Rotor tilt mechanism of electric vertical take-off and landing aircraft

Abstract

The present invention belongs to the technical field of aircraft, and discloses a rotor tilting mechanism of an electric vertical take-off and landing aircraft, comprising: a shell, which comprises: an end plate and two side plates; the two side plates are arranged opposite to each other, and one end of the two side plates is respectively connected to the two ends of the end plate, and an accommodating cavity is enclosed between the end plate and the two side plates; an electric push rod mechanism is arranged in the accommodating cavity; one end of the electric push rod mechanism is rotatably connected to the end plate, and the other end is provided with a push rod; two tilting arms, which are arranged at the other end of the side plate and correspond to the positions of the two side plates one by one; a tail thrust tilting rod, whose two ends are respectively fixedly connected to one end of the two tilting arms; wherein the push rod is rotatably connected to the tail thrust tilting rod; a rotor power motor, which is fixedly connected to the other end of the two tilting arms through a connecting seat; wherein the tilting arms and their corresponding side plates are respectively connected through rotating shafts; when the push rod is extended and retracted, it can push the tilting arms to rotate, thereby driving the rotor power motor to rotate, so as to realize rotor tilting.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a rotor tilting mechanism of an electric vertical take-off and landing aircraft. Background Art

[0002] Existing electric vertical take-off and landing aircraft are mainly divided into composite wing vertical take-off and landing aircraft and tilt-rotor vertical take-off and landing aircraft. Composite wing vertical take-off and landing aircraft use both a fixed-wing power system and a rotor power system. The fixed-wing power system is used for fixed-wing cruise flight, and the rotor power system is used for vertical take-off and landing flight. Compared with composite wing vertical take-off and landing aircraft, tilt-rotor vertical take-off and landing aircraft use a tilt-rotor power system that is compatible with fixed-wing cruise flight and vertical take-off and landing flight. The former aircraft has a heavy deadweight and low aerodynamic efficiency, while the latter aircraft has a light deadweight and high aerodynamic efficiency.

[0003] However, the existing tilt-rotor VTOL aircraft rotor tilting structures are mostly driven by servos, which have large aerodynamic resistance, poor reliability and short service life. In view of this, a new technical solution is urgently needed to solve the above problems. Summary of the invention

[0004] The purpose of the present invention is to provide a rotor tilt mechanism for an electric vertical take-off and landing aircraft, which adopts an electric push rod mechanism in conjunction with a tilt transmission assembly to achieve the tilt of the tilt arm, and can solve the problems of large aerodynamic resistance and poor reliability caused by the use of servo drive in the prior art.

[0005] The technical solution provided by the present invention is:

[0006] A rotor tilting mechanism for an electric vertical take-off and landing aircraft, comprising:

[0007] The housing comprises: an end plate and two side plates; the two side plates are arranged opposite to each other, and one end of the two side plates is respectively connected to two ends of the end plate, and a receiving cavity is formed between the end plate and the two side plates;

[0008] An electric push rod mechanism is arranged in the accommodating cavity; one end of the electric push rod mechanism is rotatably connected to the end plate, and the other end of the electric push rod mechanism has a push rod;

[0009] Two tilting arms, which are arranged at the other end of the side plate, and the positions of the two tilting arms and the two side plates correspond one to one;

[0010] A tail thrust tilt rod, both ends of which are fixedly connected to one end of the two tilt arms respectively;

[0011] Wherein, the push rod is rotatably connected to the tail thrust tilt rod;

[0012] A rotor power motor, which is fixedly connected to the other ends of the two tilt arms through a connecting seat;

[0013] Wherein, the tilt arm and its corresponding side plate are respectively connected via a rotating shaft, and the rotating shaft is located between the tail thrust tilt rod and the connecting seat;

[0014] When the push rod is extended or retracted, it can push the tilt arm to rotate, thereby driving the rotor power motor to rotate and realizing the rotor tilting.

[0015] Preferably, the electric push rod mechanism is connected to the end plate via a first push rod connector;

[0016] The first push rod connecting member comprises: a first bottom plate and two first connecting rods; the two first connecting rods are arranged parallel to each other, and one end of the two first connecting rods is vertically fixedly connected to the first bottom plate, and the other end is a free end;

[0017] Wherein, the first base plate is fixedly connected to the end plate by end plate connecting bolts, and the free ends of the two first connecting rods are respectively located on both sides of the electric push rod mechanism and are rotatably connected to the electric push rod mechanism by the first push rod connecting bolts.

[0018] Preferably, the push rod is connected to the tail thrust tilt rod via a second push rod connector;

[0019] The second push rod connecting member comprises: a second bottom plate and two second connecting rods; the two second connecting rods are arranged parallel to each other, and one end of the two second connecting rods is vertically fixedly connected to the second bottom plate, and the other end is a free end;

[0020] Wherein, the second base plate is fixedly connected to the tail thrust tilt rod through the tilt rod connecting bolts, and the free ends of the two second connecting rods are respectively located on both sides of the push rod and are rotatably connected to the push rod through the second push rod connecting bolts.

[0021] Preferably, the electric push rod mechanism adopts an electric ball screw mechanism.

[0022] Preferably, the electric push rod mechanism is provided with an electric brake.

[0023] Preferably, a bearing is installed in the side plate, and one end of the rotating shaft is rotatably supported in the bearing.

[0024] Preferably, an axis hole is provided on the tilt arm, and the tilt arm is connected to the rotating shaft via a transmission key; the other end of the rotating shaft is fixed to the tilt arm via a horizontal optical axis support.

[0025] Preferably, both ends of the tail thrust tilt rod are welded to the two tilt arms respectively.

[0026] Preferably, the two tilt arms are respectively located on the outer sides of the two side plates; an arc-shaped groove is opened on the lower side of the side plate, and the shape of the arc-shaped groove matches the movement trajectory of the tail thrust tilt rod; the tail thrust tilt rod can be pushed to the outside of the arc-shaped groove or retracted into the arc-shaped groove by the push rod.

[0027] Preferably, the rotor tilt mechanism of the electric vertical take-off and landing aircraft further includes:

[0028] An angle sensor is installed on the tilt arm and is used for measuring the tilt angle of the tilt arm in real time.

[0029] The beneficial effects of the present invention are:

[0030] The rotor tilt mechanism of the electric vertical take-off and landing aircraft provided by the present invention adopts an electric push rod mechanism in conjunction with a tilt transmission assembly to replace the existing steering gear drive; by driving the tail thrust tilt rod to rotate, the tilt arm is driven to tilt from zero to ninety degrees, thereby realizing the aircraft rotor tilt from zero to ninety degrees, making the entire rotor tilt structure simple and compact, with low space occupancy, and having the advantages of small air resistance, high reliability, and long service life, thereby improving the rotor layout scheme and rotor tilt structure of the existing electric vertical take-off and landing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a schematic diagram of the upper structure of the rotor tilt mechanism of the electric vertical take-off and landing aircraft described in the present invention.

[0032] Figure 2 The figure is a schematic diagram of the overall structure of the rotor tilt mechanism of the electric vertical take-off and landing aircraft described in the present invention.

[0033] Figure 3 This is an exploded view of the rotor tilt mechanism of the electric vertical take-off and landing aircraft described in the present invention.

[0034] Figure 4 It is a schematic diagram of the electric vertical take-off and landing aircraft of the present invention in a zero-degree tilt state.

[0035] Figure 5 This is a schematic diagram of the electric vertical take-off and landing aircraft of the present invention in a 90-degree tilt state.

[0036] Figure 6 This is an internal cross-sectional view of the rotor tilt structure of the electric vertical take-off and landing aircraft described in the present invention. DETAILED DESCRIPTION

[0037] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0038] like Figure 1-6 As shown, the present invention provides a rotor tilt mechanism for an electric vertical take-off and landing aircraft, which mainly includes: a shell 110, an electric push rod mechanism 120, a tilt arm 130, a tail thrust tilt rod 140, a connecting seat 150, a rotor power motor 160 and a rotating shaft 170.

[0039] The housing 110 is fixedly mounted on the wing rib of the aircraft, and includes: an end plate 111 and two side plates 112; the two side plates 112 are arranged parallel to each other, and one end of the two side plates 112 is respectively connected to the two ends of the end plate 111, and the end plate 111 and the two side plates 112 enclose a receiving cavity. In this embodiment, the end plate 111 and the side plates 112 are arranged vertically to form a rectangular frame with one end open, which serves as the housing 110. When working normally, the housing 110 is in a horizontal state.

[0040] The electric push rod mechanism 120 is disposed in the accommodating cavity of the housing 110 ; one end of the electric push rod mechanism 120 is rotatably connected to the end plate 111 , and the other end of the electric push rod mechanism 120 has a retractable push rod 121 .

[0041] The two tilting arms 130 are disposed at the other end of the side plate 112 (the end not connected to the end plate 111 ), and the two tilting arms 130 are disposed parallel to the two side plates 112 , and the positions thereof correspond one to one.

[0042] The tail thrust tilt rod 140 is disposed between the two tilt arms 130 and is disposed perpendicular to the tilt arms 130. Both ends of the tail thrust tilt rod 140 are respectively fixedly connected to one end (the end close to the side plate 112) of the two tilt arms 130. The push rod 121 is rotatably connected to the tail thrust tilt rod 140.

[0043] The rotor power motor 160 is fixedly connected to the other end of the two tilt arms 130 through the connecting seat 150. In this embodiment, the two sides of the connecting seat 150 are fixedly connected to the two tilt arms 130 through the connecting seat connecting bolts 150a. Among them, the tilt arms 130 and their corresponding side plates 112 are respectively connected through the rotating shaft 170, and the rotating shaft 170 is located between the tail thrust tilt rod 140 and the connecting seat 150; and the rotating shaft 170 is arranged parallel to the tail thrust tilt rod 140. When the push rod 121 is extended and retracted, it can push the tilt arm 130 to rotate around the axis direction of the rotating shaft 170, thereby driving the rotor power motor 160 to rotate and realize the rotor tilt.

[0044] As a preferred embodiment, the electric push rod mechanism 120 is connected to the end plate 111 through a first push rod connector 180. The first push rod connector 180 includes: a first base plate 181 and two first connecting rods 182; the two first connecting rods 182 are arranged parallel to each other, and one end of the two first connecting rods 182 is vertically fixedly connected to the first base plate 181, and the other end is a free end. The two ends of the first base plate 181 are respectively fixedly connected to the end plate 111 through end plate connecting bolts 111a, and the free ends of the two first connecting rods 182 are respectively located on both sides of the electric push rod mechanism 120, and are rotatably connected to the electric push rod mechanism 120 through the first push rod connecting bolts 120a that transversely penetrate the end of the electric push rod mechanism 120.

[0045] The push rod 121 is connected to the tail thrust tilt rod 140 through a second push rod connector 190. The second push rod connector 190 includes: a second base plate 191 and two second connecting rods 192; the two second connecting rods 192 are arranged parallel to each other, and one end of the two second connecting rods 192 is vertically fixedly connected to the second base plate 191, and the other end is a free end. The second base plate 191 is fixedly connected to the tail thrust tilt rod 140 through a tilt rod connecting bolt 140a, and the free ends of the two second connecting rods 192 are respectively located on both sides of the push rod 121, and are rotatably connected to the push rod 121 through a second push rod connecting bolt 121a that passes through the push rod 121 transversely.

[0046] As a preferred embodiment, the electric push rod mechanism 120 adopts an electric ball screw mechanism to ensure the stability of the push rod mechanism.

[0047] As a further preference, the electric push rod mechanism 120 is provided with an electric brake (brake) to prevent the push rod 121 of the electric push rod mechanism 120 from non-operational extension and retraction.

[0048] In this embodiment, a bearing 171 is embedded in the side plate 112, and one end of the rotating shaft 170 is rotatably supported in the bearing 171. A shaft sleeve 172 is installed between the rotating shaft 170 and the bearing to prevent the rotating shaft 170 from axially moving. An axial hole is provided on the tilt arm 130, and the rotating shaft 171 passes through the axial hole and is connected to the tilt arm 130 through a transmission key 173 to achieve power transmission. The other end of the rotating shaft 171 extends to the outside of the tilt arm 130 and performs an axial hole transition fit with the horizontal optical axis support member 174. At the same time, the horizontal optical axis support member 174 is fixedly connected to the tilt arm 130 through a support member connecting bolt 174a, thereby achieving the fixation of the rotating shaft 171 and the tilt arm 130.

[0049] In this embodiment, the two ends of the tail thrust tilt rod 140 are welded to the two tilt arms 130 respectively. The two tilt arms 130 are respectively located on the outside of the two side plates 112; the lower side of the side plate 112 is provided with an arc groove 112a, and the shape of the arc groove 112a matches the movement trajectory of the tail thrust tilt rod 140; the tail thrust tilt rod 140 can be pushed to the outside of the arc groove 112a or retracted into the arc groove 112a by the push rod 121. The tilt arm 130 is arranged on the outside of the side plate 112, and the arc groove 112a is arranged to limit the rotation (retraction) position of the tail thrust tilt rod 140, preventing the tilt arm 130 from rotating in the opposite direction and causing damage to the rotor.

[0050] As a preferred embodiment, the rotor tilt mechanism of the electric vertical take-off and landing aircraft further includes: an angle sensor 131, which is installed on the tilt arm 130 and is used to measure the tilt angle of the tilt arm 130 in real time. In this embodiment, the angle sensor 131 is installed at the end of the rotating shaft 170 (the end located outside the tilt arm 130).

[0051] The rotor tilt mechanism of the electric vertical take-off and landing aircraft provided by the present invention adopts an electric push rod mechanism in conjunction with a tilt transmission assembly to replace the existing steering gear drive; by driving the tail thrust tilt rod to rotate, the tilt arm is driven to tilt from zero to ninety degrees (horizontal to vertical upward), thereby realizing the zero to ninety degree tilt of the rotor of the present invention; the entire rotor tilt structure is simple and compact, and the space occupancy rate is low. In addition, the rotor power motor is directly installed at the tilt wing assembly, and the rotor power motor is driven by transmitting electric energy through cables, without the need for a power transmission assembly, which greatly reduces the complexity of the mechanical mechanism. During cruising, only the pod portion accommodating the rotor power motor tilts, and the overall area subjected to aerodynamic resistance is reduced. It has the advantages of high reliability, low aerodynamic resistance, and long service life, and improves the rotor layout scheme and rotor tilt structure of the existing electric vertical take-off and landing aircraft.

[0052] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and the implementation modes, and they can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily implemented. Therefore, without departing from the general concept defined by the claims and the scope of equivalents, the present invention is not limited to the specific details and the illustrations shown and described herein.

Claims

1. A rotor tilt mechanism for an electric vertical take-off and landing aircraft, characterized in that: include: The housing comprises: an end plate and two side plates; the two side plates are arranged opposite to each other, and one end of the two side plates is respectively connected to two ends of the end plate, and a receiving cavity is formed between the end plate and the two side plates; An electric push rod mechanism is arranged in the accommodating cavity; one end of the electric push rod mechanism is rotatably connected to the end plate, and the other end of the electric push rod mechanism has a push rod; Two tilting arms, which are arranged at the other end of the side plate, and the positions of the two tilting arms and the two side plates correspond one to one; A tail thrust tilt rod, both ends of which are fixedly connected to one end of the two tilt arms respectively; Wherein, the push rod is rotatably connected to the tail thrust tilt rod; A rotor power motor, which is fixedly connected to the other ends of the two tilt arms through a connecting seat; Wherein, the tilt arm and its corresponding side plate are respectively connected via a rotating shaft, and the rotating shaft is located between the tail thrust tilt rod and the connecting seat; When the push rod is extended or retracted, it can push the tilt arm to rotate, thereby driving the rotor power motor to rotate, thereby realizing the rotor tilt; The two tilt arms are respectively located on the outer sides of the two side plates; an arc-shaped groove is opened on the lower side of the side plate, and the shape of the arc-shaped groove matches the movement trajectory of the tail thrust tilt rod; the tail thrust tilt rod can be pushed to the outside of the arc-shaped groove or retracted into the arc-shaped groove by the push rod.

2. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 1, characterized in that: The electric push rod mechanism is connected to the end plate via a first push rod connector; The first push rod connecting member comprises: a first bottom plate and two first connecting rods; the two first connecting rods are arranged parallel to each other, and one end of the two first connecting rods is vertically fixedly connected to the first bottom plate, and the other end is a free end; Wherein, the first base plate is fixedly connected to the end plate by end plate connecting bolts, and the free ends of the two first connecting rods are respectively located on both sides of the electric push rod mechanism and are rotatably connected to the electric push rod mechanism by the first push rod connecting bolts.

3. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 2, characterized in that: The push rod is connected to the tail thrust tilt rod via a second push rod connector; The second push rod connecting member comprises: a second bottom plate and two second connecting rods; the two second connecting rods are arranged parallel to each other, and one end of the two second connecting rods is vertically fixedly connected to the second bottom plate, and the other end is a free end; Wherein, the second base plate is fixedly connected to the tail thrust tilt rod through the tilt rod connecting bolts, and the free ends of the two second connecting rods are respectively located on both sides of the push rod and are rotatably connected to the push rod through the second push rod connecting bolts.

4. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 3, characterized in that: The electric push rod mechanism adopts an electric ball screw mechanism.

5. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 4, characterized in that: The electric push rod mechanism is provided with an electric brake.

6. The rotor tilting mechanism of the electric vertical take-off and landing aircraft according to any one of claims 2 to 5, characterized in that: A bearing is installed in the side plate, and one end of the rotating shaft is rotatably supported in the bearing.

7. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 6, characterized in that: An axis hole is provided on the tilting arm, and the tilting arm is connected to the rotating shaft via a transmission key; the other end of the rotating shaft is fixed on the tilting arm via a horizontal optical axis support.

8. The rotor tilt mechanism of the electric vertical take-off and landing aircraft according to claim 7, characterized in that: Both ends of the tail thrust tilt rod are welded to the two tilt arms respectively.

9. The rotor tilting mechanism of the electric vertical take-off and landing aircraft according to claim 8, characterized in that: Also includes: An angle sensor is installed on the tilt arm and is used for measuring the tilt angle of the tilt arm in real time.

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