CN214648984U

CN214648984U - Carbon fiber gyroplane frame

Info

Publication number: CN214648984U
Application number: CN202120943040.5U
Authority: CN
Inventors: 窦金波
Original assignee: Jiaxing Hesheng New Material Technology Co ltd
Current assignee: Jiaxing Hesheng New Material Technology Co ltd
Priority date: 2021-04-30
Filing date: 2021-04-30
Publication date: 2021-11-09
Anticipated expiration: 2031-04-30

Abstract

The utility model discloses a carbon fiber rotorcraft frame, which comprises a flying seat and a plurality of rotor assemblies arranged around the flying seat, wherein the rotor assemblies are fixedly arranged outside the flying seat through support arms, the support arms are provided with landing leg assemblies, and the landing leg assemblies are movably connected with the side parts of the support arms; the supporting leg assembly comprises a supporting leg rod, the supporting leg rod is connected to the side part of the supporting arm, a locking and supporting rod is connected between the supporting leg rod and the supporting arm, one end of the locking and supporting rod is connected to the supporting leg rod, and the other end of the locking and supporting rod is connected to the side part of the supporting arm through a pin; the lateral part of flying seat still is equipped with the supporting seat, and supporting seat sliding connection is at the lateral part of flying seat, and the supporting seat includes the bracing piece of base and fixed mounting at the base both ends, bracing piece and the lateral part sliding connection of flying seat. The utility model discloses be equipped with the slidable supporting seat to the taking in of aircraft frame that can be convenient for reduces aircraft frame's air combat occupancy.

Description

Carbon fiber gyroplane frame

Technical Field

The utility model relates to an aircraft frame, in particular to carbon fiber rotor aircraft frame.

Background

When the rotor unmanned aerial vehicle is used, the rotor unmanned aerial vehicle generally needs to be supported by an aircraft frame. Current rotor unmanned aerial vehicle when not using, because do not set up corresponding bearing structure in the aircraft frame, the aircraft frame has two kinds of modes to accomodate when accomodating: one is to carry a set of support equipment in addition for supporting the airframe, and when placing the airframe, usually put the frame vertically to save space, and the other is directly to lie the airframe flat, but this kind of practice can lead to the airframe to occupy great space. It can be seen from this that current rotor unmanned aerial vehicle, in the aspect of accomodating, is very inconvenient.

SUMMERY OF THE UTILITY MODEL

In order to solve the deficiencies in the prior art, the utility model aims to provide a carbon fiber gyroplane frame is equipped with the slidable supporting seat in this gyroplane frame to the taking in of aircraft frame that can be convenient for reduces the air combat occupancy of aircraft frame.

The utility model provides a technical scheme that its technical problem adopted does: a carbon fiber rotor wing aircraft frame comprises a flight seat and a plurality of rotor wing assemblies arranged around the flight seat, wherein the rotor wing assemblies are fixedly arranged on the outer side of the flight seat through support arms, the support arms are also provided with support leg assemblies, and the support leg assemblies are movably connected to the side parts of the support arms;

the supporting leg assembly comprises a supporting leg rod, the supporting leg rod is connected to the side part of the supporting arm, a locking and supporting rod is further connected between the supporting leg rod and the supporting arm, one end of the locking and supporting rod is connected to the supporting leg rod, and the other end of the locking and supporting rod is connected to the side part of the supporting arm through a pin;

the lateral part of flight seat still is equipped with the supporting seat, supporting seat sliding connection be in the lateral part of flight seat, the supporting seat includes base and the bracing piece of fixed mounting at the base both ends, the bracing piece with the lateral part sliding connection of flight seat.

Optionally, sleeves for slidably connecting the support rods are fixedly installed in the middle of the side portions of the two sides of the flying seat respectively, and the support rods are slidably connected in the sleeves;

the length of the supporting rod is equal to the length of the side part of the flying seat.

Optionally, a blocking piece matched with the opening of the sleeve is arranged on the rod body of the supporting rod, so that after the supporting rod is pulled out of the sleeve, the supporting rod is prevented from sliding into the sleeve by the blocking piece.

Optionally, the blocking piece comprises mounting grooves which are arranged on the body of the support rod and symmetrically distributed, a blocking rod is hinged in the mounting groove, a triangular block is fixedly connected to the body of the outer side of the blocking rod, and the top of the triangular block is a plane;

the triangular block is characterized in that a first spring is connected between one side, away from the triangular block, of the blocking rod and the bottom of the mounting groove, the length of the notch of the mounting groove is smaller than that of the blocking rod, and the blocking rod is limited in the mounting groove.

Optionally, one end of the flying seat far away from the base is fixedly connected with a counterweight seat with the same specification as the base.

Optionally, a spring fastener is arranged between the base and the flying seat, a sub-fastener of the spring fastener is fixed on the side face of the base facing the end part of the flying seat, and a female fastener of the spring fastener is fixed on the end part of the flying seat far away from the counterweight seat.

Optionally, a support leg is arranged at the bottom of the support leg rod, and the support leg is connected with the bottom of the support leg rod through a second spring.

Adopt above-mentioned technical scheme, the utility model discloses lateral part slidable mounting at the flight seat has the supporting seat, when the aircraft uses, can receive the supporting seat, and when needs were accomodate the aircraft, can expand the supporting seat, carries out vertical support to the frame of aircraft to the aircraft of being convenient for accomodate, satisfied the demand that space occupancy is little simultaneously.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is a schematic structural view of the support base of the present invention;

FIG. 3 is a schematic view of the connection between the support base and the sleeve according to the present invention;

FIG. 4 is an enlarged view of portion A of FIG. 3;

fig. 5 is a schematic structural diagram of the leg assembly of the present invention.

Detailed Description

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1, the utility model discloses a carbon fiber gyroplane frame, it is including flying seat 1 and locating a plurality of rotor subassembly 2 around flying seat 1, and rotor subassembly 2 passes through support arm 3 fixed mounting in the outside of flying seat 1, is equipped with on the support arm 3 and still is equipped with landing leg assembly 4, and landing leg assembly 4 swing joint is at the lateral part of support arm 3. Wherein, rotor subassembly and support arm 3 are the subassembly commonly used in the unmanned aerial vehicle field, do not do too much repeated description in this specification.

The utility model discloses in, landing leg subassembly 4 is installed in support arm 3, compares in prior art, installs landing leg subassembly 4 on flight seat 1, has practiced thrift the space on the flight seat 1 to be favorable to the overall arrangement in the flight seat 1. Specifically, as shown in fig. 5, the leg assembly 4 includes a leg bar 401, the leg bar 401 is connected to the side of the support arm 3, and a lock bar 402 is further connected between the leg bar 401 and the support arm 3, and the lock bar 402 can reinforce the leg bar 401. The locking rod 402 has one end fixedly connected to the leg rod 401 and the other end connected to the side of the support arm 3 by a pin 403.

In the present invention, as shown in fig. 5, a support leg 404 is provided at the bottom of the support leg rod 401, and the support leg 404 is connected to the bottom of the support leg rod 401 by a second spring 405. Through the use of stabilizer blade 404 and second spring 405, can make flight seat 1 obtain the buffering when descending, simultaneously, also can make unmanned aerial vehicle descend in the topography of difference.

The utility model discloses in, the lateral part of flight seat 1 still is equipped with supporting seat 5, and wherein, supporting seat 5 is sliding connection at the lateral part of flight seat 1. Specifically, as shown in fig. 1 and 2, the support base 5 includes a base 501 and support rods 502 fixedly installed at two ends of the base 501, the support rods 502 are slidably connected with the side portions of the flying seat 1, and the base 501 is used for supporting on the ground when the aircraft is stored. The middle parts of the two side parts of the flying seat 1 are respectively and fixedly provided with a sleeve 503 for slidably connecting the support rod 502, and the support rod 502 is slidably connected in the sleeve 503. When the airplane is in use, the base 501 is slid in the direction of the sleeve 503 to retract the base 501, and when the airplane is stored, the base 501 is moved in the direction away from the sleeve 503 to pull out the base 501, thereby supporting the flying seat 1. In addition, in order to maintain the gravity balance of the airplane during use, a counterweight housing 504 conforming to the specifications of the base 501 is fixedly connected to one end of the flying seat 1 away from the base 501.

In order to fix the base 501 when the airplane is in use, a spring fastener may be provided between the base 501 and the flying seat 1. The male buckle of the spring buckle is fixed on the side of the end of the base 501 facing the flying seat 1, and the female buckle of the spring buckle is fixed on the end of the flying seat 1 far from the counterweight seat 504.

The utility model discloses in, the length of bracing piece 502 equals with the lateral part length of flight seat 1 to prevent that bracing piece 502 overlength from leading to when the aircraft uses, the one end that base 501 was kept away from to bracing piece 502 surpasss flight seat 1 and leads to the focus skew, is unfavorable for the flight of aircraft.

In the present invention, as shown in fig. 3, the shaft of the supporting rod 502 is further provided with a blocking member 6 engaged with the opening of the sleeve 503, so that after the supporting rod 502 is drawn out from the sleeve 503, the supporting rod 502 is prevented from sliding into the sleeve 503 by the blocking member 6.

Specifically, as shown in fig. 4, the blocking member 6 includes mounting grooves 601 symmetrically disposed on the shaft of the support rod 502, a blocking rod 602 is hinged in the mounting groove 601, a triangular block 603 is fixedly connected to the outer shaft of the blocking rod 602, and the top of the triangular block 603 is a plane. A first spring 604 is connected between a side of the blocking bar 602 away from the triangular block 603 and a bottom of the mounting groove 601, and a notch length of the mounting groove 601 is smaller than that of the blocking bar 602, so that the blocking bar 602 is restricted inside the mounting groove 601.

When the blocking piece 6 is pulled out from the sleeve 503, the triangular block 603 is ejected from the notch of the mounting groove 601 under the action of the first spring 604, the blocking rod 602 is blocked by the notch of the mounting groove 601, so that the triangular block 603 stops, at the moment, the top of the triangular block 603 exceeds the boundary of the sleeve 503, so that the sleeve 503 blocks the triangular block 603, and at the moment, the base 501 is placed on the ground, so that the flying seat 1 can be accommodated. When the airplane needs to be used, the triangular block 603 is pressed, the triangular block 603 retracts into the mounting groove 601, meanwhile, the supporting rod 502 slides into the sleeve 503, the mounting groove 601 extends into the sleeve 503, then the supporting rod 502 is moved continuously, the male buckle on the base 501 is matched with the female buckle on the flying seat 1, and then the base 501 is retracted.

The utility model discloses in, foretell flight seat 1, landing leg subassembly 4, support arm 3 and supporting seat 5 are carbon fiber material and make, are favorable to reducing the whole weight of aircraft.

The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be understood by those skilled in the art that the scope of the present invention is not limited to the specific combination of the above-mentioned features, but also covers other embodiments formed by any combination of the above-mentioned features or their equivalents without departing from the spirit of the present invention. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.

Besides the technical features described in the specification, other technical features are known to those skilled in the art, and further description of the other technical features is omitted here in order to highlight the innovative features of the present invention.

Claims

1. The carbon fiber rotor wing aircraft frame is characterized by comprising a flight seat (1) and a plurality of rotor wing assemblies (2) arranged around the flight seat (1), wherein the rotor wing assemblies (2) are fixedly arranged on the outer side of the flight seat (1) through support arms (3), the support arms (3) are further provided with support leg assemblies (4), and the support leg assemblies (4) are movably connected to the side parts of the support arms (3);

the leg assembly (4) comprises a leg rod (401), the leg rod (401) is connected to the side of the support arm (3), a locking rod (402) is connected between the leg rod (401) and the support arm (3), one end of the locking rod (402) is connected to the leg rod (401), and the other end of the locking rod is connected to the side of the support arm (3) through a pin (403);

the lateral part of flight seat (1) still is equipped with supporting seat (5), supporting seat (5) sliding connection be in the lateral part of flight seat (1), supporting seat (5) include base (501) and fixed mounting at bracing piece (502) at base (501) both ends, bracing piece (502) with the lateral part sliding connection of flight seat (1).

2. A carbon fiber rotary-wing aircraft frame according to claim 1, characterized in that the middle of the two side portions of the flying seat (1) is fixedly provided with a sleeve (503) for slidably connecting the supporting rod (502), and the supporting rod (502) is slidably connected in the sleeve (503);

the length of the support rod (502) is equal to the length of the side part of the flying seat (1).

3. A carbon fibre rotorcraft airframe as claimed in claim 2, wherein the shaft of the strut (502) is provided with a stop (6) that engages the mouth of the sleeve (503) such that the strut (502) is prevented from sliding inwardly of the sleeve (503) by the stop (6) after the strut (502) has been withdrawn from the sleeve (503).

4. A carbon fiber rotorcraft frame as claimed in claim 3, wherein the blocking member (6) comprises symmetrically distributed mounting slots (601) formed in the shaft of the support rod (502), a blocking rod (602) is hinged in the mounting slots (601), a triangular block (603) is fixedly connected to the outer shaft of the blocking rod (602), and the top of the triangular block (603) is a plane;

a first spring (604) is connected between one side, away from the triangular block (603), of the blocking rod (602) and the bottom of the installation groove (601), the notch length of the installation groove (601) is smaller than that of the blocking rod (602), and therefore the blocking rod (602) is limited inside the installation groove (601).

5. A carbon fibre rotorcraft frame as claimed in claim 4, in which the flying seat (1) is fixedly connected, at the end remote from the base (501), to a counterweight seat (504) of the same size as the base (501).

6. A carbon fiber rotorcraft frame as claimed in claim 5, wherein a snap fastener is provided between the base (501) and the flight seat (1), a male fastener of the snap fastener is fixed to the side of the base (501) facing the end of the flight seat (1), and a female fastener of the snap fastener is fixed to the end of the flight seat (1) far from the counterweight seat (504).

7. A carbon fibre rotorcraft frame as claimed in claim 6, in which the foot (404) is provided at the bottom of the leg bar (401), the foot (404) being connected to the bottom of the leg bar (401) by a second spring (405).