CN207658030U - A kind of unmanned helicopter fuselage main frame structure - Google Patents
A kind of unmanned helicopter fuselage main frame structure Download PDFInfo
- Publication number
- CN207658030U CN207658030U CN201721874187.3U CN201721874187U CN207658030U CN 207658030 U CN207658030 U CN 207658030U CN 201721874187 U CN201721874187 U CN 201721874187U CN 207658030 U CN207658030 U CN 207658030U
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- CN
- China
- Prior art keywords
- tubule
- support bar
- main frame
- frame structure
- unmanned helicopter
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model provides a kind of unmanned helicopter fuselage main frame structure, including rectangle fixed frame, rectangle fixed frame includes cross bar and longitudinal tubule (L tubule), the left end of cross bar is the first longitudinal tubule (L tubule), right end is the second longitudinal tubule (L tubule), the both ends of first longitudinal tubule (L tubule) are respectively arranged with the first left support bar upward, and the second left support bar is respectively arranged with to upper right side；The both ends of second longitudinal tubule (L tubule) are respectively arranged with the first right support bar to upper left side, and the second right support bar is respectively arranged with to upper right side；First left support bar upper end is respectively equipped with the first shock-absorbing ball, and the first left tie-beam is provided between the first left support bar；The upper end of second left support bar and the first right support bar is connect with fixed plate, and the second shock-absorbing ball is both provided in fixed plate；The upper end of second right support bar is respectively fixed with the side plate of vertical direction setting, and the upper end of two side plates is connected by the first right connecting rod with corresponding fixed plate respectively；U-shaped pipe card is provided on cross bar.The utility model enhances the intensity of the stability and tension antivibration of frame.
Description
Technical field
The utility model belongs to unmanned helicopter technical field, more particularly, to a kind of unmanned helicopter fuselage main frame knot
Structure.
Background technology
Fuselage main frame is used for supporting and fixing helicopter component, system, they is connected into an entirety, and for filling
Various instrument and equipments are carried, helicopter is made to meet set technology requirement；Fuselage main frame is the important component of helicopter.
Main frame shape has Helicopter flight performance, maneuverability and stability important influence.In use,
Main frame will bear the load and vibration that various equipment transmit, and needs to carry out damping, helicopter is avoided to generate resonance, ensure flying
Stability during row.
Invention content
In view of this, the utility model is directed to a kind of unmanned helicopter fuselage main frame structure, enhance the steady of frame
Qualitative and tension antivibration intensity.
In order to achieve the above objectives, the technical solution of the utility model is realized in：
A kind of unmanned helicopter fuselage main frame structure, including horizontally disposed rectangle fixed frame, rectangle fixed frame is by phase
Cross bar and longitudinal tubule (L tubule) head and the tail to setting are formed by connecting, and the left end of cross bar is the first longitudinal tubule (L tubule), and right end is the second longitudinal tubule (L tubule), the first longitudinal tubule (L tubule)
Both ends are respectively arranged with the first left support bar upward, and the second left support bar is respectively arranged with to upper right side；The two of second longitudinal tubule (L tubule)
It holds to upper left side and is respectively arranged with the first right support bar, the second right support bar is respectively arranged with to upper right side；
First left support bar upper end is respectively equipped with the first shock-absorbing ball, and the first left connection is provided between the first left support bar
Beam；
The upper end of second left support bar and the first right support bar is each attached in the fixed plate above cross bar, fixed plate
On be both provided with the second shock-absorbing ball；
The upper end of second right support bar is respectively fixed with the side plate of vertical direction setting, and fixation is provided between two side plates
The upper end of beam, two side plates is connected by the first right connecting rod with corresponding fixed plate respectively；
U-shaped pipe card is provided on cross bar.
Further, described further includes two left connecting rods of horizontally arranged first, the right end of the first left connecting rod
It is fixedly connected with the first left tie-beam, the first bracing diagonal is additionally provided between the first longitudinal tubule (L tubule) and the first left connecting rod, first is left
It is additionally provided with the several second left tie-beams between connecting rod, U-shaped pipe card is provided in the first left connecting rod.It can be with more convenient steady
Solid fixed equipment, with rectangle fixed frame coordinate realize main frame structure and body secured connection.
Further, the second left support bar and the angle of horizontal direction are 30 °, the first right support bar and horizontal direction
Angle be 60 °.
Further, the fixed beam is parallel with cross bar, and fixed beam has two groups, and every group includes 2, and one group of setting is at two
Upper end between side plate, another group of lower end being arranged between two side plates.The setting of fixed beam be in order to fix two side plates,
Prevent helicopter using when two side plates swing, while increasing the service life of side plate.Side plate is primarily used to connect
The tail pipe for connecing fixed helicopter keeps the connection of tail pipe and main frame more firm, when helicopter flight, effect of the tail pipe in side plate
It will not swing under power.
Further, the upper end of described two first left support bars tilts inwardly in the vertical direction, angle of inclination
It is 15~20 °.
Further, the diagonally adjacent of the rectangle fixed frame is provided with the second bracing diagonal.
Further, described further includes third bracing diagonal, and third bracing diagonal is set to by the second longitudinal tubule (L tubule), fixed beam and two
On the diagonal line for the framework that a second right support bar is formed.
Further, described further includes the 4th bracing diagonal, and the 4th bracing diagonal is set to by the first right support bar, second right side
On the diagonal line of the framework of supporting rod, side plate and the first right connecting rod composition.
Further, the longitudinal tubule (L tubule) is internally provided with reinforcing plate, and there are three reinforcing plates, centered on the center of circle of longitudinal tubule (L tubule) at
Diverging setting.
Further, it is provided with rubber pad in the U-shaped pipe card.
Compared with the existing technology, unmanned helicopter fuselage main frame structure described in the utility model has the advantage that：
Unmanned helicopter fuselage main frame structure described in the utility model by force analysis and integrally-built is matched
It closes so that fuselage main frame enhances support strength, stability and tension vibration strength, is ensureing to meet what support required
Meanwhile reducing many unnecessary sizes, keep entire fuselage compacter, and also achieve shock-absorbing function, ensure that machine
Body various functions smoothly complete.
Description of the drawings
The attached drawing for constituting the part of the utility model is used to provide a further understanding of the present invention, this practicality is new
The illustrative embodiments and their description of type are not constituted improper limits to the present invention for explaining the utility model.
In attached drawing：
Fig. 1 is the dimensional structure diagram of the unmanned helicopter fuselage main frame structure described in the utility model embodiment；
Fig. 2 is the front view of the unmanned helicopter fuselage main frame structure described in the utility model embodiment；
Fig. 3 is the vertical view of the unmanned helicopter fuselage main frame structure described in the utility model embodiment.
Reference sign：
1- cross bars；The first longitudinal tubule (L tubule)s of 2-；The second longitudinal tubule (L tubule)s of 3-；4- the first left support bars；5- the second left support bars；The first right branch of 6-
Strut；7- the second right support bars；The first shock-absorbing balls of 8-；The first left tie-beams of 9-；10- fixed plates；The second shock-absorbing balls of 11-；The sides 12-
Plate；13- fixed beams；The first right connecting rods of 14-；The first left connecting rods of 15-；The first bracing diagonals of 16-；The second left tie-beams of 17-；
The second bracing diagonals of 18-；19- third bracing diagonals；The 4th bracing diagonals of 20-.
Specific implementation mode
It should be noted that in the absence of conflict, the feature in the embodiments of the present invention and embodiment can
To be combined with each other.
In the description of the present invention, it should be understood that term "center", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of describing the present invention and simplifying the description, rather than indicate
Or imply that signified device or element must have a particular orientation, with specific azimuth configuration and operation, therefore cannot understand
For limitations of the present invention.In addition, term " first ", " second " etc. are used for description purposes only, and should not be understood as indicating
Or it implies relative importance or implicitly indicates the quantity of indicated technical characteristic." first ", " second " etc. are defined as a result,
Feature can explicitly or implicitly include one or more this feature.It is in the description of the present invention, unless another
It is described, the meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, can also be electrical connection；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, on being understood by concrete condition
State the concrete meaning of term in the present invention.
The utility model will be described in detail below with reference to the accompanying drawings and embodiments.
As shown in Figs. 1-3, a kind of unmanned helicopter fuselage main frame structure, including horizontally disposed rectangle fixed frame, square
Shape fixed frame is formed by connecting by cross bar 1 and the longitudinal tubule (L tubule) head and the tail being oppositely arranged, and the left end of cross bar 1 is the first longitudinal tubule (L tubule) 2, right end second
The both ends of longitudinal tubule (L tubule) 3, the first longitudinal tubule (L tubule) 2 are respectively arranged with the first left support bar 4 upward, and the second left branch is respectively arranged with to upper right side
Strut 5；The both ends of second longitudinal tubule (L tubule) 3 are respectively arranged with the first right support bar 6 to upper left side, and second right side is respectively arranged with to upper right side
Supporting rod 7；
First left support bar, 4 upper end is respectively equipped with the first shock-absorbing ball 8, and the first left company is provided between the first left support bar 4
Connect beam 9；
The upper end of second left support bar 5 and the first right support bar 6 is each attached in the fixed plate 10 above cross bar 1,
The second shock-absorbing ball 11 is both provided in fixed plate 10；
The upper end of second right support bar 7 is respectively fixed with the side plate 12 of vertical direction setting, is arranged between two side plates 12
There are fixed beam 13, the upper end of two side plates 12 to be connected respectively with corresponding fixed plate 10 by the first right connecting rod 14；
It is provided with U-shaped pipe card on cross bar 1.
Above-mentioned further includes the left connecting rod 15 of two horizontally arranged first, the right end and first of the first left connecting rod 15
Left tie-beam 9 is fixedly connected, and the first bracing diagonal 16 is additionally provided between the first longitudinal tubule (L tubule) 2 and the first left connecting rod 15, and first is left
It is additionally provided with the several second left tie-beams 17 between connecting rod 15, U-shaped pipe card is provided in the first left connecting rod 15.
Above-mentioned second left support bar 5 and the angle of horizontal direction are 30 °, the angle of the first right support bar 6 and horizontal direction
It is 60 °.
Above-mentioned fixed beam 13 is parallel with cross bar 1, and fixed beam 13 has two groups, and every group includes 2, and one group of setting is in two side plates
Upper end between 12, another group of lower end being arranged between two side plates 12.
The upper end of the first left support of above-mentioned two bar 4 tilts inwardly in the vertical direction, angle of inclination be 15~
20°。
The diagonally adjacent of above-mentioned rectangle fixed frame is provided with the second bracing diagonal 18.
Above-mentioned further includes third bracing diagonal 19, and third bracing diagonal 19 is set to by the second longitudinal tubule (L tubule) 3, fixed beam 13 and two
On the diagonal line for the framework that second right support bar 7 is formed.
Above-mentioned further includes the 4th bracing diagonal 20, and the 4th bracing diagonal 20 is set to by the first right support bar 6, the second right support
On the diagonal line of the framework of bar 7, side plate 12 and the first right connecting rod 14 composition.
Above-mentioned longitudinal tubule (L tubule) is internally provided with reinforcing plate, and there are three reinforcing plates, is arranged at diverging centered on the center of circle of longitudinal tubule (L tubule).
Since when helicopter will be fallen, the stress load of longitudinal tubule (L tubule) is maximum, therefore such setting enhances the stress intensity of longitudinal tubule (L tubule).
It is provided with rubber pad in above-mentioned U-shaped pipe card.Main frame structure is fixed at organism bottom by U-shaped pipe card, inner
The setting of face rubber pad, plays the role of bumper and absorbing shock.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
Within the spirit and principle of utility model, any modification, equivalent replacement, improvement and so on should be included in the utility model
Protection domain within.
Claims (10)
1. a kind of unmanned helicopter fuselage main frame structure, it is characterised in that：Including horizontally disposed rectangle fixed frame, rectangle is solid
Determine frame to be formed by connecting by cross bar (1) and the longitudinal tubule (L tubule) head and the tail being oppositely arranged, the left end of cross bar (1) is the first longitudinal tubule (L tubule) (2), right end the
The both ends of two longitudinal tubule (L tubule)s (3), the first longitudinal tubule (L tubule) (2) are respectively arranged with the first left support bar (4) upward, are respectively arranged with to upper right side
Second left support bar (5)；The both ends of second longitudinal tubule (L tubule) (3) are respectively arranged with the first right support bar (6) to upper left side, to upper right side point
It is not provided with the second right support bar (7)；
First left support bar (4) upper end is respectively equipped with the first shock-absorbing ball (8), and first left side is provided between the first left support bar (4)
Tie-beam (9)；
The upper end of second left support bar (5) and the first right support bar (6) is each attached to the fixed plate (10) above cross bar (1)
On, the second shock-absorbing ball (11) is both provided in fixed plate (10)；
The upper end of second right support bar (7) is respectively fixed with the side plate (12) of vertical direction setting, is set between two side plates (12)
It is equipped with fixed beam (13), the upper end of two side plates (12) passes through the first right connecting rod (14) and corresponding fixed plate (10) respectively
Connection；
Cross bar is provided with U-shaped pipe card on (1).
2. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Further include two level sides
To the first left connecting rod (15) of setting, the right end of the first left connecting rod (15) is fixedly connected with the first left tie-beam (9), and first
It is additionally provided with the first bracing diagonal (16) between longitudinal tubule (L tubule) (2) and the first left connecting rod (15), is gone back between the first left connecting rod (15)
The several second left tie-beams (17) are provided with, U-shaped pipe card is provided on the first left connecting rod (15).
3. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Second left support bar (5)
Angle with horizontal direction is 30 °, and the first right support bar (6) and the angle of horizontal direction are 60 °.
4. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Fixed beam (13) and cross bar
(1) parallel, fixed beam (13) has two groups, and every group includes 2, upper end of one group of setting between two side plates (12), another group
Lower end between two side plates (12) is set.
5. unmanned helicopter fuselage main frame structure according to claim 3, it is characterised in that：Two the first left support bars
(4) upper end tilts inwardly in the vertical direction, and angle of inclination is 15~20 °.
6. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Rectangle fixed frame it is diagonal
The second bracing diagonal (18) is provided on line direction.
7. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Further include that third is reinforced tiltedly
Bar (19), third bracing diagonal (19) are set to and are formed by the second longitudinal tubule (L tubule) (3), fixed beam (13) and two the second right support bars (7)
Framework diagonal line on.
8. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Further include that the 4th reinforcement is oblique
Bar (20), the 4th bracing diagonal (20) are set to right by the first right support bar (6), the second right support bar (7), side plate (12) and first
On the diagonal line of the framework of connecting rod (14) composition.
9. unmanned helicopter fuselage main frame structure according to claim 1, it is characterised in that：Longitudinal tubule (L tubule) is internally provided with
Reinforcing plate, there are three reinforcing plates, is arranged at diverging centered on the center of circle of longitudinal tubule (L tubule).
10. unmanned helicopter fuselage main frame structure according to claim 2, it is characterised in that：It is provided in U-shaped pipe card
Rubber pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721874187.3U CN207658030U (en) | 2017-12-27 | 2017-12-27 | A kind of unmanned helicopter fuselage main frame structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721874187.3U CN207658030U (en) | 2017-12-27 | 2017-12-27 | A kind of unmanned helicopter fuselage main frame structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207658030U true CN207658030U (en) | 2018-07-27 |
Family
ID=62944140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721874187.3U Expired - Fee Related CN207658030U (en) | 2017-12-27 | 2017-12-27 | A kind of unmanned helicopter fuselage main frame structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207658030U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056537A (en) * | 2021-11-19 | 2022-02-18 | 中国直升机设计研究所 | Main bearing structure of middle fuselage of unmanned high-speed helicopter |
-
2017
- 2017-12-27 CN CN201721874187.3U patent/CN207658030U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056537A (en) * | 2021-11-19 | 2022-02-18 | 中国直升机设计研究所 | Main bearing structure of middle fuselage of unmanned high-speed helicopter |
| CN114056537B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Main bearing structure of fuselage in unmanned high-speed helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180727 Termination date: 20181227 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |