FUSELAGE STRUCTURE OF AN UNMANNED HELICOPTER

STRUCTURE DE FUSELAGE D'UN HELICOPTERE SANS PILOTE

English Abstract

A fuselage structure of an unmanned helicopter is provided. The fuselage
structure
relates to the field of unmanned helicopter design. The fuselage structure
comprises two side
frames and a rotor wing frame mounted between the two side frames. The
fuselage structure
is shaped like a trapezoid structure and is strengthened by a stiffening beam.
The fuselage
structure may be characterized by high strength, simple structure, few
components, and quick
disassembly for maintenance. I-section steel may be used for manufacturing
beam structures.
In addition, both the size and the weight of the fuselage structure are
reduced, thus reducing
the weight of the unmanned helicopter and improving the loiter time and
running efficiency of
the unmanned helicopter. Parts of the unmanned helicopter may be mounted on an
extension
beam.

French Abstract

Une structure de fuselage dun hélicoptère sans pilote est présentée. La structure de fuselage est liée au domaine de la conception dhélicoptère sans pilote. La structure de fuselage comprend deux cadres latéraux et un cadre de pale de rotor installé entre les deux cadres latéraux. La structure de fuselage est de forme semblable à une structure trapézoïdale et est renforcée par une barre de raidissement. La structure de fuselage peut être caractérisée par une structure simple très solide, le petit nombre de composantes et le démontage rapide en vue de lentretien. De lacier à section en I peut être utilisé pour la fabrication des structures de montant. De plus, la taille et le poids de la structure du fuselage sont réduits, diminuant ainsi le poids de lhélicoptère sans pilote et améliorant le temps du vol d'attente et lefficacité fonctionnelle de lhélicoptère sans pilote. Les pièces de lhélicoptère sans pilote peuvent être installées sur un montant dextension.

Claims

CLAIMS:
1. A fuselage structure of an unmanned helicopter, comprising two side
frames
and a rotor wing frame mounted between the two side frames, wherein
the two side frames each comprise two cross beams in parallel, two connecting
beams, and a stiffening beam;
the two connecting beams are fixedly connected between the two cross beams;
the two connecting beams are arranged slantwise so that a trapezoid structure
is
formed between the two cross beams;
the stiffening beam is fixedly connected between the two connecting beams;
the two cross beams and the two connecting beams have an I-type cross
section;
the stiffening beam is in parallel with the cross beams;
the stiffening beam is provided with a plurality of hollowed-out grooves; and
one or more engine fixed mounts are arranged between the two side frames.
2. The fuselage structure of an unmanned helicopter according to claim 1,
wherein
the side frames further comprise an extension beam;
the extension beam is arranged parallel to and fixed to one of the two cross
beams; and
the one or more engine fixed mounts are fixed to the extension beam, or the
one or more engine fixed mounts are fixed to at least one of the two cross
beams.
4

3. The fuselage structure of an unmanned helicopter according to claim 1,
wherein
the side frames further comprise two extension beams;
the two extension beams are arranged parallel to and fixed to each of the two
cross beams; and
the one or more engine fixed mounts are fixed to at least one of the two
extension beams, or the one or more engine fixed mounts are fixed to at least
one of the two
cross beams.
4. The fuselage structure of an unmanned helicopter according to any one of
claims 1-3, wherein
a frame plate is mounted between each stiffening beam of the two side frames;
and
plugs are placed in the plurality of hollowed-out grooves to fix the frame
plate
between each stiffening beam of the two side frames.

Description

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FUSELAGE STRUCTURE OF AN UNMANNED HELICOPTER
TECHNICAL FIELD
The utility model relates to the field of unmanned helicopter, and more
particularly, to
a fuselage structure of an unmanned helicopter.
BACKGROUND OF THE INVENTION
In the prior art, the fuselage structure of an unmanned helicopter mainly is
obtained by
improving the fuselage structure of a model airplane, following the method for
designing a
side plate under stress. This fuselage structure is narrow in space and low in
strength, unable
to provide good protection of a carrying device.
A different fuselage structure is provided in a prior patent the Bridge-type
Structure of
a Turboshaft Unmanned Helicopter (Patent Number: CN 201110434831.6), which has
many
defects although solving the above-mentioned problems. This fuselage structure
is complex
in design, multiple in parts, difficult for manufacturing, high in cost,
cumbersome in assembly
and insufficient in strength. When it is necessary to repair internal parts of
the unmanned
helicopter, this structure design causes great difficulty in disassembly and
assembly and thus
being inconvenient for repairing the unmanned helicopter.
SUMMARY OF THE INVENTION
In allusion to problems in the fuselage structure of the existing unmanned
helicopter
such as complex design, multiple parts, high cost, insufficient strength,
cumbersome
assembly, inconvenient maintenance and so on, the utility model designs a
fuselage structure
of an unmanned helicopter.
The fuselage structure of an unmanned helicopter provided in the utility model
includes two side frames and a rotor wing frame mounted between the two side
frames, and
the side frames have an I-type cross section.
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The side frames include two cross beams in parallel, two connecting beams are
fixedly
connected between the two cross beams, the two connecting beams are arranged
slantwise so
that a trapezoid structure is formed between both, a stiffening beam is
fixedly connected
between the two connecting beams, and both the cross beams and the connecting
beams are
made from I-type cross section aviation aluminum or steel.
A plurality of engine fixed mounts is arranged between the two side frames.
Preferably, an extension beam is arranged in parallel on the cross beams, and
the
engine fixed mounts are fixed to the extension beam.
Preferably, the stiffening beam is in parallel with the cross beams and is
provided with
a plurality of hollowed-out grooves.
Preferably, a frame plate is mounted between the stiffening beams of the two
side
frames, plugs arranged at both sides of the frame plate are plugged into
corresponding
hollowed-out grooves.
The beneficial effects of the utility model are as below: the fuselage
structure takes
side frames as a main body structure, the inside of which is shaped like a
trapezoid structure
and is strengthened by a stiffening beam, characterized by high strength,
simple structure and
few components, disassembled quickly for maintenance. I-type cross section
steel is used for
manufacturing beam structures, which further increases the lateral rigidity
and resistance to
bending of the fuselage structure. In addition, both the size and the weight
of the fuselage
structure are reduced, thus reducing the weight of the unmanned helicopter and
improving the
loiter time and running efficiency of the unmanned helicopter. Parts of the
unmanned
helicopter may be mounted on an extension beam arranged in parallel when the
cross beams
are not long enough, thus improving the flexibility in assembly of the
fuselage structure. In
addition, the extension beam may further improve the strength of the cross
beams. Hollowed-
out grooves on the stiffening beam may not only facilitate installation of the
frame plate but
also further reduce the weight of the fuselage structure.
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According to one aspect of the present invention, there is provided a fuselage
structure
of an unmanned helicopter, comprising two side frames and a rotor wing frame
mounted
between the two side frames, wherein the two side frames each comprise two
cross beams in
parallel, two connecting beams, and a stiffening beam; the two connecting
beams are fixedly
connected between the two cross beams; the two connecting beams are arranged
slantwise so
that a trapezoid structure is formed between the two cross beams; the
stiffening beam is
fixedly connected between the two connecting beams; the two cross beams and
the two
connecting beams have an I-type cross section; the stiffening beam is in
parallel with the cross
beams; the stiffening beam is provided with a plurality of hollowed-out
grooves; and one or
more engine fixed mounts are arranged between the two side frames.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a structure diagram of the fuselage structure.
Fig. 2 is a structure diagram of a side frame.
DESCRIPTION OF THE EMBODIMENTS
As shown in Fig. 1, the fuselage structure of an unmanned helicopter provided
in the
utility model includes two side frames 1 and a rotor wing frame 2 mounted
between the two
side frames 1, the rotor wing of the unmanned helicopter is mounted on the
rotor wing frame,
and the side frames 1 are I-type cross section beams.
As shown in Fig. 2, the side frames include two cross beams 3 in parallel, two
connecting beams 4 are fixedly connected between the two cross beams 3, the
two connecting
beams 4 are arranged slantwise so that a structure the inside of which is
shaped like a
trapezoid comprises the two connecting beams 4 and the two cross beams 3,
besides, a
stiffening beam 5 is fixedly connected between the two connecting beams 4.
Both the cross beams 3 and the connecting beams 4 are made from I-type cross
section
steel, a plurality of engine fixed mounts 6 are mounted between the two side
frames 1, and the
engine of the unmanned helicopter is mounted on the engine fixed mounts 6.
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According to the needs of the structure, an extension beam 7 may be arranged
in
parallel on the cross beams 3 so that the engine fixed mounts 6 or other
devices in the
unmanned helicopter may be fixed to the extension beam 7. The extension beam 7
may be
mounted on either one of the cross beams 3, or both cross beams 3 are
respectively provided
with an extension beam 7.
The stiffening beam 5 is in parallel with the cross beams 3 so that two
trapezoid
structures are formed between the two connecting beams, which further improves
the strength
of the side frames and the fuselage structure.
A plurality of hollowed-out grooves 8 are arranged on the stiffening beam 5, a
frame
plate 9 is mounted between the two side frames 1 and the stiffening beam 5,
and plugs
arranged at both sides of the frame plate 9 are plugged into corresponding
hollowed-out
grooves 8. The frame plate 9 may be configured to support a master gear
mounted on the
principal axis of the rotor wing, and also configured to mount other parts in
the unmanned
helicopter.
In order to assemble the unmanned helicopter with this fuselage structure,
only a
plurality of brackets needs mounting between the two side frames 1 and other
parts in the
unmanned helicopter are arranged on these brackets.
3a

Representative Drawing