CN106781706B - Air traffic Track Design method based on wind field distribution - Google Patents
Air traffic Track Design method based on wind field distribution Download PDFInfo
- Publication number
- CN106781706B CN106781706B CN201611168868.8A CN201611168868A CN106781706B CN 106781706 B CN106781706 B CN 106781706B CN 201611168868 A CN201611168868 A CN 201611168868A CN 106781706 B CN106781706 B CN 106781706B
- Authority
- CN
- China
- Prior art keywords
- air route
- wind field
- route section
- model
- oil consumption
- 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
Classifications
-
- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0073—Surveillance aids
- G08G5/0091—Surveillance aids for monitoring atmospheric conditions
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Atmospheric Sciences (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Navigation (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention provides a kind of air traffic Track Design method based on wind field distribution, this method comprises: establishing the wind field space-time characterisation model of each air route section according to wind field attribute data, according to the wind field space-time characterisation model of each air route section, establish vehicle aerodynamics model, according to vehicle aerodynamics model, the oil consumption model of each air route section between starting point to the end is calculated, the oil consumption evaluation function of each air route section is calculated according to the oil consumption model of each air route section, according to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated, fuel cost based on each air route section, determine the smallest air route route of fuel cost from starting point to the end, due to considering the influence of wind field distribution factor, the smallest air route route of the fuel cost of obtained starting point to the end is the minimum air route of oil consumption transportation cost.
Description
Technical field
The present invention relates to the designing technique in air traffic air route more particularly to a kind of air traffic boats based on wind field distribution
Road design method.
Background technique
In traffic administration in the sky (Air Traffic Management, abbreviation ATM) system, air traffic air route is played the part of
Very important role, and the superiority and inferiority of flight-path seeking will directly affect the oil consumption transportation cost of each aircraft in airspace.
Currently, the foundation of optimal air traffic flight-path seeking be all air routes section between starting point to the end space length it
With shortest air route, but due to the influence of wind-engaging field distribution factor, the shortest air route of the space length is not oil consumption transport
The minimum air route of cost.
Summary of the invention
The present invention provide it is a kind of based on wind field distribution air traffic Track Design method so that consider wind field distribution because
Under the influence of element, pass through the air route that air route that this method selects is minimum for oil consumption transportation cost.
The present invention provides a kind of air traffic Track Design method based on wind field distribution, comprising:
Wind field attribute data is obtained and counts, according to the wind field attribute data, it is established that put each air route between to terminal
The wind field space-time characterisation model of section；
According to the wind field space-time characterisation model of each air route section, vehicle aerodynamics model is established；
According to the vehicle aerodynamics model, the oil consumption of each air route section between the starting point to the end is calculated
Model；
According to the oil consumption model of the quantity of each upper aircraft of air route section and each air route section, it is calculated each
The oil consumption evaluation function of air route section；
According to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated；
Based on the fuel cost of each air route section, the smallest air route route of fuel cost from starting point to the end is determined.
Optionally, described to obtain and count wind field attribute data, according to the wind field attribute data, it is established that point is to terminal
Between each air route section wind field space-time characterisation model before, further includes:
Starting point, the terminal for obtaining air route, carry out classification processing to the way point between the starting point, terminal, obtain at different levels
Way point；
Sliding-model control is carried out to the way points at different levels, determines at least one way point in each classification；
Route of each air route section between each adjacent classification between any two way point.
Optionally, described to obtain and count wind field attribute data, according to the wind field attribute data, it is established that point is to terminal
Between each air route section wind field space-time characterisation model, comprising:
The wind field attribute data includes: north and south wind field observation data；
Numerical simulation is carried out to north and south wind field observation data, obtains the wind field point of each air route section between starting point to the end
Cloth parameter；
According to the wind field distribution parameter, the wind field space-time characterisation model is established.
Optionally, the wind field space-time characterisation model according to each air route section, establishes vehicle aerodynamics mould
Type, comprising:
The quality of wind field distribution parameter and aircraft in wind field space-time characterisation model based on each air route section,
It is dynamic to establish the aircraft air at the thrust and resistance coefficient of flight course, vertical load factor and inclination angle for aircraft
Mechanical model, wherein the vehicle aerodynamics model includes: speed of the aircraft in flight course, course angle, flies
Row path angle, horizontal position, height.
Optionally, described according to the vehicle aerodynamics model, it is calculated between the starting point to the end each
The oil consumption model of air route section, comprising:
According to speed, course angle, flight of the aircraft in the vehicle aerodynamics model in flight course
Path angle, horizontal position, height and vertical load factor and inclination angle, the initial time of air route section and termination time, meter
It calculates and obtains the oil consumption model of each air route section.
Optionally, the oil consumption model according to the quantity of aircraft and each air route section in each air route section,
The oil consumption evaluation function of each air route section is calculated, comprising:
According to the quantity of each upper aircraft of air route section, by the oil consumption model of each aircraft in each air route section
It is added, the oil consumption evaluation function of each air route section is calculated.
Optionally, the oil consumption evaluation function according to each air route section, is calculated the fuel cost of each air route section,
Include:
In formula, i, j any two way point, G between adjacent classificationi,jThe oil consumption generation of any air route section between adjacent classification
Valence；dijThe distance of any air route section between adjacent classification；PijThe oil consumption evaluation function of any air route section between adjacent classification.
Optionally, the fuel cost based on each air route section, determines the fuel cost minimum from starting point to the end
Air route route, comprising:
Fuel cost based on each air route section is determined using Di Jiesitela dijkstra's algorithm from starting point to end
The smallest air route route of fuel cost of point.
Optionally, described that numerical simulation is carried out to north and south wind field observation data, it obtains respectively navigating between starting point to the end
The wind field distribution parameter in section includes:
According to default division condition, classifies to north and south wind field observation data, obtain sorted north and south wind field
Observe data；
Numerical simulation is carried out to the sorted north and south wind field observation data respectively, obtains the starting point of each classification
The wind field distribution parameter of each air route section between to terminal.
Optionally, the default division condition is at least following a kind of: season, weather.
From the embodiment of the present invention it is found that establishing the wind field space-time characterisation mould of each air route section according to the wind field attribute data
Type establishes vehicle aerodynamics model, according to the aircraft according to the wind field space-time characterisation model of each air route section
The oil consumption model of each air route section between the starting point to the end is calculated in Aerodynamics Model, according to each air route section
Oil consumption model the oil consumption evaluation function of each air route section be calculated calculated according to the oil consumption evaluation function of each air route section
In the oil consumption generation from starting point to the end, is determined based on the fuel cost of each air route section to the fuel cost of each air route section
The smallest air route route of valence, due to considering the influence of wind field distribution factor, the fuel cost of the obtained starting point to the end
The smallest air route route is the minimum air route of oil consumption transportation cost.
Detailed description of the invention
Fig. 1 is the flow chart of the air traffic Track Design method based on wind field distribution shown in an exemplary embodiment；
Fig. 2 is the process of the air traffic Track Design method based on wind field distribution shown in another exemplary embodiment
Figure；
Fig. 3 is the route schematic diagram in Fig. 2 between the adjacent classification of starting point to the end between any two way point.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
Fig. 1 is the flow chart of the air traffic Track Design method based on wind field distribution shown in an exemplary embodiment,
This method comprises:
Step 101 obtains and counts wind field attribute data, according to wind field attribute data, it is established that puts each between to terminal
The wind field space-time characterisation model of air route section.
Wherein, wind field attribute data includes: north and south wind field observation data；Wherein, north and south wind field observation data are wind field
Coordinate position and the corresponding wind speed of coordinate position, wind direction；Wherein coordinate position is longitude, dimension；
Wherein, according to wind field attribute data, it is established that put the wind field space-time characterisation model of each air route section between to terminal
It before, can also include: pre- to delete comprising the obvious non-compliant bad point in wind speed, wind direction wind field attribute data
Processing；
Wherein, wind field space-time characterisation model includes wind field distribution parameter, such as north wind parameter, east wind parameter.
Step 102, according to the wind field space-time characterisation model of each air route section, establish vehicle aerodynamics model.
Wherein, the wind field distribution parameter (e.g., north wind parameter, east wind parameter) for including according to wind field space-time characterisation model, builds
Vertical vehicle aerodynamics model.
Step 103, according to vehicle aerodynamics model, the oil consumption of each air route section between starting point to the end is calculated
Model.
The oil consumption model of step 104, the quantity that aircraft is gone up according to each air route section and each air route section, is calculated each
The oil consumption evaluation function of air route section.
Wherein, according to the quantity representative of each upper aircraft of the air route section busy extent of air route section, each air route Duan Shangfei
The quantity of row device is more, and busy extent is higher, and oil consumption evaluation function is higher；Conversely, its oil consumption evaluation function is lower.
Step 105, according to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated.
Step 106, the fuel cost based on each air route section, determine the smallest boat of fuel cost from starting point to the end
Road route.
From above-described embodiment it is found that establishing the wind field space-time characterisation model of each air route section according to wind field attribute data, according to
The wind field space-time characterisation model of each air route section, establishes vehicle aerodynamics model, according to vehicle aerodynamics model,
The oil consumption model of each air route section between starting point to the end is calculated, each air route is calculated according to the oil consumption model of each air route section
The oil consumption evaluation function of section is calculated the fuel cost of each air route section, is based on each boat according to the oil consumption evaluation function of each air route section
The fuel cost in section, determines from the smallest air route route of fuel cost of starting point to the end, due to consider wind field distribution because
The influence of element, the smallest air route route of the fuel cost of obtained starting point to the end is the minimum air route of oil consumption transportation cost.
Fig. 2 is the process of the air traffic Track Design method based on wind field distribution shown in another exemplary embodiment
Figure, on the basis of the above embodiments, this method comprises:
Step 201, the starting point for obtaining air route, terminal, carry out classification processing to the way point between starting point, terminal, obtain
Way points at different levels.
As shown in figure 3, starting point is denoted as A, terminal is denoted as B, and way point is denoted as C, and the way point that will be close to starting point A is divided into
Level-one way point, the way point close to first order way point are divided into second level way point, and so on, obtain different stage
Way point.
Step 202 carries out sliding-model control to way points at different levels, determines at least one way point in each classification, respectively
Route of the air route section between each adjacent classification between any two way point.
As shown in figure 3, starting point A is to terminal to obtain way point at different levels by step 201 between B, to terminal by starting point A
Way point between every adjacent classification of B is sequentially connected, and is not connected between the way point of principle the same level of connection, way points at different levels
Between connect two-by-two, so obtain the discrete grid chart of way point of the starting point A to terminal between B, each air route in grid chart
Route of the section between each adjacent classification between any two way point.
As shown in figure 3, the every two way point between first order way point and second level way point is attached to obtain
By each air route section between first order way point and second level way point.
Step 203 obtains and counts wind field attribute data, according to wind field attribute data, it is established that puts each between to terminal
The wind field space-time characterisation model of air route section.
Wherein, wind field attribute data includes: north and south wind field observation data；Wherein, north and south wind field observation data are wind field
Coordinate position and the corresponding wind speed of coordinate position, wind direction；Wherein coordinate position is longitude, dimension；
Wherein, according to wind field attribute data, it is established that put the wind field space-time characterisation model of each air route section between to terminal
It before, can also include: pre- to delete comprising the obvious non-compliant bad point in wind speed, wind direction wind field attribute data
Processing.
The wind field distribution parameter of the Various Seasonal of each air route section, including north wind parameter vw,NorthWith east wind parameter vw,East, number
Value simulation formula are as follows:
In formula, vWFor the size of wind speed, χWFor wind direction.
Step 204, according to the wind field space-time characterisation model of each air route section, establish vehicle aerodynamics model.
Specifically, the matter of the wind field distribution parameter and aircraft in wind field space-time characterisation model based on each air route section
Amount, aircraft establish aircraft air force at the thrust and resistance coefficient of flight course, vertical load factor and inclination angle
Model is learned, wherein vehicle aerodynamics model includes: speed, course angle, flight path of the aircraft in flight course
Angle, horizontal position, height.
Wherein, vehicle aerodynamics model is mainly made of the differential equation of sextuple degree, and every dimension respectively represents
Speed v, course angle χ, flight path angle γ, horizontal position (longitude e, dimension n) and height h of the aircraft in flight course.
Wherein, speed v approximation value of the aircraft in flight course is vacuum value of velocity vTAS, when aircraft is with Chang Mahe
When number flight, vacuum value of velocity is definedIn formula, Ma is Mach number；κ is adiabatic exponent, value 1.4, R
It is 287.05 for air gas constant；T is the temperature at current time.
By the north wind v of the wind field distribution parameter in above-mentioned wind field space-time characterisation modelw,NorthWith east wind vw,East, substitute into and fly
Row device Aerodynamics Model, obtains following formula:
In formula, m is the quality of table aircraft, and T and D are respectively aircraft thrust and resistance suffered in flight course
Power, nzFor vertical load factor, μ is inclination angle, vw,North,vw,EastFor the north wind and east wind of wind field distribution parameter.
Specifically, above-mentioned aircraft can be civil aircraft.
Step 205, according to vehicle aerodynamics model, the oil consumption of each air route section between starting point to the end is calculated
Model.
Specifically, the speed according to the aircraft in vehicle aerodynamics model in flight course, course angle, fly
Row path angle, horizontal position, height and vertical load factor and inclination angle, the initial time of air route section and termination time,
The oil consumption model of each air route section is calculated.
Wherein, oil consumption model is mainly the objective function restricted by air route length, and formula is as follows:
In formula, x (t)=[v (t) χ (t) γ (t) e (t) n (t) h (t)]T, u (t)=[nZ(t)μ(t)]T, tfAnd t0It is any
The initial time of air route section and termination time.
The oil consumption model of step 206, the quantity that aircraft is gone up according to each air route section and each air route section, is calculated each
The oil consumption evaluation function of air route section.
Specifically, according to the lift and resistance coefficient of the upper each aircraft of air route section, each in each air route section section fly is calculated
The oil consumption model of row device；The oil consumption model of each upper each aircraft of air route section is added, the oil consumption evaluation of each air route section is calculated
Function.
BADA database has pre-saved the model of different aircraft and the lift of different model aircraft and resistance system
Number；
The lift and resistance coefficient that air route section aircraft is obtained from BADA database, substitute into above-mentioned oil consumption model, obtain
To the oil consumption model of a upper each aircraft of air route section, the oil consumption model of each upper each aircraft of air route section is added, is calculated each
The oil consumption evaluation function of air route section, oil consumption evaluation function formula are as follows:
In formula, PijFor oil consumption evaluation function, M is the quantity of the upper aircraft of air route section.
Step 207, according to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated.
Specifically, according to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated, comprising:
In formula, i, j any two way point, G between adjacent classificationi,jThe oil consumption generation of any air route section between adjacent classification
Valence；dijThe distance of any air route section between adjacent classification；PijThe oil consumption evaluation function of any air route section between adjacent classification.
As can be seen from the above equation, work as dijMinimum value be 0 when, Gi,jIt is meaningless, indicate that air route section can not fly.Each air route
The oil consumption evaluation function P of sectionijIt is bigger, fuel cost Gi,jAlso bigger.
Step 208, the fuel cost based on each air route section, determine the smallest boat of fuel cost from starting point to the end
Road route.
Specifically, the fuel cost based on each air route section, using Di Jiesitela dijkstra's algorithm, determine from starting point to
The smallest air route route of the fuel cost of terminal.
From above-described embodiment it is found that establishing the wind field space-time characterisation model of each air route section according to wind field attribute data, according to
The wind field space-time characterisation model of each air route section, establishes vehicle aerodynamics model, according to vehicle aerodynamics model,
The oil consumption model of each air route section between starting point to the end is calculated, each air route is calculated according to the oil consumption model of each air route section
The oil consumption evaluation function of section is calculated the fuel cost of each air route section, is based on each boat according to the oil consumption evaluation function of each air route section
The fuel cost in section, determines from the smallest air route route of fuel cost of starting point to the end, due to consider wind field distribution because
The influence of element, the smallest air route route of the fuel cost of obtained starting point to the end is the minimum air route of oil consumption transportation cost.
On the basis of the above embodiments,
Optionally, numerical simulation is carried out to north and south wind field observation data, obtains the wind of each air route section between starting point to the end
Field distribution parameter includes:
According to default division condition, classify to north and south wind field observation data, obtains sorted north and south wind field observation
Data；Numerical simulation is carried out to sorted north and south wind field observation data respectively, is obtained between the starting point to the end of each classification
The wind field distribution parameter of each air route section.
Optionally, it presets division condition and is at least following one kind: season, weather.
Those of ordinary skill in the art will appreciate that: realize that all or part of the steps of above-mentioned each method embodiment can lead to
The relevant hardware of program instruction is crossed to complete.Program above-mentioned can be stored in a computer readable storage medium.The journey
When being executed, execution includes the steps that above-mentioned each method embodiment to sequence；And storage medium above-mentioned include: ROM, RAM, magnetic disk or
The various media that can store program code such as person's CD.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (6)
1. a kind of air traffic Track Design method based on wind field distribution characterized by comprising
Wind field attribute data is obtained and counts, according to the wind field attribute data, it is established that put each air route section between to terminal
Wind field space-time characterisation model；
According to the wind field space-time characterisation model of each air route section, vehicle aerodynamics model is established；
According to the vehicle aerodynamics model, the oil consumption mould of each air route section between the starting point to the end is calculated
Type；
According to the oil consumption model of the quantity of each upper aircraft of air route section and each air route section, each air route is calculated
The oil consumption evaluation function of section；
According to the oil consumption evaluation function of each air route section, the fuel cost of each air route section is calculated；
Based on the fuel cost of each air route section, the smallest air route route of fuel cost from starting point to the end is determined；
The acquisition simultaneously counts wind field attribute data, according to the wind field attribute data, it is established that puts each air route between to terminal
The wind field space-time characterisation model of section, comprising: the wind field attribute data includes: north and south wind field observation data；According to default division
Condition classifies to north and south wind field observation data, obtains sorted north and south wind field observation data；After the classification
North and south wind field observation data carry out numerical simulation respectively, obtain each air route section between the starting point to the end of each classification
Wind field distribution parameter；According to the wind field distribution parameter, the wind field space-time characterisation model is established；
The oil consumption model according to the quantity of aircraft and each air route section in each air route section, is calculated each
The oil consumption evaluation function of air route section, comprising:, will be every in each air route section according to the quantity of each upper aircraft of air route section
The oil consumption model of a aircraft is added, and the oil consumption evaluation function of each air route section is calculated；It is described according to each air route
The fuel cost of each air route section is calculated in the oil consumption evaluation function of section, comprising:
In formula, i, j any two way point, G between adjacent classificationi,jThe fuel cost of any air route section between adjacent classification；dij
The distance of any air route section between adjacent classification；PijThe oil consumption evaluation function of any air route section between adjacent classification.
2. the method according to claim 1, wherein described obtain and count wind field attribute data, according to described
Wind field attribute data, it is established that put between to terminal before the wind field space-time characterisation model of each air route section, further includes:
Starting point, the terminal for obtaining air route, carry out classification processing to the way point between the starting point, terminal, obtain air routes at different levels
Point；
Sliding-model control is carried out to the way points at different levels, determines at least one way point in each classification；
Route of each air route section between each adjacent classification between any two way point.
3. the method according to claim 1, wherein the wind field space-time characterisation mould according to each air route section
Type establishes vehicle aerodynamics model, comprising:
Quality, the flight of wind field distribution parameter and aircraft in wind field space-time characterisation model based on each air route section
Device establishes the vehicle aerodynamics at the thrust and resistance coefficient of flight course, vertical load factor and inclination angle
Model, wherein the vehicle aerodynamics model includes: speed, course angle, flight road of the aircraft in flight course
Diameter angle, horizontal position, height.
4. according to the method described in claim 3, it is characterized in that, described according to the vehicle aerodynamics model, meter
It calculates and obtains the oil consumption model of each air route section between the starting point to the end, comprising:
According to speed, course angle, flight path of the aircraft in the vehicle aerodynamics model in flight course
Angle, horizontal position, height and vertical load factor and inclination angle, the initial time of air route section and termination time, calculate
To the oil consumption model of each air route section.
5. according to the method described in claim 2, it is characterized in that, the fuel cost based on each air route section, determines
From the smallest air route route of the fuel cost of starting point to the end, comprising:
Fuel cost based on each air route section is determined using Di Jiesitela dijkstra's algorithm from starting point to the end
The smallest air route route of fuel cost.
6. the method according to claim 1, wherein the default division condition is at least following a kind of: season,
Weather.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611168868.8A CN106781706B (en) | 2016-12-16 | 2016-12-16 | Air traffic Track Design method based on wind field distribution |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611168868.8A CN106781706B (en) | 2016-12-16 | 2016-12-16 | Air traffic Track Design method based on wind field distribution |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106781706A CN106781706A (en) | 2017-05-31 |
| CN106781706B true CN106781706B (en) | 2019-10-18 |
Family
ID=58892241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611168868.8A Active CN106781706B (en) | 2016-12-16 | 2016-12-16 | Air traffic Track Design method based on wind field distribution |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106781706B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107544532B (en) * | 2017-10-11 | 2020-07-03 | 中国人民解放军63653部队 | Long-range high-altitude flight mission planning method for low-altitude airship |
| CN111696389B (en) * | 2020-05-29 | 2021-07-02 | 航科院中宇（北京）新技术发展有限公司 | Aircraft fuel estimation method and system based on flight plan |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104160350A (en) * | 2012-01-09 | 2014-11-19 | 谷歌公司 | Relative positioning of balloons with altitude control and wind data |
| US9026275B1 (en) * | 2013-07-24 | 2015-05-05 | Shih-Yih Young | In-flight generation of RTA-compliant optimal profile descent paths |
| CN105718727A (en) * | 2016-01-19 | 2016-06-29 | 中国科学院光电研究院 | Stratospheric airship flight performance parameter estimation method and system |
-
2016
- 2016-12-16 CN CN201611168868.8A patent/CN106781706B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104160350A (en) * | 2012-01-09 | 2014-11-19 | 谷歌公司 | Relative positioning of balloons with altitude control and wind data |
| US9026275B1 (en) * | 2013-07-24 | 2015-05-05 | Shih-Yih Young | In-flight generation of RTA-compliant optimal profile descent paths |
| CN105718727A (en) * | 2016-01-19 | 2016-06-29 | 中国科学院光电研究院 | Stratospheric airship flight performance parameter estimation method and system |
Non-Patent Citations (9)
| Title |
|---|
| Ascending trajectory optimization of near-space airship based on Genetic Algorithm;Xiaoguang Di;《2013 IEEE 8th Conference on Industrial Electronics and Applications (ICIEA)》;20130725;918-922 * |
| K. Legrand.Aircraft trajectory planning under wind uncertainties.《2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)》.2016,1-9. * |
| Sake J. Bijlsma.•Optimal Aircraft Routing in General Wind Fields.《•Journal of Guidance, Control, and Dynamics 》.2012,第32卷(第3期),1025-1029. * |
| Short-term turning in presence of wind as a trajectory optimization problem;Kamran Turkoglu;《2014 IEEE Aerospace Conference》;20160619;1-6 * |
| 基于遗传算法的平流层飞艇航迹规划方法研究;吴雷;《航天返回与遥感》;20110228;第32卷(第1期);1-6 * |
| 基于风场信息的无人机在线航迹规划方法;屈耀红;《西北工业大学学报》;20120831;第30卷(第4期);576-581 * |
| 基于飞行数据分析的飞机燃油估计模型;刘婧;《万方数据库》;20121211;1-67 * |
| 急流风场中平流层飞艇放飞轨迹研究;张祥壮;《电子设计工程》;20140831;第22卷(第16期);11-14 * |
| 风力助航船舶航线优化模型及智能算法研究;李元奎;《万方数据库》;20150420;1-127 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106781706A (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111427100B (en) | Typhoon center positioning method and device and typhoon path generation method | |
| CN105487554B (en) | A kind of multi-rotor unmanned aerial vehicle is maked a return voyage path planning algorithm automatically | |
| CN110009037B (en) | Short-term engineering wind speed prediction method and system based on physical information coupling | |
| CN106225800B (en) | Environmentally friendly vehicle navigation path construction method based on real-time road condition information | |
| JP2018165930A (en) | Drone navigation device, drone navigation method and drone navigation program | |
| CN109978275B (en) | Extreme strong wind speed prediction method and system based on mixed CFD and deep learning | |
| CN106156267B (en) | A kind of lane stage enhancement type vector numerical map production method towards highway | |
| CN109050535A (en) | A kind of quick landform industry and mining city method based on vehicle attitude | |
| CN106781706B (en) | Air traffic Track Design method based on wind field distribution | |
| CN106768123A (en) | A kind of depopulated helicopter fuel oil predictor method | |
| CN108803656A (en) | A kind of flight control method and system based on complicated low latitude | |
| CN110059863A (en) | A kind of aircraft four-dimension route optimization method based on required arrival time | |
| Elias et al. | Automatic generation and application of landmarks in navigation data sets | |
| JP2021517290A (en) | Evaluation method of congestion degree of the route based on the optimum passage route under convective weather conditions | |
| CN111399084B (en) | High-altitude rapid flow extraction method based on three-dimensional wind field data | |
| CN106777875A (en) | A kind of air traffic Complexity Measurement method based on double-deck multistage network model | |
| CN114065407B (en) | Dynamic wake interval reduction method based on multi-element perception of airport wind speed | |
| CN113758478A (en) | Routing inspection flight planning method and system for long-distance power transmission and transformation line unmanned aerial vehicle | |
| CN109445462B (en) | Unmanned aerial vehicle robust path planning method in uncertain environment | |
| CN106772697A (en) | Sea of clouds natural landscape forecasting procedure and system | |
| CN115981376B (en) | Unmanned aerial vehicle long-time lag flight planning method and device based on airflow model | |
| CN104123671A (en) | Weather reference station zoning method | |
| CN110413656B (en) | Rapid flow axis automatic identification method based on high spatial resolution numerical mode | |
| Bharat et al. | Effects of high rise building complex on the wind flow patterns on surrounding urban pockets | |
| CN112882058B (en) | Shipborne laser radar obstacle detection method based on variable-size grid map |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210129 Address after: 100191 1409-038, 14th floor, shining building, 35 Xueyuan Road, Haidian District, Beijing Patentee after: Liangliang Hangke (Beijing) Technology Co.,Ltd. Address before: 100191 200, Ruxin building, Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Patentee before: BEIHANG University |