CN211391654U - Unmanned aerial vehicle with parachute bay door closing mechanism - Google Patents
Unmanned aerial vehicle with parachute bay door closing mechanism Download PDFInfo
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- CN211391654U CN211391654U CN202020081631.1U CN202020081631U CN211391654U CN 211391654 U CN211391654 U CN 211391654U CN 202020081631 U CN202020081631 U CN 202020081631U CN 211391654 U CN211391654 U CN 211391654U
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Abstract
The utility model provides an unmanned aerial vehicle with parachute cabin hatch door closing mechanism, including the unmanned aerial vehicle body, the ventral of unmanned aerial vehicle body is equipped with the square parachute cabin of placing the parachute, square parachute cabin bottom be equipped with around the parachute cabin lateral wall rotatable coupling's first umbrella hatch door and second umbrella hatch door, the side of first and second umbrella hatch door all is connected with two rudder arms, two rudder arms are close to umbrella hatch door front and back end respectively, square parachute cabin is inside to be equipped with to drive the parachute hatch door and open and the closing mechanism who closes, closing mechanism includes servo steering wheel and a plurality of steel wire cable, servo steering wheel fixes the square parachute cabin roof in parachute cabin door top, two rudder arms on the first umbrella cabin door are connected with servo steering wheel's rhombus rocking arm one end respectively through the steel wire cable, two rudder arms on the second umbrella cabin door are connected with the rhombus rocking arm other end of servo steering wheel through the steel wire cable respectively. This application can realize the umbrella cabin door through closing mechanism and open and close, and the umbrella cabin door can not release after the cabin is opened, but reuse has practiced thrift the cost.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to unmanned aerial vehicle with parachute cabin hatch door closing mechanism.
Background
An unmanned aircraft, referred to as "drone" for short, is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an on-board computer. From a technical point of view, the definition can be divided into: unmanned fixed wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane aircraft, and the like.
Unmanned aerial vehicle according to the application, can divide into for military use and civilian, for military use aspect, unmanned aerial vehicle divide into scout plane and target drone, and in civilian aspect, unmanned aerial vehicle + industry application are real just needing of unmanned aerial vehicle. At present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
Because the parachute has easy operation's characteristics, present wide application in unmanned aerial vehicle's recovery, the parachute of current unmanned aerial vehicle is placed in the parachute cabin of ventral, and when the parachute is released to the unmanned aerial vehicle flight in-process when needs, through the current autopilot system control release parachute cabin door of unmanned aerial vehicle self, the parachute of placing in the parachute cabin is followed the parachute cabin door and is thrown the parachute. However the utility model discloses an inventor discovers through research that current unmanned aerial vehicle is retrieving the in-process through the parachute, and the parachute cabin door after the release can drift down with the wind and seek at the inconvenient staff of arbitrary place, therefore is unfavorable for the recovery of parachute cabin door and recycles, has promoted unmanned aerial vehicle use cost.
SUMMERY OF THE UTILITY MODEL
To current unmanned aerial vehicle retrieving the in-process through the parachute, the parachute cabin door after the release can drift to fall in the inconvenient staff of arbitrary place and seek with the wind, therefore is unfavorable for the recovery of parachute cabin door to recycle, has promoted the technical problem of unmanned aerial vehicle cost, the utility model provides an unmanned aerial vehicle with parachute cabin hatch door closing mechanism.
In order to solve the technical problem, the utility model discloses a following technical scheme:
an unmanned aerial vehicle with a parachute cabin door opening and closing mechanism comprises an unmanned aerial vehicle body, wherein a square parachute cabin for placing a parachute is arranged on the belly of the unmanned aerial vehicle body, a first parachute cabin door and a second parachute cabin door which are rotatably connected with the front side wall and the rear side wall of the parachute cabin are arranged at the bottom of the square parachute cabin, two rudder arms are connected to the side edges of the first parachute cabin door and the second parachute cabin door and respectively close to the front end and the rear end of a parachute cabin door which is rotatably connected with the front side wall and the rear side wall of the parachute cabin, an opening and closing mechanism for driving the parachute cabin door to open and close is arranged in the square parachute cabin and comprises a servo steering engine and a plurality of steel wire inhaul cables, the servo steering engine is fixedly connected to the top wall of the square parachute cabin above the parachute cabin door, the two rudder arms on the first parachute cabin door are respectively connected with one end of one steel wire inhaul cable, and, two rudder arms on the second parachute bay door are connected with one end of a steel wire cable respectively, the other end of the steel wire cable is connected with the other end of the diamond-shaped rocker arm of the servo steering engine, and the servo steering engine is electrically connected with an existing automatic pilot system of the unmanned aerial vehicle.
Compared with the prior art, the utility model provides an unmanned aerial vehicle with parachute cabin hatch door closing mechanism, when the flight in-process need release the parachute, give signal to servo steering wheel through unmanned aerial vehicle self current autopilot system earlier, servo steering wheel's rhombus rocking arm begins upwards to rotate by the level, drive first parachute cabin door and second parachute cabin door through steel wire cable and rudder arm and begin downwards to rotate by the level in step, the rhombus rocking arm when servo steering wheel is rotated to vertical direction by the level, first parachute cabin door and second parachute cabin door then are opened completely, parachute in the parachute cabin is automatic throwing under the action of gravity this moment, first parachute cabin door and second parachute cabin door accomplish under servo steering wheel drives and close after the parachute is successful, its closing process is opposite with the opening process. Parachute bay door closing mechanism in this application is applicable to the abdomen class aircraft that lands after unmanned aerial vehicle abdomen parachute bay is opened, the class aircraft is opened in unmanned aerial vehicle abdomen parachute bay no delay, the reliability is high, the parachute bay door after opening the cabin can not be released along with the parachute, therefore reuse when waiting to open the parachute next time, unmanned aerial vehicle use cost has effectively been practiced thrift, the parachute bay door can be closed after the parachute is succeeded to the while, therefore can perfectly avoid current parachute bay door release to open the damage that the back aircraft led to the fact the parachute bay in the twinkling of an eye in the landing.
Furthermore, the front end and the rear end of the first umbrella cabin door and the second umbrella cabin door are respectively provided with an integrally formed connecting shaft, and the connecting shafts extend into connecting holes preset in the front side wall and the rear side wall of the umbrella cabin to be matched and rotatably connected.
Furthermore, the side edges of the first umbrella cabin door and the second umbrella cabin door are rotatably connected with the left side wall and the right side wall of the umbrella cabin through mounting hinges.
Furthermore, the servo steering engine is fixedly connected to the top wall of the square umbrella cabin and is superposed with the left and right center lines of the first umbrella cabin door and the second umbrella cabin door below the servo steering engine.
Drawings
Fig. 1 is the utility model provides an unmanned aerial vehicle umbrella cabin door closing mechanism's cross-sectional structure sketch map.
FIG. 2 is a schematic bottom view of the first and second umbrella door of FIG. 1.
In the figure, 1, a first umbrella door; 10. a connecting shaft; 2. a second umbrella bay door; 3. a rudder arm; 4. a servo steering engine; 5. a steel wire inhaul cable; 6. a diamond-shaped rocker arm.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand and understand, the present invention is further explained by combining with the specific drawings.
In the description of the present invention, it is to be understood that the terms "longitudinal", "radial", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and to simplify the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1 and 2, the utility model provides an unmanned aerial vehicle with a parachute cabin door opening and closing mechanism, which comprises an unmanned aerial vehicle body, wherein the belly of the unmanned aerial vehicle body is provided with a square parachute cabin for placing a parachute, namely, the parachute is arranged in the square parachute cabin of the belly, the bottom of the square parachute cabin is provided with a first parachute cabin door 1 and a second parachute cabin door 2 which are rotatably connected with the front and rear side walls of the parachute cabin, the side edges of the first parachute cabin door 1 and the second parachute cabin door 2 are both connected with two rudder arms 3, the two rudder arms 3 are respectively close to the front and rear ends of the parachute cabin door which is rotatably connected with the front and rear side walls of the parachute cabin, namely, the two rudder arms 3 are respectively arranged at the front end and the rear end of the first parachute cabin door 1 and the second parachute cabin door 2 and correspondingly close to the front and rear side walls of the parachute cabin, the inside of the square parachute cabin is provided with an opening and closing mechanism for driving the first parachute cabin door 1, the opening and closing mechanism comprises a servo steering engine 4 and a plurality of steel wire inhaul cables 5, the servo steering engine 4 is fixedly connected to the top wall of the square umbrella cabin above the first umbrella cabin door 1 and the second umbrella cabin door 2, two rudder arms 3 on the first umbrella cabin door 1 are respectively connected with one end of one steel wire inhaul cable 5, the other end of the steel wire inhaul cable 5 is connected with one end of a diamond-shaped rocker arm 6 of the servo steering engine 4, namely the two rudder arms 3 on the first umbrella cabin door 1 are respectively connected with one end of the diamond-shaped rocker arm 6 of the servo steering engine 4 through one steel wire inhaul cable 5, the two rudder arms 3 on the second umbrella cabin door 2 are respectively connected with one end of one steel wire inhaul cable 5, the other end of the steel wire inhaul cable 5 is connected with the other end of the diamond-shaped rocker arm 6 of the servo steering engine 4, namely the two rudder arms 3 on the second, one end and the other end of the rhombic rocker arm 6 are just right opposite, so that four rudder arms 3 on the first parachute bay door 1 and the second parachute bay door 2 are respectively connected to the rhombic rocker arm 6 of the servo steering engine 4 through one steel wire inhaul cable 5 (four rudder arms in total), the servo steering engine 5 is electrically connected with an existing automatic pilot system of the unmanned aerial vehicle, namely, a signal is given out through the existing automatic pilot system of the unmanned aerial vehicle to control the linear servo steering engine to act, the specific control mode belongs to the prior art well known by the technical personnel in the field, and the description is omitted.
Compared with the prior art, the utility model provides an unmanned aerial vehicle with a parachute bay door opening and closing mechanism, when the parachute needs to be released in the flying process, a signal is sent to the servo steering engine through the existing automatic pilot system of the unmanned aerial vehicle, the diamond-shaped rocker arm of the servo steering engine rotates upwards from the horizontal position, the first umbrella cabin door and the second umbrella cabin door are driven to synchronously rotate downwards from the horizontal direction through the steel wire inhaul cable and the rudder arm, when the diamond-shaped rocker arm of the servo steering engine rotates to the vertical direction from the horizontal direction, the first umbrella cabin door and the second umbrella cabin door are completely opened, the opening directions of the first umbrella cabin door and the second umbrella cabin door are shown as arrows (dotted lines represent movement tracks) in the figure 1, a parachute in the umbrella cabin is automatically thrown out under the action of gravity, the first umbrella cabin door and the second umbrella cabin door are driven by the servo steering engine to complete closing after the parachute is successfully thrown, and the closing process is opposite to the opening process. Parachute bay door closing mechanism in this application is applicable to the abdomen class aircraft that lands after unmanned aerial vehicle abdomen parachute bay is opened, the class aircraft is opened in unmanned aerial vehicle abdomen parachute bay no delay, the reliability is high, the parachute bay door after opening the cabin can not be released along with the parachute, therefore reuse when waiting to open the parachute next time, unmanned aerial vehicle use cost has effectively been practiced thrift, the parachute bay door can be closed after the parachute is succeeded to the while, therefore can perfectly avoid current parachute bay door release to open the damage that the back aircraft led to the fact the parachute bay in the twinkling of an eye in the landing.
As a specific embodiment, please refer to fig. 2, the front and rear ends of the first and second umbrella chamber doors 1 and 2 are respectively provided with an integrally formed connecting shaft 10, the connecting shafts 10 extend into the connecting holes preset in the front and rear side walls of the umbrella chamber to be rotatably connected in a matching manner, that is, the first and second umbrella chamber doors 1 and 2 are rotatably connected with the front and rear side walls of the umbrella chamber by the insertion and matching of the connecting shafts 10 and the connecting holes, so as to ensure that the first and second umbrella chamber doors do not fall off from the umbrella chamber after the umbrella chamber doors are opened.
As another specific embodiment, the side edges of the first and second parachute bay doors 1 and 2 are rotatably connected to the left and right side walls of the parachute bay by mounting hinges, that is, the first and second parachute bay doors 1 and 2 are rotatably connected to the left and right side walls of the parachute bay by the existing hinges, and the specific mounting manner is the same as the rotatable connection manner of the existing door leaf and door frame, and therefore, the description is omitted.
As a specific embodiment, the servo steering engine 4 is fixedly connected to the top wall of the square umbrella cabin and is superposed with the left and right center lines of the first umbrella cabin door 1 and the second umbrella cabin door 2 below the square umbrella cabin, that is, the servo steering engine 4 is arranged right above the left and right center lines of the first umbrella cabin door 1 and the second umbrella cabin door 2, so that the first umbrella cabin door 1 and the second umbrella cabin door 2 can be opened and closed more stably, and the umbrella cabin is covered tightly.
Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.
Claims (4)
1. An unmanned aerial vehicle with a parachute cabin door opening and closing mechanism comprises an unmanned aerial vehicle body, wherein a square parachute cabin for placing a parachute is arranged on the belly of the unmanned aerial vehicle body, and the unmanned aerial vehicle is characterized in that a first parachute cabin door (1) and a second parachute cabin door (2) which are rotatably connected with the front side wall and the rear side wall of the parachute cabin are arranged at the bottom of the square parachute cabin, two rudder arms (3) are connected to the side edges of the first parachute cabin door (1) and the second parachute cabin door (2), the two rudder arms (3) are respectively close to the front end and the rear end of a parachute cabin door which is rotatably connected with the front side wall and the rear side wall of the parachute cabin, an opening and closing mechanism for driving the parachute cabin door to open and close is arranged inside the square parachute cabin and comprises a servo steering engine (4) and a plurality of steel wire inhaul cables (5), the servo steering engine (4) is fixedly connected to the top wall of the square parachute cabin door above the parachute cabin door, the two rudder arms (3, the other end of the steel wire inhaul cable is connected with one end of a diamond-shaped rocker arm (6) of the servo steering engine (4), two rudder arms (3) on the second parachute bay door (2) are connected with one end of a steel wire inhaul cable (5) respectively, the other end of the steel wire inhaul cable is connected with the other end of the diamond-shaped rocker arm (6) of the servo steering engine (4), and the servo steering engine (4) is electrically connected with an existing autopilot system of the unmanned aerial vehicle.
2. The unmanned aerial vehicle with the parachute bay door opening and closing mechanism according to claim 1, wherein integrally formed connecting shafts (10) are respectively arranged at the front end and the rear end of the first parachute bay door (1) and the second parachute bay door (2), and the connecting shafts (10) extend into connecting holes preset in the front side wall and the rear side wall of the parachute bay to be matched and rotatably connected.
3. The unmanned aerial vehicle with parachute bay door opening and closing mechanism of claim 1, wherein the sides of the first parachute bay door (1) and the second parachute bay door (2) are rotatably connected to the left and right side walls of the parachute bay by mounting hinges.
4. The unmanned aerial vehicle with the parachute bay door opening and closing mechanism according to claim 1, wherein the servo steering engine (4) is fixedly connected to the top wall of the square parachute bay and coincides with the left and right center lines of the first parachute bay door (1) and the second parachute bay door (2) below.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020081631.1U CN211391654U (en) | 2020-01-14 | 2020-01-14 | Unmanned aerial vehicle with parachute bay door closing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020081631.1U CN211391654U (en) | 2020-01-14 | 2020-01-14 | Unmanned aerial vehicle with parachute bay door closing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211391654U true CN211391654U (en) | 2020-09-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020081631.1U Active CN211391654U (en) | 2020-01-14 | 2020-01-14 | Unmanned aerial vehicle with parachute bay door closing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211391654U (en) |
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2020
- 2020-01-14 CN CN202020081631.1U patent/CN211391654U/en active Active
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder |
Address after: 401120 16-6, building 1, No. 1228, Jinkai Avenue, Liangjiang New Area, Yubei District, Chongqing Patentee after: CHONGQING TONGHUI EXPLORATION PROGRAM Co.,Ltd. Address before: 401122 No. 16, No. 18, Qixia Road, Beibu new area, Chongqing Patentee before: CHONGQING TONGHUI EXPLORATION PROGRAM Co.,Ltd. |
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| CP02 | Change in the address of a patent holder |