CN108791798A - Craft variant nose cone based on 6-SPS space parallel mechanisms - Google Patents
Craft variant nose cone based on 6-SPS space parallel mechanisms Download PDFInfo
- Publication number
- CN108791798A CN108791798A CN201810509284.5A CN201810509284A CN108791798A CN 108791798 A CN108791798 A CN 108791798A CN 201810509284 A CN201810509284 A CN 201810509284A CN 108791798 A CN108791798 A CN 108791798A
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- China
- Prior art keywords
- body segment
- taper body
- craft
- nose cone
- taper
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Moulding By Coating Moulds (AREA)
- Tires In General (AREA)
Abstract
Craft variant nose cone based on 6-SPS space parallel mechanisms, including the multiple taper body segments set gradually, taper body segment overall alignment is pyramidal structure, the outer diameter of previous taper body segment tail portion is equal with the latter internal diameter of taper body segment stem, the setting of taper body segment inner wall drives the parallel institution that two adjacent pitch cone body sections are realized elongation and are bent, parallel institution is arranged at intervals on taper body segment inner wall, it is not provided with parallel institution in first pitch cone body section and minor details taper body segment, first pitch cone body section end set has conehead, it can realize the deformation of aircraft nose cone, and with compact-sized, deformation is flexible, precision is high, rigidity is big, bearing capacity is strong, the advantages that dynamic response is stablized.
Description
Technical field
The present invention relates to aerospace flight vehicle technical fields, more particularly to the flight based on 6-SPS space parallel mechanisms
Device variant nose cone.
Background technology
Aircraft can obtain the optimal aerodynamic configuration under different conditions in flight course by changing own form.
And the research of the variant of aircraft is concentrated mainly on variable rotor aircraft at present, for the Study on Deformation phase of aircraft nose cone
To less.The research of craft variant nose cone is of great significance for optimizing the aerodynamic characteristic of aircraft.
Invention content
In order to overcome the above-mentioned deficiencies of the prior art, the purpose of the present invention is to provide based on 6-SPS space parallel mechanisms
Craft variant nose cone, can realize the deformation of aircraft nose cone, and with compact-sized, deformation flexibly, precision is high, rigidity
Greatly, the advantages that bearing capacity is strong, dynamic response is stablized.
To achieve the goals above, the technical solution adopted by the present invention is：
Craft variant nose cone based on 6-SPS space parallel mechanisms, including multiple taper body segments 100 for setting gradually,
100 overall alignment of taper body segment is pyramidal structure, the outer diameter of previous 100 tail portion of taper body segment and latter 100 stem of taper body segment
Internal diameter it is equal, described 100 inner wall of the taper body segment setting drives two adjacent pitch cone body sections 100 to realize elongation and bending
Parallel institution 200, parallel institution 200 are arranged at intervals on 100 inner wall of taper body segment, the first pitch cone body section 100 and end
Parallel institution 200 is not provided in pitch cone body section 100, first 100 end set of pitch cone body section has conehead 400.
The parallel institution 200 includes servoBcylinder 210 and flexural pivot 220, and one end is fixed on previous pitch cone by flexural pivot 220
On the triangular pedestals 120 of 100 tail portion of body section, the other end is fixed on 100 stem of later section taper body segment by flexural pivot 220
On triangular pedestals 120, it is connected by servoBcylinder 210 between flexural pivot 220, triangular pedestals 120 are arranged on taper body segment 100
Mounting platform 110 on.
The servoBcylinder 210 that the parallel institution 200 is connected by six both ends with flexural pivot 220 forms, each servoBcylinder 210
Both ends are threadedly coupled with flexural pivot 220, and flexural pivot 220 is fixed on the triangular pedestals 120 of mounting platform 110.
At horizontal position, the axis of each taper body segment 100 overlaps the taper body segment 100.
The 200 outboard cone section 100 of parallel institution is flexible covering 300.
The taper body segment 100 is 6 and diameter is sequentially reduced, and the diameter of 6 100 tail portions of taper body segment is followed successively by
1200 millimeters, 1168 millimeters, 1004 millimeters, 850 millimeters, 546 millimeters, 372 millimeters, and the wall thickness of taper body segment 100 is 20 millis
Rice.
Beneficial effects of the present invention：
The present invention have compact-sized, deformation flexibly, that precision is high, rigidity is big, bearing capacity is strong, dynamic response is stablized etc. is excellent
Point.
Six servoBcylinders 210 in every group of 6-SPS space parallel mechanism 200 can keep determining elongation, carry energy
Power is strong and precision is higher, it is ensured that the deformed stability of deformation nose cone of aircraft.
Description of the drawings
Fig. 1 is the structural schematic diagram of craft variant nose cone.
Fig. 2 is the original state of craft variant nose cone.
Fig. 3 is elongation and the flexuosity of craft variant nose cone.
Fig. 4 is the structural schematic diagram of the 6-SPS space parallel mechanisms of craft variant nose cone.
Fig. 5 is the servoBcylinder scheme of installation of craft variant nose cone.
Fig. 6 is the triangular pedestals and flexural pivot schematic diagram of craft variant nose cone.
Specific implementation mode
Invention is further described in detail below in conjunction with the accompanying drawings.
As shown in Figure 1, the craft variant nose cone 1 according to the ... of the embodiment of the present invention based on 6-SPS space parallel mechanisms wraps
Include 100, two groups of multiple taper body segments, 200, two groups of 6-SPS space parallel mechanisms flexible covering 300 and a conehead 400.
(front-rear direction is as shown in the arrow A in Fig. 1) is arranged in multiple taper body segments 100 along the longitudinal direction, and described second
100 tail portion of pitch cone body section, the stem of the 4th pitch cone body section 100 and tail portion, the 6th pitch cone body section 100
Stem be provided with the mounting platforms 110 of installation 6-SPS space parallel mechanisms 200.
6-SPS space parallel mechanisms 200 drive two adjacent pitch cone body sections 100 to realize flexible and flexural deformation.First
When beginning state, the axis of two pitch cone body sections 100 overlaps, and servoBcylinder 210 is in former length, and flexible covering 300 does not deform；
During only realizing dilatation, the axis of two pitch cone body sections 100 overlaps, and flexible covering 300 is deformed upon to adapt to
Deformed nose cone configuration；During realizing flexible and flexural deformation at the same time, the axis of two pitch cone body sections 100 is inclined to
Certain angle, flexible covering 300 are deformed upon with the nose cone configuration after adaptive deformation.
Conehead 400 is located at the forefront of multiple taper body segments 100.
Below with reference to the accompanying drawings it describes to be become according to the aircraft based on 6-SPS space parallel mechanisms of the specific embodiment of the invention
Body nose cone 1.
As shown in Figure 1, multiple taper body segments 100 are arranged along the longitudinal direction in the initial state, taper body segment 100 is 6
And diameter is sequentially reduced.Specifically, the tail diameter of 6 taper body segments 100 be followed successively by 1200 millimeters, 1168 millimeters, 1004
Millimeter, 850 millimeters, 546 millimeters, 372 millimeters, and the wall thickness of taper body segment 100 be 20 millimeters.
Third section and the 5th pitch cone body section 100 are made of flexible covering 300 and 6-SPS space parallel mechanisms 200.Third
6-SPS space parallel mechanisms 200 in section are mounted on the installation of the second pitch cone body section tail portion and the 4th pitch cone body section stem
On platform 110, the 6-SPS space parallel mechanisms 200 in Section five are mounted on the 4th pitch cone body section tail portion and the 6th pitch cone shape
On the mounting platform 110 of body segment stem.
Conehead 400 is mounted on 100 front end of first segment taper body segment.
As shown in Figures 2 and 3, Fig. 2 is the original state of craft variant nose cone, and Fig. 3 is stretching for craft variant nose cone
Long and flexuosity, when nose cone is deformed, multiple servoBcylinders 210 carry out the elongation of different amplitudes, drive previous bullet
Movement of the section 100 relative to latter taper body segment.Meanwhile the deflection of every group of six servoBcylinders 210 uniquely determines aircraft
The telescoping collapse deformation degree of variant nose cone 1, by maintaining deflection constant, it is ensured that the deformation nose cone 1 of aircraft deforms
Stability afterwards.
As shown in Figure 4 and Figure 5,6-SPS space parallel mechanisms 200 include multiple servoBcylinders 210, flexural pivot 220.ServoBcylinder
210 are connected with flexural pivot 220 by screw-thread fit, and flexural pivot 220 is connect by triangular pedestals 120 with mounting platform 110.According to not
Same duty requirements, servoBcylinder 210 can be substituted by other driving devices.
As shown in fig. 6, it is since triangular pedestals 120 change servoBcylinder to connect flexural pivot 220 using triangular pedestals 120
210 with mounting platform 110 on mounting surface angle, make its in deformation process always be in flexural pivot 220 allow move model
In enclosing.
The operation principle of the present invention：
When craft variant nose cone based on 6-SPS space parallel mechanisms carries out dilatation, 6-SPS space parallel mechanisms
210 constant amplitude of servoBcylinder in 200 is flexible, to drive adjacent two tapers body segment 100 to complete dilatation；Based on the spaces 6-SPS
When the craft variant nose cone of parallel institution is carried out at the same time elongation and flexural deformation, the deformation quantity of servoBcylinder 210 is different, tool
For body, top (upper and lower directions is as shown in the arrow B in Fig. 2) two 210 elongations of servoBcylinder are larger, two, middle part servoBcylinder
210 elongations take second place, and 210 elongation of servoBcylinder of lower part two is minimum, to realize the elongation and bending of craft variant nose cone
Movement.ServoBcylinder 210 keeps deformation quantity constant, you can craft variant nose cone is maintained to correspond to the stability of configuration.
Claims (6)
1. the craft variant nose cone based on 6-SPS space parallel mechanisms, which is characterized in that including the multiple tapers set gradually
Body segment (100), taper body segment (100) overall alignment are pyramidal structure, outer diameter and the latter cone of previous taper body segment (100) tail portion
The internal diameter of body section (100) stem is equal, and the setting of described taper body segment (100) inner wall drives two adjacent pitch cone body sections
(100) realize that the parallel institution (200) of elongation and bending, parallel institution (200) are arranged at intervals on taper body segment (100) inner wall
On, it is not provided with parallel institution (200), first pitch cone body in the first pitch cone body section (100) and minor details taper body segment (100)
Section (100) end set has conehead (400).
2. the craft variant nose cone according to claim 1 based on 6-SPS space parallel mechanisms, which is characterized in that institute
The parallel institution (200) stated includes servoBcylinder (210) and flexural pivot (220), and one end is fixed on previous pitch cone shape by flexural pivot (220)
On the triangular pedestals (120) of body segment (100) tail portion, the other end is fixed on later section taper body segment (100) by flexural pivot (220)
On the triangular pedestals (120) of stem, it is connected by servoBcylinder (210) between flexural pivot (220), triangular pedestals (120) setting
On mounting platform (110) on taper body segment (100).
3. the craft variant nose cone according to claim 1 or 2 based on 6-SPS space parallel mechanisms, which is characterized in that
The servoBcylinder (210) that the parallel institution (200) is connected by six both ends with flexural pivot (220) forms, each servoBcylinder (210)
Both ends are threadedly coupled with flexural pivot (220), and flexural pivot (220) is fixed on the triangular pedestals (120) of mounting platform (110).
4. the craft variant nose cone according to claim 1 based on 6-SPS space parallel mechanisms, which is characterized in that institute
At horizontal position, the axis of each taper body segment (100) overlaps the taper body segment (100) stated.
5. the craft variant nose cone according to claim 1 based on 6-SPS space parallel mechanisms, which is characterized in that institute
Parallel institution (200) the outboard cone section (100) stated is flexible covering (300).
6. the craft variant nose cone according to claim 1 based on 6-SPS space parallel mechanisms, which is characterized in that institute
The taper body segment (100) stated is 6 and diameter is sequentially reduced, and the diameter of 6 taper body segment (100) tail portions is followed successively by 1200 millis
Rice, 1168 millimeters, 1004 millimeters, 850 millimeters, 546 millimeters, 372 millimeters, and the wall thickness of taper body segment 100 be 20 millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509284.5A CN108791798B (en) | 2018-05-24 | 2018-05-24 | Aircraft variant nose cone based on 6-SPS space parallel mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509284.5A CN108791798B (en) | 2018-05-24 | 2018-05-24 | Aircraft variant nose cone based on 6-SPS space parallel mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108791798A true CN108791798A (en) | 2018-11-13 |
| CN108791798B CN108791798B (en) | 2020-10-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810509284.5A Active CN108791798B (en) | 2018-05-24 | 2018-05-24 | Aircraft variant nose cone based on 6-SPS space parallel mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113232828A (en) * | 2021-05-31 | 2021-08-10 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4692057A (en) * | 1985-05-10 | 1987-09-08 | Stabilus Gmbh | Taper connection on a chair or table column of adjustable height |
| CN103267210A (en) * | 2013-05-16 | 2013-08-28 | 燕山大学 | Six-freedom-degree parallel pointing platform |
| CN103383821A (en) * | 2013-07-05 | 2013-11-06 | 燕山大学 | Six-freedom-degree heavy load static balance parallel motion simulation table mechanism with balancing mechanism |
| CN105346702A (en) * | 2015-11-16 | 2016-02-24 | 清华大学 | Deformation nose cone of aircraft |
-
2018
- 2018-05-24 CN CN201810509284.5A patent/CN108791798B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4692057A (en) * | 1985-05-10 | 1987-09-08 | Stabilus Gmbh | Taper connection on a chair or table column of adjustable height |
| CN103267210A (en) * | 2013-05-16 | 2013-08-28 | 燕山大学 | Six-freedom-degree parallel pointing platform |
| CN103383821A (en) * | 2013-07-05 | 2013-11-06 | 燕山大学 | Six-freedom-degree heavy load static balance parallel motion simulation table mechanism with balancing mechanism |
| CN105346702A (en) * | 2015-11-16 | 2016-02-24 | 清华大学 | Deformation nose cone of aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113232828A (en) * | 2021-05-31 | 2021-08-10 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
| CN113232828B (en) * | 2021-05-31 | 2022-04-22 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108791798B (en) | 2020-10-09 |
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