CN210882648U - Docking mechanism for aircraft and carrying bin - Google Patents
Docking mechanism for aircraft and carrying bin Download PDFInfo
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- CN210882648U CN210882648U CN201920512579.8U CN201920512579U CN210882648U CN 210882648 U CN210882648 U CN 210882648U CN 201920512579 U CN201920512579 U CN 201920512579U CN 210882648 U CN210882648 U CN 210882648U
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Abstract
The utility model discloses a docking mechanism of an aircraft and a carrying bin, which comprises a docking cavity arranged on any one of the aircraft and the carrying bin; a docking boss disposed on the other of the aircraft and the carrier pod, the docking boss being embeddable within the docking cavity; a first locking member disposed within the docking cavity; the second locking piece is arranged on the butt joint boss and matched with the first locking piece, at least one of the first locking piece and the second locking piece is a telescopic active locking piece, and the first locking piece and the second locking piece are locking hooks; or one of the first locking piece and the second locking piece is a locking hook, the other one is a locking plate, and a locking hole corresponding to the locking hook is formed in the locking plate. The docking mechanism can realize rapid positioning and locking in the docking process of the aircraft and the carrying bin, and rapid and convenient unlocking in the separation process and separation of the aircraft and the carrying bin.
Description
Technical Field
The utility model relates to an aircraft design production technical field, more specifically the docking mechanism of an aircraft and delivery storehouse that says so.
Background
With the progress of urban three-dimensional traffic technology, low-altitude aircrafts (such as flying cars) with carrying functions have become a development trend. The low-altitude aircraft is mainly applied to urban low-altitude environments, the buffer distance between the low-altitude aircraft and the ground is short in the landing process, and how to safely and stably land is one of the focuses of attention of those skilled in the art at present.
In order to reduce the burden of parachute line itself, the delivery storehouse and the separable delivery aircraft concept of aircraft appear gradually, under the normal flight condition, aircraft and delivery storehouse link to each other through docking mechanism and form wholly, and the aircraft carries the delivery storehouse and carries out goods or passenger's transportation, and in case meet special circumstances and need promptly when descending, docking mechanism between aircraft and the delivery storehouse can break away from, and the delivery storehouse realizes steadily descending through the parachute, and the aircraft can glide to unmanned area and descend.
The appearance of detachable delivery vehicle concept makes the parachute cord of parachute only need bear the weight in delivery compartment, need not to bear the weight of aircraft simultaneously, and the reliability of parachute cord consequently obtains the guarantee, however, how to provide suitable docking mechanism to guarantee convenient butt joint and separation of aircraft and delivery compartment still is the technical problem that technical staff in this field need to solve urgently at present.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model discloses an aircraft and docking mechanism of delivery storehouse to can guarantee convenient butt joint and the separation of aircraft and delivery storehouse.
In order to achieve the above object, the utility model discloses an aircraft and delivery compartment's docking mechanism, include:
a docking cavity disposed on either the aircraft or the carrier pod;
a docking boss disposed on the other of the aircraft and the carrier pod, the docking boss being embeddable within the docking cavity;
a first locking member disposed within the docking cavity;
the second locking piece is arranged on the butt joint boss and matched with the first locking piece, wherein the first locking piece and the second locking piece are both telescopic active locking pieces;
the shape of the butt joint boss is consistent with the shape of the inner cavity of the butt joint cavity;
the first locking piece and the second locking piece are both locking hooks, the locking hooks are mutually buckled to realize locking when extending out, and the locking hooks are separated when retracting; or one of the first locking piece and the second locking piece is a locking hook, the other one is a locking plate, and a locking hole corresponding to the locking hook is formed in the locking plate.
Preferably, the docking cavity is arranged at the top of the carrying bin, and the docking boss is arranged at the bottom of the aircraft.
Preferably, the docking cavity doubles as an umbrella chamber for accommodating a parachute, and the parachute is embedded in the bottom of the docking cavity.
Preferably, the cross section of the inner cavity of the butt joint cavity is rectangular, and a cover plate for covering the parachute is further rotatably arranged on the inner wall of the butt joint cavity.
In the docking mechanism of the aircraft and the carrying bin disclosed in the utility model, the aircraft and the carrying bin are integrally positioned through the docking boss and the docking cavity, the active locking piece in the first locking piece and the second locking piece extends out, and the first locking piece and the second locking piece are matched to realize mutual locking, so that the aircraft is prevented from being separated from the carrying bin; when the aircraft needs to be separated from the carrying bin, the active locking pieces in the first locking piece and the second locking piece retract, and the locking state is released, so that the aircraft can be smoothly separated from the carrying bin.
Therefore, the utility model discloses a docking mechanism can realize quick location and the locking of aircraft and delivery storehouse butt joint in-process to and quick convenient unblock and the separation of realization aircraft and delivery storehouse in the disengaging process.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of an aircraft disclosed in an embodiment of the present invention;
fig. 2 is a schematic structural view of a disclosed carrier bin in an embodiment of the present invention;
fig. 3 is a schematic structural view of the carrying cabin and the flying body in the embodiment of the present invention after being docked;
fig. 4 is a schematic structural view of the docking boss disclosed in the embodiment of the present invention;
fig. 5 is a schematic structural view of the docking cavity disclosed in the embodiment of the present invention;
fig. 6 is a schematic view of a locking structure of the docking station and the docking cavity disclosed in the embodiment of the present invention;
fig. 7 is a schematic view of the falling process of the disclosed carrier vehicle after being separated from the aircraft.
Wherein, 1 is the aircraft, 2 is the delivery storehouse, 11 is the butt joint boss, 12 is the locking recess, 21 is the butt joint cavity, 22 is the apron, 23 is the locking arch, 24 is the parachute package.
Detailed Description
The core of the utility model is to provide an aircraft and delivery storehouse's docking mechanism to can guarantee convenient butt joint and the separation of aircraft and delivery storehouse.
In order to make the technical solution of the present invention better understood, the following description is given with reference to the accompanying drawings in the embodiments of the present invention, and the technical solution in the embodiments of the present invention is clearly and completely described. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 7, the docking mechanism for an aircraft and a carrying cabin disclosed in this embodiment includes a docking cavity 21, a docking boss 11, a first locking member and a second locking member, the docking cavity 21 is disposed on any one of the aircraft 1 and the carrying cabin 2, the docking boss 11 is disposed on the other one of the aircraft 1 and the carrying cabin 2, the docking boss 11 and the docking cavity 21 are matched with each other, the docking boss 11 can be embedded into the docking cavity 21, the first locking member is disposed in the docking cavity 21, the second locking member is disposed on the docking boss 11, the first locking member and the second locking member are matched with each other to realize docking locking of the aircraft 1 and the carrying cabin 2, and at least one of the first locking member and the second locking member is an active locking member capable of extending and contracting.
The aircraft 1 and the carrying bin 2 are integrally positioned through the butt joint boss 11 and the butt joint cavity 21, the active locking piece of the first locking piece and the active locking piece of the second locking piece extend out, and mutual locking is realized through the matching of the first locking piece and the second locking piece, so that the aircraft 1 is prevented from being separated from the carrying bin 2; when the aircraft 1 needs to be separated from the carrying cabin 2, the active locking pieces in the first locking piece and the second locking piece retract, and the locking state is released, so that the aircraft 1 is smoothly separated from the carrying cabin 2.
It is understood that the basic positioning of the aircraft 1 and the carrying cabin 2 during the docking process can be realized as long as the docking boss 11 can be embedded into the docking cavity 21, and in order to further improve the docking accuracy and the docking efficiency, the shape of the docking boss 11 in the present embodiment is consistent with the shape of the inner cavity of the docking cavity 21, and the size of the docking boss 11 is matched with the inner cavity of the docking cavity 21.
In one embodiment, the docking cavity 21 is disposed at the top of the carrying bin 2, and the docking boss 11 is disposed at the bottom of the aircraft 1, as shown in fig. 1 and 2, of course, the docking cavity 21 is not limited to be disposed at the bottom of the carrying bin 2, for example, depending on the actual shape of the carrying bin 2, the docking cavity 21 may be disposed at the side of the carrying bin 2, and the docking boss 11 may be disposed at a position on the aircraft 1 corresponding to the docking cavity 21; in addition, it is also possible to arrange the docking cavity 21 on the aircraft 1 and the docking boss 11 on the delivery bay 2, in which case it is optimal to arrange the docking cavity 21 at the bottom of the aircraft 1 and the docking boss 11 at the top of the delivery bay 2.
The active locking member may be a locking post or a locking hook, the structure matched with the locking post is generally a locking groove, and the structure matched with the locking hook is generally a locking hole, in this embodiment, the first locking member is specifically an active locking member, the first locking member is a locking protrusion 23 capable of extending out and retracting into the inner wall of the docking cavity 21, as shown in fig. 5 and 6, and the second locking member is a locking groove 12 opened on the docking boss 11 and corresponding to the locking protrusion 23, as shown in fig. 4 and 6.
As a preferable mode, the locking protrusion 23 is a strip-shaped protrusion surrounding a circumference of the inner wall of the docking cavity 21, as shown in fig. 5, and correspondingly, the locking groove 12 is a strip-shaped groove (or referred to as an annular groove) surrounding a circumference of the docking boss 11.
Of course, those skilled in the art can also provide a plurality of locking protrusions 23, and the locking protrusions 23 are intermittently arranged along the circumferential direction of the inner wall of the docking cavity 21, and correspondingly, the locking grooves 12 should also be provided in a plurality of numbers, and the locking grooves 12 are intermittently arranged along the circumferential direction of the docking boss 11.
The driving mechanism capable of driving the locking projection 23 to extend and retract is not limited to one, and for example, an electric push rod is used to drive the locking projection 23 to extend and retract; the slide block in the screw slide block mechanism can be connected with the locking protrusion 23, so that the locking protrusion 23 can extend and retract, and even a micro piston cylinder (an air cylinder or an oil cylinder) can be used for driving the locking protrusion 23 to extend and retract.
In another embodiment, the second locking member is an active locking member, the first locking member is a locking groove 12 opened on the inner wall of the docking cavity 21, and the second locking member is a locking protrusion 23 which can extend out and retract into the docking boss 11 and corresponds to the locking groove 12.
In addition, the first locking piece and the second locking piece can be active locking pieces, for example, the first locking piece and the second locking piece are locking hooks, the locking hooks are mutually buckled to realize locking when extending out, and the locking hooks are separated when retracting; or one of the first locking piece and the second locking piece is a locking hook, the other one is a locking plate, and a locking hole corresponding to the locking hook is formed in the locking plate.
Referring to fig. 5, in order to further expand the function of the docking cavity 21, the docking cavity 21 in this embodiment is also used as a parachute bay for accommodating a parachute, and the parachute is embedded at the bottom of the docking cavity 21, so that the whole docking mechanism can further provide a space for accommodating the parachute, and the conventional parachute accommodating cavity and the docking mechanism are combined into one, so that the overall structure formed by docking the aircraft and the carrying bay is simplified, and the appearance is also beautified.
The shape of the inner cavity of the docking cavity 21 is not limited, and in view of convenience in production and manufacture, the inner cavity of the docking cavity 21 in this embodiment has a rectangular cross section, as shown in fig. 5, a parachute is usually accommodated in the parachute bag 24, and in order to protect the parachute bag 24, a cover plate 22 for covering the parachute bag 24 is rotatably provided on the inner wall of the docking cavity 21 in this embodiment, the cover plate 22 may be specifically two, and the two cover plates 22 are hinge-mounted on the inner wall of the docking cavity 21 by hinges, thereby forming a split door type, as shown in fig. 5.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (4)
1. An aircraft and delivery compartment docking mechanism, comprising:
a docking cavity (21) provided on either of the aircraft (1) and the carrier pod (2);
a docking boss (11) provided on the other of the aircraft (1) and the carrier bay (2), the docking boss (11) being insertable into the docking cavity (21);
a first locking member disposed within the docking cavity (21);
the second locking piece is arranged on the butt joint boss (11) and matched with the first locking piece, wherein the first locking piece and the second locking piece are both telescopic active locking pieces;
the shape of the butt joint boss (11) is consistent with the shape of an inner cavity of the butt joint cavity (21);
the first locking piece and the second locking piece are both locking hooks, the locking hooks are mutually buckled to realize locking when extending out, and the locking hooks are separated when retracting; or one of the first locking piece and the second locking piece is a locking hook, the other one is a locking plate, and a locking hole corresponding to the locking hook is formed in the locking plate.
2. The docking mechanism according to claim 1, characterized in that the docking cavity (21) is arranged at the top of the carrier magazine (2) and the docking boss (11) is arranged at the bottom of the aircraft (1).
3. A docking mechanism according to claim 1 or 2, characterized in that the docking chamber (21) doubles as a canopy for accommodating a parachute, which is built into the bottom of the docking chamber (21).
4. A docking mechanism according to claim 3 characterised in that the cross section of the inner cavity of the docking chamber (21) is rectangular and the inner wall of the docking chamber (21) is also provided with a cover plate (22) for covering the parachute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920512579.8U CN210882648U (en) | 2019-04-16 | 2019-04-16 | Docking mechanism for aircraft and carrying bin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920512579.8U CN210882648U (en) | 2019-04-16 | 2019-04-16 | Docking mechanism for aircraft and carrying bin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210882648U true CN210882648U (en) | 2020-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920512579.8U Active CN210882648U (en) | 2019-04-16 | 2019-04-16 | Docking mechanism for aircraft and carrying bin |
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| CN (1) | CN210882648U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891373A (en) * | 2020-07-27 | 2020-11-06 | 淮阴工学院 | Multi-position split type land air-berthing unmanned aerial vehicle |
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2019
- 2019-04-16 CN CN201920512579.8U patent/CN210882648U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891373A (en) * | 2020-07-27 | 2020-11-06 | 淮阴工学院 | Multi-position split type land air-berthing unmanned aerial vehicle |
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