CN211076332U

CN211076332U - Spliced aircraft

Info

Publication number: CN211076332U
Application number: CN201921434271.2U
Authority: CN
Inventors: 田悦丰
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-08-31
Filing date: 2019-08-31
Publication date: 2020-07-24
Anticipated expiration: 2029-08-31

Abstract

The utility model discloses a spliced aircraft, including rotary mechanism and connecting rod, rotary mechanism is used for connecting the connecting rod, constitutes collapsible frame, and all or part of rotary mechanism department installs driving system, rotary mechanism includes first group's connection piece and the second group connection piece of placing of overlapping in turn, first group's connection piece and the second group connection piece all have two or more, be equipped with circular port and plug end on all the connection pieces, two sets of connection pieces are through running through in the public pivot rotatable connection of circular port; each end of the connecting rod is provided with a jack matched with the plug of the first group of connecting sheets or a jack matched with the plug of the second group of connecting sheets, and the jacks are used for being connected with the plugs in an inserting mode. The utility model discloses a concatenation formula aircraft makes simply, intensity is big, easy installation, portable, easy maintenance.

Description

Spliced aircraft

Technical Field

The utility model relates to an aircraft technical field, concretely relates to many rotors class aircraft, especially concatenation formula aircraft.

Background

The aircrafts may be classified into military aircrafts, which may be classified into reconnaissance aircrafts, decoy aircrafts, electronic countermeasure aircrafts, communication relay aircrafts, unmanned fighters, target planes, etc., and civil aircrafts may be classified into patrol/monitor aircrafts, agricultural aircrafts, meteorological aircrafts, exploration aircrafts, surveying and mapping aircrafts, etc.

The existing aircraft has complex structure and various components, not only has high requirements on production process and materials, but also has the problem that the maneuverability of the aircraft is reduced by at least one percent when the weight of the aircraft body is increased by one percent when the power of an engine is constant, and the service problem is serious.

Accordingly, there is a need in the art for new aircraft structural solutions.

SUMMERY OF THE UTILITY MODEL

There is above-mentioned technical problem to prior art, the utility model provides a universalization, modularization, standardized aircraft organism structural system, especially a concatenation formula aircraft of making simply, intensity is big, easy installation, portable.

In order to achieve the above purpose, the utility model provides a splicing type aircraft, the aircraft comprises a rotating mechanism and a connecting rod, the rotating mechanism is used for connecting the connecting rod to form a foldable frame, a power system is arranged at all or part of the rotating mechanism,

the rotating mechanism comprises a first group of connecting pieces and a second group of connecting pieces which are alternately overlapped, the first group of connecting pieces and the second group of connecting pieces are two or more, all the connecting pieces are provided with circular holes and plug ends,

the two groups of connecting sheets are rotatably connected through a common rotating shaft penetrating through the circular hole;

each end of the connecting rod is provided with a jack matched with the plug of the first group of connecting sheets or a jack matched with the plug of the second group of connecting sheets, and the jacks are used for being connected with the plugs in an inserting mode.

In one embodiment, the connecting sheet is a single-ended connecting sheet or a double-ended connecting sheet, the single-ended connecting sheet is positioned at the edge of the foldable frame and comprises a circular hole at one end and a plug at the other end, and the plug of each set of single-ended connecting sheets is plugged with one connecting rod; the double-end connecting piece is positioned in the middle of the foldable frame and comprises a circular hole positioned in the center and plugs positioned at two ends, and the plugs at two ends of each group of connecting pieces are respectively spliced with one connecting rod.

In one embodiment, the connecting rod comprises a rod body and connectors at two ends, and the connectors are used for being plugged with the plugs.

In one embodiment, the connecting rod has a hollow cavity.

In one embodiment, the connecting rod has a hollow cavity in which any one or more selected from the group consisting of: the device comprises a power module, a control module, a communication module and an energy module.

In one embodiment, the power system is disposed on the common shaft.

In one embodiment, the powered system is distributed discretely on the collapsible frame.

In one embodiment, the thickness of each of the two sets of tabs is the same for one rotation mechanism, and may be different.

In one embodiment, for a rotational mechanism, the pins of the first and second sets of tabs are bent toward each other such that the inserted connecting bars are parallel to each other.

In one embodiment, the curvature of the first set of tabs and the second set of tabs is mirror image of the curvature of a rotating mechanism.

In one embodiment, the first set of tabs and the second set of tabs are the same number for one rotation mechanism.

In one embodiment, for a rotational mechanism, a braking mechanism is further included to fix the angle between the first set of tabs and the second set of tabs.

Compared with the prior art, the utility model discloses a concatenation formula aircraft makes simply, intensity is big, easy installation, portable, easy maintenance.

Drawings

Non-limiting and non-exhaustive embodiments of the present invention are described, by way of example, with reference to the following drawings, in which:

fig. 1 is the utility model discloses a concatenation formula aircraft's expansion state schematic diagram.

Fig. 2 is the folding state schematic diagram of the spliced aircraft of the utility model.

Fig. 3 is a schematic structural diagram of the rotating mechanism of the spliced aircraft of the present invention including a first set of connecting pieces (a and B) and a second set of connecting pieces (a 'and B') alternately stacked.

Fig. 4 is a schematic structural view of the insertion hole of the connecting rod end of the spliced aircraft according to the invention, showing two schematic structures (a and B) and a side schematic perspective view (C) of the front view of the connecting rod end.

Fig. 5 is the utility model discloses a structural schematic of the public pivot of concatenation formula aircraft.

Detailed Description

Hereinafter, embodiments of the present disclosure are described with reference to the drawings. The following detailed description and drawings are included to illustrate the principles of the disclosure, which is not to be limited to the preferred embodiments described, but is to be defined by the claims. The disclosure will now be described in detail with reference to exemplary embodiments thereof, some of which are illustrated in the accompanying drawings. The following description refers to the accompanying drawings, in which like reference numerals refer to the same or similar elements in different drawings unless otherwise indicated. The aspects described in the following exemplary embodiments do not represent all aspects of the present disclosure. Rather, these aspects are merely examples of a spliced aircraft of the various aspects of the present disclosure recited in the appended claims.

The spliced aircraft of the embodiment is shown in fig. 1 to 5. Fig. 1 is the utility model discloses a concatenation formula aircraft's expansion state schematic diagram. Fig. 2 is the folding state schematic diagram of the spliced aircraft of the utility model. Spliced aircraft comprises a rotary mechanism 1 and a connecting rod 2, wherein the rotary mechanism 1 is used for connecting the connecting rod 2 to form a foldable frame, and a power system, such as a propeller 3, is arranged at all or part of the rotary mechanisms 1 and 1'. The connecting rod 2 may have a hollow cavity. Hollow chamber can be used for assisting the heat dissipation with the leading-in motor of air is inside, and the one end in hollow chamber can set up air filtration system inside with the separation pollutant entering motor. The connecting rod 2 can also be made into a cabin as required, so as to accommodate the load needing to be loaded in the cabin. For example, the connecting rod 2 can be made as a connecting cabin that can carry and carry the required loads both inside and outside, such as the avionics system, energy sources (batteries or fuel oil, etc.) required by the aircraft itself. The rotary mechanism 1, 1' comprises connecting tabs, all of which are rotatably connected by a common shaft 4 extending through the circular hole. The foldable frame can carry a detachable load 5. After the aircraft is unfolded, the geometrical angle of the aircraft fuselage can be fixed by connecting the foldable frame with 2, 3, 4 or more connecting rods of the aircraft. Dimensional changes in this foldable frame can result in changes in the geometric angles of the aircraft fuselage. In one example, the power system, such as propellers, are distributed discretely on the collapsible frame such that reactive torque generated by individual drive units in the aircraft is isolated from digestion to prevent malignant stress build-up that reduces body life. And energy waste caused by uneven force can be prevented.

Fig. 3 is a schematic structural diagram of the rotating mechanism of the spliced aircraft of the present invention including a first set of connecting pieces (a and B) and a second set of connecting pieces (a 'and B') alternately stacked. The rotary mechanism 1,1 ' comprises a first group of connecting pieces (A and B) and a second group of connecting pieces (A ' and B ') which are alternately overlapped, two or more connecting pieces are arranged on the first group of connecting pieces (A and B) and the second group of connecting pieces (A ' and B '), a circular hole 11 and a plug end 12 are arranged on all the connecting pieces, and the two groups of connecting pieces (A and B; A ' and B ') are rotatably connected through a common rotating shaft penetrating through the circular hole 11. The rotating mechanism 1 comprises a double-end connecting piece (see fig. 3A, A '), the double-end connecting piece is positioned in the middle of the foldable frame (see fig. 1 and 2), the double-end connecting piece comprises a circular hole 11 positioned in the center and plugs 12 positioned at two ends, and the plugs 12 at two ends of each group of connecting pieces (A or A') are respectively inserted into one connecting rod 2. The rotating mechanism 1 'comprises single-end connecting sheets, the single-end connecting sheets are located on the edge of the foldable frame and comprise circular holes 11 located at one end and plugs 12 located at the other end, and the plugs 12 of each group of single-end connecting sheets (B or B') are connected with one connecting rod 2 in an inserting mode. The plug 13 may optionally have a positioning hole for fixing after being inserted into the connecting rod 2. In one example, for a rotating mechanism, a braking mechanism is further included to fix the angle between the first set of connecting plates and the second set of connecting plates. In one example, the thickness of each of the two sets of tabs is the same for one rotation mechanism to facilitate opening of the receptacles of the connecting rods. Alternatively, the thickness of each lug of the two sets of lugs may be the same or different, in particular to optimize the stress and fuselage weight reduction. For example, rotary mechanism fittings are manufactured with thickness and complex geometry adjustments based on the amount of stroke force required in each direction in order to reduce unnecessary "dead weight". In one example, for a rotating mechanism, the pins of the first and second sets of connecting tabs are bent towards each other so that the inserted connecting rods are parallel to each other. In one example, the curvature of the first set of tabs and the second set of tabs is mirror symmetric for a single rotational mechanism. The effect of the folded foldable frame is then as shown in fig. 2, which is more space-saving and more resistant to deformation. In one example, the first set of tabs and the second set of tabs are the same number, e.g., both 2 or 3, for a single rotational mechanism.

Fig. 4 is a schematic structural view of the insertion hole of the connecting rod end of the spliced aircraft according to the invention, showing two schematic structures (a and B) and a side schematic perspective view (C) of the front view of the connecting rod end. Each end of the connecting rod 2 has a

socket

21, 23 matching the plug 12 of the first set of connecting tabs (a and B) or a

socket

22, 24 matching the plug 12 of the second set of connecting tabs (a 'and B') for plugging with the plug 12. In one example, the connecting rod comprises a rod body and connectors at two ends, and the connectors are used for being plugged with the plugs. In one example, the connecting rod has a hollow cavity. In a more specific example, the connecting rod has a hollow cavity in which any one or more selected from the group consisting of: a power module, a control module, a communication module, an energy module, such as a battery.

Fig. 5 is a schematic structural diagram of the common rotating shaft 4 of the spliced aircraft. For each rotary mechanism 1, 1', the common shaft 4 extends through the rotatable connection of the circular holes 11 of all the coupling pieces. The common shaft 4 is secured by a lower bolt arrangement 42 and an upper bracket 43 may be used to mount a power system, such as a propeller 3. Preferably, the common rotating shaft 4 has holes 44 penetrating all the connecting pieces, and after the connecting pieces are adjusted to a proper angle, the positions of the common rotating shaft 4 and the two groups of connecting pieces are fixed by inserting fixing rods.

The utility model discloses a concatenation is extended in the structure, can infinitely make up, forms the concatenation formula aircraft of various big or small demands. Therefore, the utility model discloses a concatenation formula aircraft makes simply, intensity is big, easy installation, portable. When the aircraft breaks down, can normally drop into use once more fast through changing the module, only need in addition to the module that breaks down maintain can, need not (through the complete machine decomposition maintenance) to inspect the complete machine, saved cost of maintenance, improved work efficiency greatly.

It should be finally noted that the above embodiments are only intended to illustrate the technical solutions of the present invention, and not to limit the scope of the present invention, and 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 technical solutions of the present invention can be modified or replaced with equivalents without departing from the spirit and scope of the technical solutions of the present invention. Also, the respective technical features described above may be arbitrarily combined. Although not all possible combinations of features are described, any combination of features should be considered to be covered by the present specification as long as there is no contradiction between such combinations.

While the invention has been described in connection with embodiments, it is to be understood by those skilled in the art that the foregoing description and drawings are merely illustrative and not restrictive of the broad invention, and that the invention is not limited to the disclosed embodiments. Various modifications and variations are possible without departing from the spirit of the invention.

Claims

1. A spliced aircraft is characterized by comprising a rotating mechanism and a connecting rod, wherein the rotating mechanism is used for connecting the connecting rod to form a foldable frame, a power system is arranged at all or part of the rotating mechanism,

the rotating mechanism comprises a first group of connecting pieces and a second group of connecting pieces which are alternately overlapped, one or more connecting pieces are arranged on the first group of connecting pieces and the second group of connecting pieces, a circular hole and a plug end are arranged on all the connecting pieces,

2. The spliced aircraft of claim 1, wherein the connecting pieces are single-ended connecting pieces or double-ended connecting pieces, the single-ended connecting pieces are located at the edges of the foldable frame and comprise circular holes at one end and plugs at the other end, and the plugs of each set of single-ended connecting pieces are plugged with one connecting rod; the double-end connecting piece is positioned in the middle of the foldable frame and comprises a circular hole positioned in the center and plugs positioned at two ends, and the plugs at two ends of each group of connecting pieces are respectively spliced with one connecting rod.

3. Spliced aircraft according to claim 1 or 2, characterized in that the connecting rod comprises a rod body and two end connectors for plugging with the plugs.

4. Spliced aircraft according to claim 1 or 2, characterized in that the power system is arranged on the common shaft.

5. Spliced aircraft according to claim 1 or 2, characterized in that the connecting rod has a hollow cavity.

6. Spliced aircraft according to claim 1 or 2, characterized in that the power system is distributed decentrally over the foldable frame.

7. Spliced aircraft according to claim 1 or 2, characterized in that for a rotating mechanism the plugs of the first and second set of connection tabs are bent towards each other so that the plugged connection bars are parallel to each other.

8. Spliced aircraft according to claim 1 or 2, characterized in that the curvature of the first and second set of webs is mirror-symmetrical for one rotation mechanism.

9. Spliced aircraft according to claim 1 or 2, characterized in that the number of the first and second set of webs is the same or different for one rotation mechanism.

10. Spliced aircraft according to claim 1 or 2, characterized in that it further comprises, for one rotation mechanism, a braking mechanism for fixing the angle between the first set of lugs and the second set of lugs.