CN104298798B - Three-dimensional coordinating method for airplane product - Google Patents
Three-dimensional coordinating method for airplane product Download PDFInfo
- Publication number
- CN104298798B CN104298798B CN201410154137.2A CN201410154137A CN104298798B CN 104298798 B CN104298798 B CN 104298798B CN 201410154137 A CN201410154137 A CN 201410154137A CN 104298798 B CN104298798 B CN 104298798B
- Authority
- CN
- China
- Prior art keywords
- coordination
- dimensional
- lid
- coordinated
- requirement
- 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.)
- Active
Links
Landscapes
- Processing Or Creating Images (AREA)
Abstract
The invention belongs to the field of airplane design and relates to establishment of a method for conducting three-dimensional coordination on all systems of an airplane product in the detailed initial design stage. The method is characterized by comprising the steps that firstly, coordination of all specialties of the airplane product is divided into three types; secondly, three types of three-dimensional coordination models are established respectively; thirdly, mutual coordination is conducted between the specialties to confirm data. By means of the method, the whole course data transmission in the developing process of large industrial products such as airplanes is achieved, and thus the transmission of the coordination data is accurate and fast; the geometric models expressed with points, lines and planes which occupy quite little resources and quite small space are adopted in the three-dimensional coordination models to specially express the coordination information between the specialties, and the expressed content is concise and clear; the standardized three-dimensional coordination models enable coordination elements to be completely expressed, and missing and incompletion of the coordination elements are effectively avoided; the three-dimensional coordination models facilitate the concentrated expression of the coordination elements; state control is adopted in the three-dimensional coordination models, and thus data management and tracing are facilitated.
Description
Technical field
The invention belongs to field of airplane design, is related between a kind of each system for aircraft product in detailed Preliminary design rank
A kind of establishment of method when Duan Jinhang is three-dimensional coordinated.
Background technology
For conventional airplane, the coordination between detailed concept phase, each specialty be using two dimension coordination figure,
Coordinate label and coordination summary to record the coordinating content between specialty, after coordinated area's Acceptance Review is qualified, as winged
The Main Basiss of machine detailed design.Due to aircraft product be related to it is numerous specialty between it is mutually coordinated, content is extremely complex, one
Aircraft type generally requires thousand of or even up to ten thousand parts and coordinates single, while also need to draw hundreds of magnifying type coordination figure.Draw and coordinate figure
Designer's substantial amounts of time is occupied with label is coordinated, the workload of coordination is very huge.According to statistics, the association of conventional airplane
About 4~5 months tune cycles.
In recent years, the main research company of the aircraft of home and abroad is employed the digital prototype for setting up part three-dimensional entity model
To replace coordination to scheme, but the coordination label of the interface for expression specialty, still follow traditional two-dimensional approach.It is this
2nd, the coordination mode of hybrid three-dimensional causes the transmission of digitized design data to interrupt, and turns two-dimentional, D reconstruction three-dimensional
During easily produce the deviation of data, the problems such as lose, and because the quantity for coordinating label is huger, draws, beat
Print and implement and all occupy designer's plenty of time.It can be said that in the present circumstance, it is to restrict this that two dimension coordinates single presence
Plant the quality and the main cause of efficiency of two, three coordination modes for mixing.
The content of the invention
The purpose of the present invention is：There is provided a kind of aircraft product three-dimensional coordinated method, it is complete by creating three-dimensional coordinated model
Replace traditional two dimension to coordinate single entirely so that the transmission of coordination data is smooth, accurate, realize whole three-dimensional coordinated；And three
Increase normalized attribute expressing information in dimension Coordination Model, it is ensured that coordinate key element comprehensively, so as to improve the quality and effect of coordination
Rate.
The technical scheme is that：A kind of establishment of the three-dimensional coordinated method of aircraft product, for the detailed of aircraft product
The thin concept phase.By the conclusion to each specialty of aircraft product, classification, the three-dimensional coordinated model of 3 classes, three-dimensional association are created
Mode transfer type includes：1. the geometric model for being represented with point, line, surface；2. Common Difference ＆ Cooperation, the rough surface expressed with three-dimensional labeling
Degree；3. with attribute information and environment, the clearance requirement of literal expression, it is characterised in that comprise the steps：
First, the coordination between each specialty of aircraft product is divided into into following 3 class：
1) system and interstructural coordination
2) interface coordination between system attachment
3) interface coordination between structure member
Second, it is respectively created the three-dimensional coordinated model of above-mentioned 3 class
1）System is set up in the steps below with interstructural three-dimensional coordinated model
I. the exterior contour curved surface of extraction system adnexa, for representing system attachment locus aboard；Set up
System attachment is connected curved surface with the installation of structure, for representing link position and the region of system attachment；Have with structure relative
The adnexa of motion, makes its motion envelope face relative to structure, for taking the locus that fitments are scanned；
Ii. with the attribute information of literal expression system attachment include the title of system attachment, model, weight, affiliated bay section,
Damping requirement, air-conditioning requirement, ambient vibration requirement, ambient temperature requirement, connection cable requirement, sealing requirements, electromagnetic compatibility
Property requirement, clearance requirement, maintainability require；
Iii. by the installation lid of system attachment and safeguard the outline shape of lid with the form flash of space lines to winged
On the appearance curved surface of machine structure, installation lid and position and the geometry of safeguarding lid of expression system attachment use literal table
The attribute information for state system attachment installation, safeguarding includes lid purposes, lid fixed form, lid maintenance period, lid mark；
Iv. in structure perforate is coordinated to carry out the incidental pipe path of system, is projected to outside structure using space lines
On shape curved surface, for representing the geometry and size of pipe path, included with the attribute information of character express pipe path logical
Road purposes, pipeline fixed form, open road particular/special requirement；
2）The three-dimensional coordinated model between system attachment is set up in the steps below
I. the position by the interface between mutually coordinated two systems adnexa aboard, sets up two systems adnexa indirect
Appearance profile curved surface at mouthful, for representing position, the shape and size of system attachment interface；Set up above-mentioned two mutually to assist
The geometric curved surfaces connected between the system attachment of tune, for expressing link information；
Ii. with the attribute information of the mutually coordinated two systems adnexa of character express include the title of system attachment, model,
Weight, affiliated bay section；Seal request, clearance requirement, pressure requirements, the work of seam are expressed with the form of word or three-dimensional labeling
Make liquid, working gas, particular/special requirement；
Iii. Common Difference ＆ Cooperation, the surface of mutually coordinated two systems adnexa interface are expressed with the form of three-dimensional labeling
Roughness, the diameter of thread, pitch, thread tolerance；
3）The three-dimensional coordinated model between structure member is set up in the steps below
I. according to jointing position aboard is concentrated between structure member, the appearance profile for concentrating jointing is set up
Curved surface, for the relative position and type of attachment of joint between expression structure part；
Ii. the geometric curved surfaces of bonding pad between above-mentioned two structure member are set up, for expressing position and the connection of bonding pad
Region；
If iii. needing to open up technique lid in connection, lid is drawn with curve on the external surface of structure
Appearance profile, with character express attribute information lid purposes, lid connected mode, lid mark are included；
Iv. concentrated between load joint with the expression of the form of three-dimensional labeling and the Common Difference ＆ Cooperation of bonding pad, surface roughness,
Particular/special requirement.
3rd, mutually coordinated between specialty, the above-mentioned data of confirmation.
A) coordinate to refer to the design requirement proposed between aircraft detailed concept phase each specialty, including space erect-position, peace
Reload request, working service are required, and are confirmed whether executable process by relevant speciality, if not can perform, adjust each special
The space erect-position of industry, installation requirement, working service require parameter；Including between said system and interstructural coordination, system attachment
Interface coordination and structure member between interface coordination；
B) system is to refer to all devices on aircraft in addition to structure, adnexa and pipeline, including dynamical system, Fuel System
It is system, environmental control system, hydraulic system, steerable system, avionics system, life-support system, armament systems, cabin display and control system, logical
Lead, the equipment of antenna, take-off and landing device, adnexa and associated pipe；
C) structure or structure member refer to that airframe, wing, empennage, undercarriage etc. bear and transmit takeoff and anding load
Lotus, overall flight load, the associated components of the various system attachments of fixation, structure is the skeleton of aircraft；
D) exterior contour curved surface refers to structure or the space erect-position outside system attachment, is not allow in the range of the curved surface
Other systems, structure；
E) motion envelope face refers to the sky that the system attachment for producing motion relative to structure is scanned out in motor process
Between position curved surface, other systems, structure are not allow in the range of the curved surface；
F) digital prototype refer to aircraft the detailed concept phase set up between each specialty coordinate fly
The combination of machine part three-dimensional entity model.
Distinguish over and coordinated using the digital prototype of material object parts model, the three-dimensional coordinated side of described aircraft product
Method, the geometric model constituted using point, line, surface and three-dimensional labeling, the Word message of correlation, specially to express the coordination between specialty
Information.
It is an advantage of the invention that：
1）The foundation of three-dimensional coordinated model realizes the whole data transfer of the large scale industry product development such as aircraft, thoroughly gets rid of
Existing three-dimensional is abandoned and has turned two-dimentional, D reconstruction again unscientific coordination mode so that the transmission of coordination data is accurately, soon
Speed, and coordination flow process is simplified, accompanying drawing 1 is seen, so as to improve the efficiency of coordination；
2）Three-dimensional coordinated model is very little light-weighted using resource space is taken（Point, line, surface etc.）Geometric model, and
Material object parts model is not adopted, specially to express the coordination information between specialty so that the content of expression is succinct, clear；
3）Due to the three-dimensional coordinated model of code requirement, all of coordination key element all with geometry, attribute information and
The form of three-dimensional labeling is expressed so that the expression for coordinating key element is complete, is effectively prevented from coordinating the omission of key element, not comprehensive
Deng substantially increasing the quality of coordination；
4）Three-dimensional coordinated model is easy to coordination key element concentration to express, one of such as hydraulic system and rear body structure discipline
Three-dimensional coordinated model can replace original more than 100 parts of coordination list；
5）Three-dimensional coordinated model tormulation is directly perceived, and visual strong, friendly interface is easily received by user；
6）Three-dimensional coordinated model can be easy to the management of data and reviewed with adoption status control.
Description of the drawings
Accompanying drawing 1 is that traditional coordination approach is contrasted with the flow process of three-dimensional coordinated method
Accompanying drawing 2 is the coordination information that oil return hydraulic filter is put in structure and fixed
Accompanying drawing 3 is oil return hydraulic filter environment in structure and clearance requirement
Accompanying drawing 4 is oil return hydraulic filter installation lid in structure and safeguards the coordination of lid
Accompanying drawing 5 is that the pipe path perforate in structure of hydraulic system is coordinated
The interface coordination of the take-off and landing device cabin door lock of accompanying drawing 6 and hydraulic pipe
The dimension information of the take-off and landing device cabin door lock hydraulic pipe joint of accompanying drawing 7
Shape and position of the vertical fin of accompanying drawing 8 with rear body part jointing
The technique lid and lid information of the vertical fin of accompanying drawing 9 and rear body part
Specific embodiment
Below by some specific embodiments and combine accompanying drawing the present invention is described in further detail.
Most preferred embodiment one
With aircraft product the adnexa, pipeline and rear body structure discipline of detailed concept phase hydraulic system coordination
As a example by, system as follows is set up with interstructural three-dimensional coordinated model：
First, according to digital prototype, the appearance profile curved surface of the oil return hydraulic filter of hydraulic system is put in by putting position
In three-dimensional coordinated model（The cylindrical shape curved surface seen in accompanying drawing 2）；Set up oil return hydraulic filter and the curved surface being connected is installed with structure（See
Bearing shape curved surface in accompanying drawing 2）, for expressing the join domain and type of attachment of oil return hydraulic filter and structure；
2nd, title of the attribute information including oil return hydraulic filter is filled in one by one（Oil return hydraulic filter）, model（YYL-
69Z）, weight (2kg), affiliated bay section（Left tail boom area）；
3rd, carry out oil return hydraulic filter to coordinate with interstructural environment and gap, with character express oil return hydraulic filter
Damping requirement, air-conditioning requirement, ambient vibration requirement, ambient temperature requirement, connection cable requirement, sealing requirements, electromagnetic compatibility
Property requirement, clearance requirement, maintainability require, "None" is filled in if not requiring, see accompanying drawing 3；
4th, the coordination of installation lid and maintainability lid of the oil return hydraulic filter in rear body structure is carried out, first will
The space lines of lid are projected on the appearance curved surface of rear body structure, are installed lid for expression and are safeguarded the geometric form of lid
Shape, above-mentioned space lines are put in the geometric figure of " lid model " and concentrate, with character express lid purposes, lid classification, mouth
Lid fixed form, lid maintenance period, are shown in accompanying drawing 4；
5th, in structure perforate is coordinated to carry out the incidental pipe path of hydraulic system, to ensure the insertion of conduit under fluid pressure,
Project on construction profile curved surface to express the geometry and size of pipe path using space lines, the lines are put in " to be opened
The geometric figure of pore model " is concentrated, and with the attribute information of character express pipe path perforate title, the tapping side of fixation are included
Formula, perforate particular/special requirement, are shown in accompanying drawing 5.
6th, the technical staff of hydraulic pressure specialty and rear body structure discipline coordinates, confirms the realizability and standard of above-mentioned data
Really property, three-dimensional coordinated model is put in data base examine label, frozen state after the completion of coordination.
Because the adnexa of hydraulic system is a lot, should coordinate one by one, but hydraulic system is to rear body structure discipline
All of coordination information can be put in same three-dimensional coordinated model so that the expression of coordination information concentrates, complete.
Most preferred embodiment two
By taking coordination of the aircraft product between detailed concept phase take-off and landing device cabin door lock and hydraulic pipe as an example, set up
Three-dimensional coordinated model between system attachment as follows：
First, according to the interface position aboard of take-off and landing device cabin door lock and hydraulic pipe, two adnexaes are set up indirect
Appearance profile curved surface at mouthful, for representing position, the shape and size of take-off and landing device cabin door lock hydraulic joint；Set up above-mentioned two
The geometric curved surfaces connected between person, for expressing link information, are shown in accompanying drawing 6；
2nd, title, model, weight, material are included with the attribute information of character express take-off and landing device cabin door lock；With word or
Seal request, clearance requirement, operating pressure, work at the form expression take-off and landing device cabin door lock hydraulic pipe of three-dimensional labeling
Liquid, working gas, the blowing pressure, particular/special requirement, are shown in accompanying drawing 6；
3rd, the reach 13, surface with the form expression take-off and landing device cabin door lock hydraulic pipe joint of three-dimensional labeling is thick
Rugosity Ra1.6, diameter of thread Φ 12, pitch 1, thread tolerance 6e, catheter diameter Φ 3.7, catheter head diameter of phi 4.6, conduit
Head outer diameter Φ 10.5,74 ° ± 30 ' of catheter head cone angle, is shown in accompanying drawing 7.
Most preferred embodiment three
By taking coordination of the aircraft product between detailed concept phase vertical fin structure member and rear body structure member as an example,
Set up the three-dimensional coordinated model between structure shown below part：
First, according to center tap position aboard is collected between vertical fin and rear body, the profile wheel for concentrating jointing is set up
Contour curved surface, for expressing the relative position and type of attachment of vertical fin and rear body jointing, vertical fin adopts ears auricle, rear machine
Body adopts monaural auricle, every group of joint to adopt two groups of bolt connections, and auricle form, selection, bolt position, size and selection are shown in attached
Fig. 8；
2nd, the geometric curved surfaces of bonding pad between vertical fin root and rear body structure are set up, for express bonding pad position and
Join domain, is shown in accompanying drawing 8；
3rd, need to open up technique lid when rudder steering wheel is installed, lid is drawn with curve on the external surface of structure
Appearance profile, be put in " lid model " geometric figure concentrate, with character express attribute information include lid purposes, lid class
Not, lid fixed form, lid maintenance period, lid mark, are shown in accompanying drawing 8；
4th, the Common Difference ＆ Cooperation Φ 30H8/ in track bolt hole is concentrated with the form expression vertical fin and rear body of three-dimensional labeling
F7, vertical fin auricle thickness deviation 17H7, rear body auricle thickness deviation 34h11, surface roughness Ra 1.6, two bolts hole
Apart from tolerance 161.64（+0.05/0）.
Claims (1)
1. a kind of establishment of the three-dimensional coordinated method of aircraft product, for the detailed concept phase of aircraft product, by right
The conclusion of aircraft product each specialty, classification, create the three-dimensional coordinated model of 3 classes, and three-dimensional coordinated model includes：1. with point, line,
The geometric model that face represents；2. Common Difference ＆ Cooperation, the surface roughness expressed with three-dimensional labeling；3. believed with the attribute of literal expression
Breath and environment, clearance requirement, it is characterised in that comprise the steps：
First, the coordination between each specialty of aircraft product is divided into into following 3 class
1) system and interstructural coordination
2) interface coordination between system attachment
3) interface coordination between structure member
Second, it is respectively created the three-dimensional coordinated model of above-mentioned 3 class
1) system is set up in the steps below with interstructural three-dimensional coordinated model
I. the exterior contour curved surface of extraction system adnexa, for representing system attachment locus aboard；Set up system
Adnexa is connected curved surface with the installation of structure, for representing link position and the region of system attachment；There is relative motion with structure
Adnexa, its motion envelope face relative to structure is made, for taking the locus that fitments are scanned；
Ii. title, model, weight, affiliated bay section, the damping of system attachment are included with the attribute information of literal expression system attachment
Requirement, air-conditioning requirement, ambient vibration requirement, ambient temperature requirement, connection cable requirement, sealing requirements, Electro Magnetic Compatibility are wanted
Ask, clearance requirement, maintainability requirement；
Iii. the installation lid of system attachment is tied with the outline shape for safeguarding lid with the form flash of space lines to aircraft
On the appearance curved surface of structure, installation lid and position and the geometry of safeguarding lid of expression system attachment use character express system
System adnexa is installed, the attribute information of maintenance includes lid purposes, lid fixed form, lid maintenance period, lid mark；
Iv. in structure perforate is coordinated to carry out the incidental pipe path of system, projects to construction profile using space lines bent
On face, for representing the geometry and size of pipe path, used including path with the attribute information of character express pipe path
On the way, pipeline fixed form, open road particular/special requirement；
2) the three-dimensional coordinated model between system attachment is set up in the steps below
I. the position by the interface between mutually coordinated two systems adnexa aboard, sets up at two systems adnexa interface
Appearance profile curved surface, for representing position, the shape and size of system attachment interface；Set up above-mentioned two mutually coordinated
The geometric curved surfaces connected between system attachment, for expressing link information；
Ii. title, model, the weight of system attachment are included with the attribute information of the mutually coordinated two systems adnexa of character express
Amount, affiliated bay section；Seal request, clearance requirement, pressure requirements, the work of seam are expressed with the form of word or three-dimensional labeling
Liquid, working gas, particular/special requirement；
Iii. Common Difference ＆ Cooperation, the rough surface of mutually coordinated two systems adnexa interface are expressed with the form of three-dimensional labeling
Degree, the diameter of thread, pitch, thread tolerance；
3) the three-dimensional coordinated model between structure member is set up in the steps below
I. according to jointing position aboard is concentrated between structure member, set up and concentrate the appearance profile of jointing bent
Face, for the relative position and type of attachment of joint between expression structure part；
The geometric curved surfaces of bonding pad between two structure members ii. set up in said structure part, for expressing the position of bonding pad
Put and join domain；
If iii. needing to open up technique lid in connection, the profile of lid is drawn with curve on the external surface of structure
Profile, with character express attribute information lid purposes, lid connected mode, lid mark are included；
Iv. concentrated between load joint with the expression of the form of three-dimensional labeling and the Common Difference ＆ Cooperation of bonding pad, surface roughness, special
Require；
3rd, mutually coordinated between specialty, the above-mentioned three-dimensional coordinated model data of confirmation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410154137.2A CN104298798B (en) | 2014-04-17 | 2014-04-17 | Three-dimensional coordinating method for airplane product |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410154137.2A CN104298798B (en) | 2014-04-17 | 2014-04-17 | Three-dimensional coordinating method for airplane product |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104298798A CN104298798A (en) | 2015-01-21 |
| CN104298798B true CN104298798B (en) | 2017-05-17 |
Family
ID=52318523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410154137.2A Active CN104298798B (en) | 2014-04-17 | 2014-04-17 | Three-dimensional coordinating method for airplane product |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104298798B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10043311B2 (en) * | 2015-09-16 | 2018-08-07 | The Boeing Company | Immersive design management system |
| CN107357964B (en) * | 2017-06-19 | 2019-09-27 | 江苏科技大学 | A kind of graphic representation method of geometric tolerance |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101556704A (en) * | 2009-05-19 | 2009-10-14 | 武汉一冶钢结构有限责任公司 | Method for establishing temporary supporting frame system assembled by steel structures |
| CN102982220A (en) * | 2012-12-25 | 2013-03-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Parametrization design method of first-level member of rib type part of airplane |
| CN102999677A (en) * | 2012-12-25 | 2013-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | First-level construction member parametrization design method for airplane frame-type parts |
| CN103020375A (en) * | 2012-12-25 | 2013-04-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for parametrically designing primary components of airplane long truss-type parts |
| CN103093031A (en) * | 2012-12-25 | 2013-05-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Parametrization design method for aircraft skin wall panel part primary components |
-
2014
- 2014-04-17 CN CN201410154137.2A patent/CN104298798B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101556704A (en) * | 2009-05-19 | 2009-10-14 | 武汉一冶钢结构有限责任公司 | Method for establishing temporary supporting frame system assembled by steel structures |
| CN102982220A (en) * | 2012-12-25 | 2013-03-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Parametrization design method of first-level member of rib type part of airplane |
| CN102999677A (en) * | 2012-12-25 | 2013-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | First-level construction member parametrization design method for airplane frame-type parts |
| CN103020375A (en) * | 2012-12-25 | 2013-04-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for parametrically designing primary components of airplane long truss-type parts |
| CN103093031A (en) * | 2012-12-25 | 2013-05-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Parametrization design method for aircraft skin wall panel part primary components |
Non-Patent Citations (4)
| Title |
|---|
| 全三维技术在飞机设计中的应用;田承根等;《航空制造技术》;20111231;第2011年卷(第22期);第57-59、97页 * |
| 基于数字标工模型的飞机数字化协调方法;周秋忠等;《计算机集成制造***》;20080430;第14卷(第4期);第683-689页 * |
| 飞机协调三维数字化研究;樊海东等;《第五届中国航空学会青年科技论坛》;20121008;第116-119页 * |
| 飞机数字化制造环境下的协调方法;孟飙;《沈阳航空工业学院学报》;20090228;第26卷(第1期);第31-34页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104298798A (en) | 2015-01-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Dimino et al. | Integrated design of a morphing winglet for active load control and alleviation of turboprop regional aircraft | |
| Lei et al. | The aerodynamic performance of passive wing pitch in hovering flight | |
| CN104298798B (en) | Three-dimensional coordinating method for airplane product | |
| CN104708195A (en) | Apparatus for friction stir welding | |
| CN107526303A (en) | A kind of Vehicle Management System simulation and verification platform | |
| Bramsiepe et al. | Loads and structural optimization process for composite long range transport aircraft configuration | |
| Tomac et al. | Towards automated hybrid-prismatic mesh generation | |
| Yoo et al. | Computational analysis of the external aerodynamics of the unpowered X-57 Mod-III aircraft | |
| Ito et al. | JAXA’s and KHI’s Contribution to the Third High Lift Prediction Workshop | |
| Bishay et al. | Design and analysis of MataMorph-3: A fully morphing UAV with camber-morphing wings and tail stabilizers | |
| Handojo et al. | Potential Estimation of Load Alleviation and Future Technologies in Reducing Aircraft Structural Mass | |
| Li et al. | A review of flow control for gust load alleviation | |
| Karpuk et al. | Design Investigation of Potential Long-Range Hydrogen Combustion Blended Wing Body Aircraft with Future Technologies | |
| Sagaga et al. | CFD hover predictions for the side-by-side urban air taxi concept rotor | |
| Pattinson et al. | High fidelity simulation of the folding wing tip for loads alleviaton | |
| CN104217052A (en) | Collaborative design method for mechanical assembly and structure | |
| Ceruti et al. | Maintenance in Aeronautics in an Industry 4.0 Context: the role of AR and AM | |
| Mohan et al. | Systems integration framework for hybrid-electric commuter and regional aircraft | |
| Kuzmin et al. | Airfoils admitting anomalous behavior of lift coefficient in descending transonic flight | |
| Voß et al. | Design, structural optimization and loads assessment for a flying wing | |
| Ventura Diaz et al. | High-fidelity computational aerodynamics of the elytron 4S UAV | |
| CN206107550U (en) | Wing wallboard butt -joint structural | |
| He et al. | CYFFD parameterization method for cylindrical components of aircrafts | |
| Imumbhon et al. | Structural and CFD analyses of a reciprocating-airfoil (RA) driven UAV wing under maximum lift and inertia forces | |
| Chiarelli et al. | Design and Feasibility Study of Novel Flying Wing Carrier for Launching Small Satellites in Low Earth Orbit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |