CN108372936A - A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely - Google Patents
A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely Download PDFInfo
- Publication number
- CN108372936A CN108372936A CN201810165900.XA CN201810165900A CN108372936A CN 108372936 A CN108372936 A CN 108372936A CN 201810165900 A CN201810165900 A CN 201810165900A CN 108372936 A CN108372936 A CN 108372936A
- Authority
- CN
- China
- Prior art keywords
- airvane
- covering
- skeleton
- rocket
- efficient
- Prior art date
- 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.)
- Withdrawn
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 11
- 239000006260 foam Substances 0.000 claims abstract description 34
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 14
- 239000004917 carbon fiber Substances 0.000 claims abstract description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 14
- 239000002131 composite material Substances 0.000 claims abstract description 12
- 239000011347 resin Substances 0.000 claims abstract description 12
- 229920005989 resin Polymers 0.000 claims abstract description 12
- 239000011159 matrix material Substances 0.000 claims abstract description 9
- 238000001723 curing Methods 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000000805 composite resin Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims description 2
- 238000009954 braiding Methods 0.000 claims 1
- 239000010410 layer Substances 0.000 description 17
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229920007790 polymethacrylimide foam Polymers 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000004035 construction material Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/245—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it being a foam layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
- B32B2266/02—Organic
- B32B2266/0214—Materials belonging to B32B27/00
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Airvane and its manufacturing method, including airvane ontology are moved entirely the present invention relates to a kind of rocket efficient and light weight, and the airvane ontology includes skeleton and the rudderpost that is connected with the skeleton, and the left side of the skeleton is equipped with left covering, and the right side of the skeleton is equipped with right covering；Further include the foam layer between left covering and right covering, reinforcer is equipped in the foam layer；Carbon fiber resin matrix composite is used, and is provided with foam layer between left covering and right covering, reinforcer is equipped in the foam layer, the load-carrying efficiency of rudder face structure greatly improved；Skeleton, rudderpost, stirrup, foam layer, left covering and right covering it is separately formed after be assembled together using secondary curing technique, the connection of each component reduces assembly work amount without using fastener.
Description
Technical field
The present invention relates to a kind of airvane, its manufacturing method is further related to.
Background technology
Payload is usually sent into space using carrier rocket as means of transport, needs to control during rocket flight
Flight attitude, control flaps are the execution structure of control system.There are mainly two types of control flaps：One is jet vane, jet vane peaces
Behind nozzle, control force is just will produce when the action of high-speed airflow that combustion chamber ejects is on rudder face,
Change the posture of rocket with this, but such control mode can lose part thrust；Another kind is airvane, and airvane is often pacified
On the outside of rocket body endpiece, air-flow generates air force when flowing through airvane, can be produced by changing the angle of rudder reflection of airvane
Raw required control force.
In order to bear and transmit aerodynamic load, ensure that the intensity and toughness of rudder face, conventional air rudder mostly use metal knot
Structure is made, the drawback that there are construction weights is big, bearing capacity is low.Since the requirement to rocket carrying capacity is continuously improved, metal
Structure is gradually difficult to meet design requirement.
Invention content
Technical problem to be solved by the invention is to provide it is a kind of carrying it is big, light-weight, versatile, reliability is high, structure
Type is succinctly convenient for assembly, and aerodynamic efficiency is high, and a kind of good rocket efficient and light weight of rudder face versatility moves airvane entirely.
In order to solve the above technical problems, the technical scheme is that：A kind of rocket efficient and light weight moves airvane entirely, including
Airvane ontology, the airvane ontology include skeleton and the rudderpost that is connected with the skeleton, and the left side of the skeleton is equipped with a left side
The right side of covering, the skeleton is equipped with right covering；Further include the foam layer between left covering and right covering, the foam
Reinforcer is equipped in interlayer.
The reinforcer is stirrup as a preferred technical solution, and the first end of the stirrup is towards the left illiteracy
Skin, the second end of the stirrup is towards the right covering.
The rudderpost is hollow shaft as a preferred technical solution, and there is keyway in the outer surface of the rudderpost.
The foam layer is located at the leading edge and rear of the airvane ontology as a preferred technical solution, is located at institute
The inner cavity for stating the airvane ontology between leading edge and rear is cavity.
The stirrup is carbon fiber resin matrix composite stick as a preferred technical solution, and the stirrup is by same
Direction carbon fiber bundle composition.
The foam core is PMI250 foams as a preferred technical solution,.
The left covering and the right covering are carbon fiber resin matrix composite laminate as a preferred technical solution,
The surfaces externally and internally of structure, the left covering and right covering is respectively laid with 2 layers of woven cloth, and inside is one-way tape, laying deflection be [±
45/+45/-45/90/0]s。
The skeleton and the rudderpost are an integral structure as a preferred technical solution,.
The skeleton is integrated carbon fibre resin base three-dimensional braided structure with rudderpost as a preferred technical solution,.
Another technical problem to be solved by this invention be to provide a kind of above-mentioned carrying of manufacture it is big, it is light-weight, versatile,
Configuration is succinctly convenient for assembly, and aerodynamic efficiency is high, and a kind of good rocket efficient and light weight of rudder face versatility moves airvane entirely
Method.
In order to solve the above technical problems, the technical scheme is that：The skeleton, rudderpost, reinforcer, foam layer,
Left covering and right covering are all made of composite material manufacture, and skeleton, rudderpost, reinforcer, foam layer, left covering and right covering are independent
It is assembled together using secondary curing technique after molding.
Due to the adoption of the above technical scheme, use carbon fiber resin matrix composite, and left covering and right covering it
Between be provided with foam layer, reinforcer is equipped in the foam layer, the load-carrying efficiency of rudder face structure greatly improved；Skeleton,
Rudderpost, stirrup, foam layer, left covering and right covering it is separately formed after be assembled together using secondary curing technique, each group
Part connection does not use fastener, reduces assembly work amount；Entire rudder face can be rotated around rudderpost, and aerodynamic efficiency is high；Rudder
Face versatility is good, is applicable to the installation of all kinds of rockets.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention without having to pay creative labor, may be used also for those of ordinary skill in the art
With obtain other attached drawings according to these attached drawings.
Fig. 1 is structural schematic diagram of the embodiment of the present invention；
Fig. 2 is the sectional view of the embodiment of the present invention；
Fig. 3 is the upward view of Fig. 1；
Fig. 4 is the structural schematic diagram of middle skeleton of the embodiment of the present invention and rudderpost；
Fig. 5 is the structural schematic diagram of rudderpost in the embodiment of the present invention；
Fig. 6 is the structural schematic diagram of left covering and right covering in the embodiment of the present invention；
Fig. 7 is the structural schematic diagram of foam layer in the embodiment of the present invention.
Specific implementation mode
The present invention is illustrated below by specific embodiment, but is not intended to limit the present invention.
As shown in Figures 1 to 4, a kind of rocket efficient and light weight moves airvane, including airvane ontology, the airvane sheet entirely
Body includes skeleton 1 and the rudderpost being connected with the skeleton 12, and the left side of the skeleton 1 is equipped with left covering 3, the right side of the skeleton 1
Side is equipped with right covering 4；Further include the foam layer 5 between left covering 3 and right covering 4, is equipped with and adds in the foam layer 5
Strong part 6.Carbon fiber resin matrix composite is used, and is provided with foam layer between left covering and right covering, the bubble
It is equipped with reinforcer in foam interlayer, the load-carrying efficiency of rudder face structure greatly improved.
As shown in Fig. 2, the reinforcer 6 is stirrup, the first end of the stirrup is described towards the left covering 3
The second end of stirrup is towards the right covering 4.Such structure can further ensure the intensity booster action of stirrup, carry
The high load-carrying efficiency of rudder face structure.
As shown in Figure 1 and Figure 5, the rudderpost 2 is hollow shaft, and there is keyway 7 in the outer surface of the rudderpost 2.It further increases
Structure efficiency.
As shown in Fig. 2, the foam layer is located at the leading edge and rear of the airvane ontology, it is located at the leading edge with after
The inner cavity of the airvane ontology between edge is cavity.Structural bearing efficiency can be further increased using such structure.
The stirrup is carbon fiber resin matrix composite stick, and the stirrup is made of equidirectional carbon fiber bundle.It adopts
It uses carbon fiber resin matrix composite as stirrup, the load-carrying efficiency of rudder face structure can be effectively improved.
The foam core is PMI250 foams.The full name of PMI foams is Polymethacrylimide, is a kind of lightweight
The foamed plastics of high intensity is mainly used in aerospace, radar antenna outer cover, CT medical treatment bed board, wind-powered electricity generation helicopter blade, height
Fast train is structural core most hard under same density conditions at present, PMI250 foams are PMI foams even in construction material
One kind.
As shown in Fig. 1, Fig. 3 and Fig. 6, the left covering and the right covering are carbon fiber resin matrix composite laminate
The surfaces externally and internally of structure, the left covering and right covering is respectively laid with 2 layers of woven cloth, and inside is one-way tape, laying deflection be [±
45/+45/-45/90/0]s。
As shown in figure 4, the skeleton 1 and the rudderpost 2 are an integral structure, intermediate no connector improves structure effect
Rate.
Preferably, the skeleton 1 is integrated carbon fibre resin base three-dimensional braided structure with rudderpost 2.Using carbon fiber tree
The load-carrying efficiency of resin-based composite, rudder face structure is high.
The present invention also provides the manufacturing methods that a kind of rocket efficient and light weight moves airvane entirely.
A kind of rocket efficient and light weight moves the manufacturing method of airvane, the skeleton, rudderpost, reinforcer, foam layer, a left side entirely
Covering and right covering be all made of composite material manufacture, skeleton, rudderpost, reinforcer, foam layer, left covering and right covering individually at
It is assembled together using secondary curing technique after type.
Due to the adoption of the above technical scheme, skeleton, rudderpost, stirrup, foam layer, left covering and right covering are separately formed
It is assembled together afterwards using secondary curing technique, each component connection does not use fastener, reduces assembly work amount；Entire rudder face
It can be rotated around rudderpost, aerodynamic efficiency is high；Rudder face versatility is good, is applicable to the installation of all kinds of rockets.Each component connection
Without using fastener, assembly work amount is reduced.
The basic principles and main features and advantages of the present invention of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the above embodiments and description only describe this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (10)
1. a kind of rocket efficient and light weight moves airvane entirely, which is characterized in that including airvane ontology, the airvane ontology includes
The left side of skeleton and the rudderpost being connected with the skeleton, the skeleton is equipped with left covering, and the right side of the skeleton is equipped with right covering；
Further include the foam layer between left covering and right covering, reinforcer is equipped in the foam layer.
2. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the reinforcer is stirrup,
The first end of the stirrup is towards the left covering, and the second end of the stirrup is towards the right covering.
3. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the rudderpost is hollow shaft, institute
There is keyway in the outer surface for stating rudderpost.
4. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the foam layer is located at described
The inner cavity of the leading edge and rear of airvane ontology, the airvane ontology between the leading edge and rear is cavity.
5. rocket efficient and light weight as claimed in claim 2 moves airvane entirely, which is characterized in that the stirrup is carbon fiber tree
Resin-based composite stick, the stirrup are made of equidirectional carbon fiber bundle.
6. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the foam core is
PMI250 foams.
7. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the left covering and the right illiteracy
Skin is carbon fiber resin matrix composite laminated plate structure, surfaces externally and internally respectively 2 layers of braiding of laying of the left covering and right covering
Cloth, inside are one-way tape, and laying deflection is [± 45/+45/-45/90/0] s.
8. rocket efficient and light weight as described in claim 1 moves airvane entirely, which is characterized in that the skeleton and the rudderpost are
Integral structure.
9. rocket efficient and light weight as claimed in claim 8 moves airvane entirely, which is characterized in that the skeleton is integrated with rudderpost
Change carbon fibre resin base three-dimensional braided structure.
10. a kind of method that manufacture rocket efficient and light weight as described in claim 1 moves airvane entirely, it is characterised in that：Skeleton,
Rudderpost, reinforcer, foam layer, left covering and right covering are all made of composite material manufacture, skeleton, rudderpost, reinforcer, foam folder
Layer, left covering and right covering it is separately formed after be assembled together using secondary curing technique.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810165900.XA CN108372936A (en) | 2018-03-02 | 2018-03-02 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810165900.XA CN108372936A (en) | 2018-03-02 | 2018-03-02 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108372936A true CN108372936A (en) | 2018-08-07 |
Family
ID=63018331
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810165900.XA Withdrawn CN108372936A (en) | 2018-03-02 | 2018-03-02 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108372936A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN110450939A (en) * | 2019-08-19 | 2019-11-15 | 西安长峰机电研究所 | A kind of variable cross-section airvane |
| CN111071430A (en) * | 2019-12-26 | 2020-04-28 | 湖北航天技术研究院总体设计所 | Switching structure and rudder of composite material rudder of high-speed aircraft |
| RU2724081C1 (en) * | 2019-09-13 | 2020-06-19 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | High-speed aircraft aerodynamic rudder |
| CN111946461A (en) * | 2020-07-27 | 2020-11-17 | 山东鑫聚龙动力科技集团有限公司 | Wing shaft for aerospace engine and manufacturing process thereof |
| CN113686206A (en) * | 2021-08-18 | 2021-11-23 | 上海机电工程研究所 | 3D printing air vane and processing method |
-
2018
- 2018-03-02 CN CN201810165900.XA patent/CN108372936A/en not_active Withdrawn
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN109631688B (en) * | 2018-11-21 | 2021-09-07 | 中国运载火箭技术研究院 | X-shaped composite material rocket stage section or box section connecting structure |
| CN110450939A (en) * | 2019-08-19 | 2019-11-15 | 西安长峰机电研究所 | A kind of variable cross-section airvane |
| RU2724081C1 (en) * | 2019-09-13 | 2020-06-19 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | High-speed aircraft aerodynamic rudder |
| CN111071430A (en) * | 2019-12-26 | 2020-04-28 | 湖北航天技术研究院总体设计所 | Switching structure and rudder of composite material rudder of high-speed aircraft |
| CN111071430B (en) * | 2019-12-26 | 2021-11-30 | 湖北航天技术研究院总体设计所 | Switching structure and rudder of composite material rudder of high-speed aircraft |
| CN111946461A (en) * | 2020-07-27 | 2020-11-17 | 山东鑫聚龙动力科技集团有限公司 | Wing shaft for aerospace engine and manufacturing process thereof |
| CN113686206A (en) * | 2021-08-18 | 2021-11-23 | 上海机电工程研究所 | 3D printing air vane and processing method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108372936A (en) | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely | |
| Ghori et al. | The role of advanced polymer materials in aerospace | |
| CA2838300C (en) | Box structures for carrying loads and methods of making the same | |
| EP3077194B1 (en) | Bonded and tailorable composite assembly | |
| EP2778393A2 (en) | Wind turbine blade design and associated manufacturing methods using rectangular spars | |
| US20120148789A1 (en) | Aircraft structure with structural parts connected by nanostructure and a method for making said aircraft structure | |
| EP2415665B1 (en) | Rotor blade | |
| CN105015761A (en) | Morphing airfoil leading edge | |
| EP3205575B1 (en) | Laminar flow panel | |
| EP3159259B1 (en) | Leading edge with laminar flow control and manufacturing method thereof | |
| CA2803434C (en) | Optimized core for a structural assembly | |
| EP2759470A2 (en) | Box structures for carrying loads and methods of making the same | |
| US11565800B2 (en) | Multi-piece assembly for a tubular composite body | |
| EP2895389B1 (en) | Passive load alleviation for aerodynamic lift structures | |
| CN208602720U (en) | A kind of rocket efficient and light weight moves airvane entirely | |
| US20230219696A1 (en) | Lightning strike protection layer | |
| CA2995889C (en) | Method and apparatus to improve lift to drag ratio of a rotor blade | |
| CN110341927A (en) | Aircraft fuselage with composite prefabricated | |
| US20220119092A1 (en) | Composite thin wingbox architecture for supersonic business jets | |
| US11148783B2 (en) | Corrugated lift fan rotor | |
| US11319052B2 (en) | Leading-edge arrangement for a flow body of a vehicle | |
| KR102131562B1 (en) | Fiber reinforced plastic propellers for unmanned aerial vehicle and menufacturing method thereof | |
| US20240017812A1 (en) | System, apparatus, and method of manufacture for a rib structure | |
| US20240109643A1 (en) | Tubular wing structures and methods of manufacture | |
| Davis et al. | Status of ERA Airframe Technology Demonstrators |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Address before: 100176 329, 3rd floor, building 1, No.9, Disheng South Street, Beijing Economic and Technological Development Zone, Daxing District, Beijing Applicant before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. |
|
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180807 |