model will be described in detail below with reference to the accompanying drawings.

Referring to fig. 1 to 7, a propeller mount for an aircraft includes a center pole 41, inner and outer poles 42 and 43 respectively provided at both sides of the center pole 41, and a connecting pole 44; both ends of the inner rod 42 are connected with the middle rod 41 by connecting rods 44; both ends of the outer rod 43 are connected with the middle rod 41 by connecting rods 44; the inner rod 42 and the outer rod 43 are both connected to the front wing 2 of the aircraft, and the tail end of the middle rod 41 is connected to the tail wing 3 of the aircraft. Specifically, the inner rod 42 and the outer rod 43 are equal-length rods, and the connecting rods 44 at two ends of the inner rod 42 and the outer rod 43 are connected with the same section of the middle rod 41.

During actual use, a plurality of lifting propeller mechanisms 5 are arranged on the propeller mounting frame for the aircraft, so that the aircraft can realize vertical take-off and landing and large-load transportation. This screw mounting bracket for aircraft adopts middle pole 41 to be connected with front wing 2 and rear fin 3 respectively to both sides at middle pole 41 distribute have interior pole 42 and outer pole 43, adopt connecting rod 44 with interior pole 42, outer pole 43 with middle pole 41 connects as an organic whole structure, makes the aircraft stationarity good when flight, has reduced front wing 2 atress and atress comparatively balanced simultaneously, improves the life of use.

In this embodiment, the inner rod 42, the outer rod 43, and the four connecting rods 44 in the propeller mounting frame 4 enclose a parallel hexagonal frame, the middle rod 41 is located at a center line position in a length direction of the parallel hexagonal frame, and the front wing 2 is connected with a middle position of the parallel hexagonal frame. The parallel hexagonal frame is in a symmetrical design structure relative to the middle rod 41 on the front wing 2, and the load of the middle rod 41 is shared by the front wing 2 and the tail wing 3 at the same time, so that the aircraft propeller mounting rack is balanced in layout and good in stability during flight.

In this embodiment, the center pole 41, the inner pole 42, and the outer pole 43 are each provided with a lift screw mechanism 5. Specifically, the lift propeller mechanism 5 is disposed at both ends of the inner rod 42 and both ends of the outer rod 43; the lifting propeller mechanism 5 is arranged at the joint of the two ends of the middle rod 41 and the connecting rod 44. Ten lifting propeller mechanisms 5 are designed, three lifting propeller mechanisms 5 are distributed in front of and behind the front wing 2 on one side of the fuselage 1, and three lifting propeller mechanisms 5 are distributed in a triangle shape, so that the aircraft has strong power and good stability when taking off and landing vertically. The lift propeller mechanism 5 comprises a propeller and a motor for driving the propeller to rotate. The tail of the middle rod 41 is provided with a second thrust propeller mechanism 7, which increases the cruising power of the aircraft.

The present utility model is not limited to the preferred embodiments, but is intended to be limited to the following description, and any modifications, equivalent changes and variations in light of the above-described embodiments will be apparent to those skilled in the art without departing from the scope of the present utility model.

Claims

1. A propeller mounting bracket for aircraft, its characterized in that: comprises a middle rod (41), an inner rod (42) and an outer rod (43) which are respectively arranged at two sides of the middle rod (41), and a connecting rod (44); both ends of the inner rod (42) are connected with the middle rod (41) by connecting rods (44); both ends of the outer rod (43) are connected with the middle rod (41) by connecting rods (44);

the inner rod (42) and the outer rod (43) are connected with the front wing (2) of the aircraft, and the tail end of the middle rod (41) is connected with the tail wing (3) of the aircraft.

2. A propeller mounting for an aircraft as claimed in claim 1, wherein: an inner rod (42), an outer rod (43) and four connecting rods (44) in the propeller mounting frame (4) enclose into a parallel hexagonal frame, the middle rod (41) is located at the center line position of the length direction of the parallel hexagonal frame, and the front wing (2) is connected with the middle position of the parallel hexagonal frame.

3. A propeller mounting for an aircraft according to claim 1 or 2, wherein: and the middle rod (41), the inner rod (42) and the outer rod (43) are respectively provided with a lifting propeller mechanism (5).

4. A propeller mounting for an aircraft as claimed in claim 3, wherein: the lift propeller mechanism (5) is arranged at both ends of the inner rod (42) and both ends of the outer rod (43); the lifting propeller mechanisms (5) are arranged at the joints of the two ends of the middle rod (41) and the connecting rods (44).

5. A propeller mounting for an aircraft as claimed in claim 3, wherein: the lifting propeller mechanism (5) comprises a propeller and a motor for driving the propeller to rotate.

6. A propeller mounting for an aircraft according to claim 1 or 2, wherein: the tail part of the middle rod (41) is provided with a second thrust propeller mechanism (7).