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CN-122003368-A - Unmanned vehicles and panorama shooting aircraft

CN122003368ACN 122003368 ACN122003368 ACN 122003368ACN-122003368-A

Abstract

The application relates to the technical field of aircrafts, in particular to an unmanned aircraft and a panoramic shooting aircraft. An unmanned aerial vehicle comprises a fuselage (10), an image acquisition device (50) and a cradle (20). The support (20) is connected to the machine body (10), the support (20) is provided with a heat dissipation structure, the image acquisition device (50) is connected to the support (20) and is connected to the machine body (10) through the support (20), and the heat dissipation structure is used for dissipating heat of the image acquisition device (50). According to the unmanned aerial vehicle, the heat dissipation structure is used for dissipating heat of the image acquisition device (50), and the heat dissipation efficiency is high.

Inventors

  • Request for anonymity
  • Request for anonymity

Assignees

  • 影石创新科技股份有限公司
  • 深圳影翎科技有限公司

Dates

Publication Date
20260508
Application Date
20240906

Claims (20)

  1. An unmanned aerial vehicle, comprising: a body (10); An image acquisition device (50); The image acquisition device comprises a frame (20), a frame (20) and an image acquisition device (50), wherein the frame (20) is connected to the machine body (10), the frame (20) is provided with a heat dissipation structure, the image acquisition device (50) is connected to the frame (20) and is connected to the machine body (10) through the frame (20), and the heat dissipation structure is used for dissipating heat of the image acquisition device (50).
  2. The unmanned aerial vehicle according to claim 1, wherein the bracket (20) comprises a mounting body (21) and a shock absorber (23), the image acquisition device (50) is provided to the mounting body (21), and the mounting body (21) is connected to the fuselage (10) by the shock absorber (23).
  3. The unmanned aerial vehicle according to claim 2, wherein the bracket (20) further comprises a connecting frame (25), the shock absorbing member (23) is connected between the mounting body (21) and the connecting frame (25), the connecting frame (25) is provided with a mounting portion (254), and the mounting portion (254) is directly connected to the middle frame (123) of the fuselage (10) by a fastener.
  4. An unmanned aerial vehicle according to claim 3, wherein the shock absorbing member (23) comprises a shock absorbing ball, the mounting body (21) is provided with a first mounting hole (211), the connecting frame (25) is provided with a second mounting hole (251), one side of the shock absorbing ball is connected to the first mounting hole (211), and the other side is connected to the second mounting hole (251).
  5. The unmanned aerial vehicle as claimed in claim 4, wherein the shock absorbing balls have deformation axes, the shock absorbing balls are divided into two groups, the two groups of shock absorbing balls are respectively positioned on two sides of the connecting frame (25), each group of shock absorbing balls at least comprises three shock absorbing balls, and the deformation axes of the three shock absorbing balls in the same group are intersected in pairs.
  6. The unmanned aerial vehicle of claim 5, wherein three of the shock absorbing balls in each set of shock absorbing balls are distributed at three vertices of a regular triangle.
  7. The unmanned aerial vehicle according to any one of claims 3 to 6, wherein the connecting frame (25) comprises a mounting seat (252) and a plurality of mounting portions (254), the plurality of mounting portions (254) are distributed on the mounting seat (252) at intervals, the plurality of mounting portions (254) are respectively connected with the fuselage (10), and a heat dissipation gap (256) communicated with the outside exists between the mounting seat (252) and the fuselage (10).
  8. The unmanned aerial vehicle of claim 7, wherein the fuselage (10) comprises a main body shell portion (1232) and two support shell portions (1235), wherein the two support shell portions (1235) are connected to the same end of the main body shell portion (1232), the two support shell portions (1235) are relatively spaced to form a containing space (124), the bracket (20) is contained in the containing space (124), the plurality of mounting portions (254) are distributed on two sides of the bracket (20) and are respectively connected with the two support shell portions (1235), and the heat dissipation gap (256) is arranged between the support shell portions (1235) and the mounting base (252).
  9. The unmanned aerial vehicle of any of claims 2-8, wherein the mounting body (21) forms at least part of the heat dissipation structure, the mounting body (21) comprises a heat conduction portion (2121) and heat dissipation fins (2123), the heat dissipation fins (2123) are connected to the heat conduction portion (2121), and the first fisheye lens (521) and the second fisheye lens (523) are respectively disposed on the heat conduction portion (2121).
  10. The unmanned aerial vehicle of claim 9, wherein the bracket (20) further comprises a protective shell (27), the protective shell (27) being connected to the thermally conductive portion (2121) and surrounding an outer periphery of at least part of the structure of the first fisheye lens (521) or/and the second fisheye lens (523).
  11. The unmanned aerial vehicle according to any one of claims 1 to 10, wherein the image acquisition device (50) comprises a first fisheye lens (521) and a second fisheye lens (523), and the first fisheye lens (521) and the second fisheye lens (523) are respectively connected to two sides of the bracket (20).
  12. An unmanned aerial vehicle as claimed in any one of claims 1 to 10, wherein the image acquisition device (50) comprises a first obstacle avoidance module (54) connected to the fuselage (10), the first obstacle avoidance module (54) comprises a first front camera (541) and a second front camera (543) arranged at intervals, and the first front camera (541) and the second front camera (543) are respectively connected to the bracket (20).
  13. The unmanned aerial vehicle of claim 12, wherein the first front camera (541) and the second front camera (543) are located on a same side of the first fisheye lens (521), the first front camera (541) and the second front camera (543) are aligned along a yaw axis of the unmanned aerial vehicle, the first fisheye lens (521) and the second fisheye lens (523) are aligned along the yaw axis, the unmanned aerial vehicle is in a hover state with a lighting side of the first fisheye lens (521) facing upward of the fuselage (10) and the second fisheye lens (523) facing downward of the fuselage (10).
  14. The unmanned aerial vehicle of claim 12 or 13, wherein a virtual line of the optical center of the first fisheye lens (521) and the optical center of the second fisheye lens (523) forms a first axis, the first fisheye lens (521) having a first optical axis, the second fisheye lens (523) having a second optical axis, the first optical axis passing through the optical center of the first fisheye lens (521), the second optical axis passing through the optical center of the second fisheye lens (523).
  15. Unmanned aerial vehicle according to claim 14, wherein the first front camera (541) has a third optical axis and the second front camera (543) has a fourth optical axis, the third and/or fourth optical axis being perpendicular to the first axis.
  16. The unmanned aerial vehicle of claim 15, wherein the range of angles between the first axis and the yaw axis falls within any of the range of angles [0 °,3 °,6 °,10 ° ], 10 °,20 °,35 °.
  17. An unmanned aerial vehicle as claimed in claim 12, wherein the pitch and roll axes of the unmanned aerial vehicle together define a first face, the first front camera (541) having a third optical axis, the second front camera (543) having a fourth optical axis, the third and/or fourth optical axis intersecting the first face.
  18. An unmanned aerial vehicle as claimed in claim 12, wherein the unmanned aerial vehicle is in a forward flat flight condition, the light collecting sides of the first front camera (541) and the second front camera (543) are oriented towards the front of the unmanned aerial vehicle, the first front camera (541) has a third optical axis, the second front camera (543) has a fourth optical axis, and the third optical axis or/and the fourth optical axis are parallel to a horizontal plane.
  19. An unmanned aerial vehicle as claimed in claim 17, wherein in a hovering state of the unmanned aerial vehicle, a horizontal forward direction of the unmanned aerial vehicle is set to a first vector direction, a direction from inside the first front camera (541) toward a lighting side of the first front camera (541) along the third optical axis is set to a second vector direction, the second vector direction is spatially located above the first vector direction reference direction, and an angle range between the first vector direction and the second vector direction falls within any one of an angle range of [0 °,3 ° ], [3 °,6 ° ], [6 °,10 ° ], [10 °,20 ° ], and [20 °,35 ° ].
  20. An unmanned aerial vehicle as claimed in any one of claims 12 to 14, wherein the first front camera (541) has a third optical axis and the second front camera (543) has a fourth optical axis, the third optical axis being parallel to the fourth optical axis.

Description

Unmanned vehicles and panorama shooting aircraft Technical Field The application relates to the technical field of aircrafts, in particular to an unmanned aircraft and a panoramic shooting aircraft. Background The unmanned plane is called as unmanned plane for short, and is a unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other devices. Personnel on the ground, ships or on a mother machine remote control station track, position, remote control, telemetere and digital transmission through radar and other equipment. Currently, in order to capture a bird's eye view of a panoramic view, a panoramic image is generally captured by providing fish-eye lenses at the bottom and top of an unmanned aerial vehicle. When the imaging device shoots, elements such as an image sensor generate heat, and the quality of an image shot by the imaging device is affected with the rise of temperature. The fish-eye lens of the existing unmanned aerial vehicle is usually installed in the middle of the machine body, the distance between the fish-eye lens and an element generating heat in the machine body is relatively short, the temperature of the fish-eye lens is further improved, and the operation performance of the fish-eye lens can be reduced due to high temperature. Disclosure of Invention The application provides an unmanned aerial vehicle and a panoramic shooting aerial vehicle. In a first aspect, the present application provides an unmanned aerial vehicle comprising a fuselage, an image acquisition device, and a cradle. The image acquisition device is connected to the bracket and is connected to the machine body through the bracket, and the heat dissipation structure is used for dissipating heat of the image acquisition device. In a second aspect, the present application also provides an unmanned aerial vehicle, the unmanned aerial vehicle comprising a fuselage, an image acquisition device, and a cradle. The fuselage includes organism and preceding shell, and preceding shell is connected in the organism. The image acquisition device is arranged on the machine body and comprises a first fisheye lens and a second fisheye lens, and the first fisheye lens and the second fisheye lens are respectively arranged on two sides of the machine body. The image acquisition device is connected with the bracket and connected with the machine body through the bracket, and the heat dissipation air channel is used for dissipating heat of the image acquisition device. In a third aspect, the present application further provides a panoramic shooting aircraft, including a fuselage, an image acquisition device and a bracket, where the image acquisition device includes a first fisheye lens and a second fisheye lens, the first fisheye lens and the second fisheye lens are respectively disposed on two sides of the fuselage facing away from each other, and field of view ranges of the first fisheye lens and the second fisheye lens overlap to be used for acquiring panoramic images. The image acquisition device is connected to the bracket and is connected to the machine body through the bracket, and the heat dissipation structure is used for dissipating heat of the image acquisition device. Drawings In order to more clearly illustrate the technical solutions of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art. Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present application. Fig. 2 is a simplified schematic structural diagram of the unmanned aerial vehicle shown in fig. 1. Fig. 3 is a schematic view of the overall structure of the unmanned aerial vehicle shown in fig. 1. Fig. 4 is a schematic view of the unmanned aerial vehicle shown in fig. 3 in a stowed state. Fig. 5 is a simplified schematic illustration of the reference plane and the support plane of the unmanned aerial vehicle of fig. 3 in a hovering state. Fig. 6 is a simplified schematic illustration of the reference plane and the support plane of the unmanned aerial vehicle of fig. 3 in a cocked state. Fig. 7 is a simplified schematic view of a reference plane of the unmanned aerial vehicle shown in fig. 3. Fig. 8 is a simplified schematic view of a support plane of the unmanned aerial vehicle shown in fig. 3. Fig. 9 is a schematic view of an explosive structure of the interior of the fuselage of the unmanned aerial vehicle shown in fig. 3. Fig. 10 is an exploded structural schematic view of a partial structure of the unmanned aerial vehicle shown in fig. 9. Fig. 11 is a schematic view of the unm