CN106777573A - A kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope - Google Patents
A kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope Download PDFInfo
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Abstract
A kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope,Studied by the movement mechanism that empty auxiliary fuel tank is delivered to Aircraft Air,The flying height of comprehensive analysis aircraft,Speed,The factor such as attitude angle and air wind speed delivers the influence of movement locus to empty auxiliary fuel tank,And calculate the aerodynamic characteristic of auxiliary fuel tank,Aircraft delivers the Halo vest characteristic of empty auxiliary fuel tank,Deliver the initial flight parameter of space-time auxiliary fuel tank,With reference to the mass property of empty auxiliary fuel tank,Set up the flight path simulating model for delivering space-time auxiliary fuel tank,Parameter in simulation model can be obtained by computer numerical value calculation or test measurement,The flying height of space-time auxiliary fuel tank is delivered finally by real-time simulated animation,Track,Attitude,The flight parameter such as speed and time,To obtain empty auxiliary fuel tank landing area Results,And then determine flying area scope,It is efficiently quick,And the landing scope of calculating is accurate,To determine that flying area provides support.
Description
Technical field
Range computation simulation technical field is delivered the present invention relates to aviation, more particularly to a kind of Aircraft Air delivers empty secondary oil
Case lands the emulation mode of scope.
Background technology
Currently for the research of Aircraft Air External Store thing, mainly both ways：One is auxiliary fuel tank, conventional bomb and system
When leading the store Combinations such as weapon and delivering, whether can be collided when aircraft and Halo vest and wait dispensing safety problem；Two is conventional
The range and accuracy at target etc. of the external stores such as bomb and guided weapon after transmitting is delivered are related to grinding for trajectory and guidance technology
Study carefully.Because though Aircraft Air delivers the dispensing safety problem that empty auxiliary fuel tank can consider with aircraft separate in launch process, due to
It is not belonging to weapon, therefore empty auxiliary fuel tank is delivered and leaves aircraft until the dropping trajectory of landing does not carry out correlative study.Together
When due to empty auxiliary fuel tank dimension volume it is relatively large, it is lightweight after fuel oil is used up, after Aircraft Air delivers empty auxiliary fuel tank, flying
Under machine interference in air flow, initial release altitude speed, air air speed influence, the landing point range that empty auxiliary fuel tank is likely to occur is larger.
In the past, to avoid dense population areas to ensure the people and property safety, general more options are desolate and uninhabited when delivering empty auxiliary fuel tank
Larger spatial domain place carry out, but the today increased in town and country high speed development and civil airline, select the difficulty in larger spatial domain
Increase therewith, required for dispensing spatial domain can be allowed to propose limitation higher, it is therefore desirable to predict that Aircraft Air delivers empty pair oil
The landing scope of case, for selection spatial domain size provides reference.From the point of view of published document, lack at present and Aircraft Air is delivered
The emulation mode of the landing scope of empty auxiliary fuel tank, the degree of becoming more meticulous for delivering flying area planning need to be improved.
The content of the invention
Technical problem solved by the invention is to provide a kind of Aircraft Air to deliver the emulation that empty auxiliary fuel tank lands scope
Method, to solve the shortcoming in above-mentioned background technology.
Technical problem solved by the invention is realized using following technical scheme：
A kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope, comprises the following steps that：
1) aerodynamic characteristic of auxiliary fuel tank is calculated
According to the geometric shape of auxiliary fuel tank, obtain the aerodynamic characteristic of auxiliary fuel tank using CFD numerical computations, auxiliary fuel tank it is pneumatic
Characteristic includes the lift coefficient, resistance coefficient, pitching moment coefficient, sideway force coefficient, the rolling power that change with the angle of attack and Mach number
Moment coefficient and yawing moment coefficient, area of reference take auxiliary fuel tank the maximum cross-section area, and reference length takes auxiliary fuel tank total length；Secondary oil
Case correlation aerodynamic characteristic can also be obtained by wind tunnel test；
2) the Halo vest characteristic that aircraft delivers empty auxiliary fuel tank is calculated
Aerodynamic characteristic, auxiliary fuel tank aerodynamic characteristic, empty auxiliary fuel tank mass property according to aircraft, using CFD numerical methods, meter
Calculate under the influence of aircraft flow field, in aircraft sky auxiliary fuel tank launch process, the Halo vest characteristic of aircraft, be guaranteed empty secondary oil
Case delivers the aircraft flight Mach number and the angle of attack of separation safety, while obtain sky auxiliary fuel tank being separated initially with respect to the dispensing of aircraft
Speed, the angle of attack and attitude angular dimensions；Wherein, the Halo vest characteristic of the empty auxiliary fuel tank of aircraft dispensing can also be obtained by wind tunnel test
；
3) the initial flight parameter for delivering space-time auxiliary fuel tank is calculated
The Halo vest characteristic of empty auxiliary fuel tank is delivered according to aircraft, aircraft allow to deliver the Mach number of empty auxiliary fuel tank and
In the range of angle of attack limitation, flying height, speed and the attitude angle of aircraft are given, the initial of relative aircraft is delivered with reference to empty auxiliary fuel tank
State, is calculated the initial flight parameter of the initial velocity, height and attitude angle of delivering space-time auxiliary fuel tank；
4) the flight path simulating model that Aircraft Air delivers space-time auxiliary fuel tank is set up
Initial velocity according to the dispensing of empty auxiliary fuel tank relative to winged axis, height, speed and attitude angle with reference to aircraft flight,
And consider to be superimposed the influence of air wind speed, the speed of relatively axle when asking sky auxiliary fuel tank to deliver：
VxE_0=V0×cosθ+V1+Vwx
VyE_0=V0×sinθ+Vwy
Wherein, VxE_0The relatively initial forward speed of axle when being delivered for empty auxiliary fuel tank；
VyE_0The relatively initial normal velocity of axle when being delivered for empty auxiliary fuel tank；
V1For aircraft equals winged true air speed；
VwxHorizontal component for air wind speed with respect to the earth's axis；
VwyVertical component for air wind speed with respect to the earth's axis；
When empty auxiliary fuel tank is delivered, the true air speed V of empty auxiliary fuel tankqInitial velocity V for empty auxiliary fuel tank relative to winged axis0With fly
The flat winged true air speed V of machine1Vector, i.e., the relatively forward speed V of axle when empty auxiliary fuel tank is deliveredxE_0With the normal direction of the relative earth's axis
Speed VyE_0Vector,
After empty auxiliary fuel tank is delivered, due to being influenceed by aerodynamic force and own wt, horizontal velocity reduces, and decrease speed is gradually
Increase, height declines, untill empty auxiliary fuel tank lands；
Aerodynamics evaluation of the empty auxiliary fuel tank in whole flight course be：
D=cx×q×S；L=cy×q×S；
The aerodynamic coefficient c of its hollow auxiliary fuel tankx、cyAccording to the Mach number M numerical value of current state, interpolation calculation is obtained；Speed
Pressureρ is the atmospheric density of place pressure altitude；
Track angle φ of the empty auxiliary fuel tank in whole flight course is calculated as：
Wherein, VxEIt is the horizontal velocity that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
VyEIt is the vertical speed that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
What empty auxiliary fuel tank was subject in whole flight course makes a concerted effort, and decomposes to the component that the earth's axis fastens and is：
FxE=-L × sin φ-D × cos φ；
FyE=L × cos φ-D × sin φ-G；
Wherein, FxEIt is empty auxiliary fuel tank stress in the horizontal component of ground shafting, it is horizontal forward for just；
FyEIt is empty auxiliary fuel tank stress in the vertical component of ground shafting, vertically upward for just；
Then in whole flight course, the Flight Acceleration fastened in the earth's axis is empty auxiliary fuel tank：
axE=FxE/m；
ayE=FyE/m；
Wherein, m is the quality of sky auxiliary fuel tank；
axEIt is the horizontal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
ayEIt is the normal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
Acceleration in the shafting of base area, integration obtains the flying speed fastened in the earth's axis and is：
VxE=∫ axEdt；
VyE=∫ ayEdt；
Then the speed of base area shafting, integration obtains the flying distance fastened in the earth's axis and is：
Lx=∫ VxEdt；
Ly=∫ VyEdt；
By numerical integration iteration, as the vertical range L of empty auxiliary fuel tankyVariable quantity be equal to when empty auxiliary fuel tank is delivered just
During beginning height, then empty auxiliary fuel tank landing, the horizontal range of this space-time auxiliary fuel tank flight is Lx；
The computational methods of the lateral distance of empty auxiliary fuel tank are consistent with the computational methods of the horizontal range that empty auxiliary fuel tank flies, only
Initial level speed need to be replaced with corresponding initial side velocity and be superimposed atmospheric side wind effect, so as to set up aircraft sky
The middle flight path simulating model for delivering space-time auxiliary fuel tank, is then input into simulation parameter in flight path simulating model, obtains final product
Empty auxiliary fuel tank landing scope is delivered to Aircraft Air.
Beneficial effect：The present invention delivers the Halo vest of empty auxiliary fuel tank by calculating the aerodynamic characteristic of auxiliary fuel tank, aircraft
Characteristic, the initial flight parameter for delivering space-time auxiliary fuel tank, with reference to the mass property of empty auxiliary fuel tank, set up and deliver space-time auxiliary fuel tank
Flight path simulating model, is input into simulation parameter in flight path simulating model, that is, obtain Aircraft Air and deliver empty auxiliary fuel tank
Landing scope, it is efficiently quick, and the landing scope for calculating is accurate, to determine that flying area provides support.
Specific embodiment
In order that technological means, creation characteristic, reached purpose and effect that the present invention is realized are easy to understand, tie below
Specific embodiment is closed, the present invention is expanded on further.
A kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope, by delivering empty auxiliary fuel tank to Aircraft Air
Movement mechanism research, the factor such as the flying height of comprehensive analysis aircraft, speed, attitude angle and air wind speed thrown empty auxiliary fuel tank
The influence of movement locus is put, and calculates the aerodynamic characteristic of auxiliary fuel tank, aircraft and delivered the Halo vest characteristic of empty auxiliary fuel tank, deliver
The initial flight parameter of space-time auxiliary fuel tank, with reference to the mass property of empty auxiliary fuel tank, sets up the flight path for delivering space-time auxiliary fuel tank
Simulation model, the parameter in simulation model can be obtained by computer numerical value calculation or test measurement, finally by real-time simulation
The flight parameters such as flying height, track, attitude, speed and the time of dispensing space-time auxiliary fuel tank are calculated, to obtain empty auxiliary fuel tank
Landing area Results, and then determine flying area scope；Comprise the following steps that：
1) aerodynamic characteristic of auxiliary fuel tank is calculated
According to the geometric shape of auxiliary fuel tank, the aerodynamic characteristic of auxiliary fuel tank is obtained using CFD numerical computations, it is main to include with meeting
Lift coefficient, resistance coefficient, pitching moment coefficient, sideway force coefficient, rolling moment coefficient and driftage that angle and Mach number change
Moment coefficient, area of reference takes auxiliary fuel tank the maximum cross-section area, and reference length takes auxiliary fuel tank total length；The related pneumatic spy of auxiliary fuel tank
Property can also be obtained by wind tunnel test；
2) the Halo vest characteristic that aircraft delivers empty auxiliary fuel tank is calculated
Aerodynamic characteristic, auxiliary fuel tank aerodynamic characteristic, empty auxiliary fuel tank mass property according to aircraft, using CFD numerical methods, meter
Calculate under the influence of aircraft flow field, in aircraft sky auxiliary fuel tank launch process, the Halo vest characteristic of aircraft, by calculating, is obtained
Ensure that empty auxiliary fuel tank delivers the aircraft flight Mach number and the angle of attack of separation safety, while obtaining throwing of the sky auxiliary fuel tank with respect to aircraft
Put separation initial velocity, the angle of attack and attitude angular dimensions；Wherein, the Halo vest characteristic of the empty auxiliary fuel tank of aircraft dispensing can also pass through
Wind tunnel test is obtained；
3) the initial flight parameter for delivering space-time auxiliary fuel tank is calculated
The Halo vest characteristic of empty auxiliary fuel tank is delivered according to aircraft, aircraft allow to deliver the Mach number of empty auxiliary fuel tank and
In the range of angle of attack limitation, flying height, speed and the attitude angle of aircraft are given, the initial of relative aircraft is delivered with reference to empty auxiliary fuel tank
State, is calculated the initial flight parameter of the initial velocity, height and attitude angle of delivering space-time auxiliary fuel tank；
4) the flight path simulating model for delivering space-time auxiliary fuel tank is set up
Initial velocity according to the dispensing of empty auxiliary fuel tank relative to winged axis, height, speed and attitude angle with reference to aircraft flight,
And consider to be superimposed the influence of air wind speed, obtain the speed of relatively axle when sky auxiliary fuel tank is delivered：
VxE_0=V0×cosθ+V1+Vwx
VyE_0=V0×sinθ+Vwy
Wherein, VxE_0The relatively initial forward speed of axle when being delivered for empty auxiliary fuel tank；
VyE_0The relatively initial normal velocity of axle when being delivered for empty auxiliary fuel tank；
V1For aircraft equals winged true air speed；
VwxHorizontal component for air wind speed with respect to the earth's axis；
VwyVertical component for air wind speed with respect to the earth's axis；
When empty auxiliary fuel tank is delivered, the true air speed V of empty auxiliary fuel tankqInitial velocity V for empty auxiliary fuel tank relative to winged axis0With fly
The flat winged true air speed V of machine1Vector, i.e., the relatively forward speed V of axle when empty auxiliary fuel tank is deliveredxE_0With the normal direction of the relative earth's axis
Speed VyE_0Vector：
After empty auxiliary fuel tank is delivered, due to being influenceed by aerodynamic force and own wt, horizontal velocity reduces, and decrease speed is gradually
Increase, height declines, untill empty auxiliary fuel tank lands；
Aerodynamics evaluation of the empty auxiliary fuel tank in whole flight course be：
D=cx×q×S；L=cy×q×S；
The aerodynamic coefficient c of its hollow auxiliary fuel tankx、cyAccording to the Mach number M numerical value of current state, interpolation calculation is obtained；Speed
Pressureρ is the atmospheric density of place pressure altitude；
Track angle φ of the empty auxiliary fuel tank in whole flight course is calculated as：
Wherein, VxEIt is the horizontal velocity that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
VyEIt is the vertical speed that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
What empty auxiliary fuel tank was subject in whole flight course makes a concerted effort, and decomposes to the component that the earth's axis fastens and is：
FxE=-L × sin φ-D × cos φ；
FyE=L × cos φ-D × sin φ-G；
Wherein, FxEIt is empty auxiliary fuel tank stress in the horizontal component of ground shafting, it is horizontal forward for just；
FyEIt is empty auxiliary fuel tank stress in the vertical component of ground shafting, vertically upward for just；
Then in whole flight course, the Flight Acceleration fastened in the earth's axis is empty auxiliary fuel tank：
axE=FxE/m；
ayE=FyE/m；
Wherein, m is the quality of sky auxiliary fuel tank；
axEIt is the horizontal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
ayEIt is the normal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
Acceleration in the shafting of base area, integration obtains the flying speed fastened in the earth's axis and is：
VxE=∫ axEdt；
VyE=∫ ayEdt；
Then the speed of base area shafting, integration obtains the flying distance fastened in the earth's axis and is：
Lx=∫ VxEdt；
Ly=∫ VyEdt；
By numerical integration iteration, as the vertical range L of empty auxiliary fuel tankyVariable quantity be equal to when empty auxiliary fuel tank is delivered just
During beginning height, then empty auxiliary fuel tank landing, the horizontal range of this space-time auxiliary fuel tank flight is Lx；
The computational methods of the lateral distance of empty auxiliary fuel tank are consistent with the computational methods of the horizontal range that empty auxiliary fuel tank flies, only
Initial level speed need to be replaced with corresponding initial side velocity and be superimposed atmospheric side wind effect, so that when setting up dispensing
The flight path simulating model of empty auxiliary fuel tank, the empty secondary oil of flat winged dispensing is carried out with aircraft in flying height 3km, table speed 600km/h
As a example by case, it is considered under conditions of air wind speed 30m/s, by above-mentioned emulation mode carry out calculating have leisure auxiliary fuel tank deliver landing model
Enclose, that is, it is 6.1km × 4.4km to carry out the aerial required field domain for delivering empty auxiliary fuel tank, to determine that flying area provides support.
General principle of the invention and principal character and advantages of the present invention has been shown and described above.The technology of the industry
Personnel it should be appreciated that the present invention is not limited to the above embodiments, simply explanation described in above-described embodiment and specification this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and modifications of the present invention are possible, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appending claims and its
Equivalent thereof.
Claims (4)
1. a kind of Aircraft Air delivers the emulation mode that empty auxiliary fuel tank lands scope, it is characterised in that comprise the following steps that：
1) aerodynamic characteristic of auxiliary fuel tank is calculated
According to the geometric shape of auxiliary fuel tank, the aerodynamic characteristic of auxiliary fuel tank, the aerodynamic characteristic of auxiliary fuel tank are obtained using CFD numerical computations
Including the lift coefficient, resistance coefficient, pitching moment coefficient, sideway force coefficient, the rolling moment system that change with the angle of attack and Mach number
Number and yawing moment coefficient；
2) the Halo vest characteristic that aircraft delivers empty auxiliary fuel tank is calculated
The aerodynamic characteristic of aerodynamic characteristic, auxiliary fuel tank according to aircraft, empty auxiliary fuel tank mass property, using CFD numerical methods, calculate
Under the influence of aircraft flow field, in aircraft sky auxiliary fuel tank launch process, the Halo vest characteristic of aircraft, be guaranteed sky auxiliary fuel tank
The aircraft flight Mach number and the angle of attack of separation safety are delivered, while obtain sky auxiliary fuel tank separates initial speed with respect to the dispensing of aircraft
Degree, the angle of attack and attitude angular dimensions；
3) the initial flight parameter for delivering space-time auxiliary fuel tank is calculated
The Halo vest characteristic of empty auxiliary fuel tank is delivered according to aircraft, allows to deliver the Mach number and the angle of attack of empty auxiliary fuel tank in aircraft
In the range of limitation, flying height, speed and the attitude angle of aircraft are given, the initial shape of relative aircraft is delivered with reference to empty auxiliary fuel tank
State, is calculated the initial flight parameter of the initial velocity, height and attitude angle of delivering space-time auxiliary fuel tank；
4) the flight path simulating model that Aircraft Air delivers space-time auxiliary fuel tank is set up
Initial velocity relative to winged axis, height, speed and attitude angle with reference to aircraft flight are delivered according to empty auxiliary fuel tank, and is examined
Consider the influence of superposition air wind speed, the speed of relatively axle when asking sky auxiliary fuel tank to deliver：
VxE_0=V0×cosθ+V1+Vwx
VyE_0=V0×sinθ+Vwy
Wherein, VxE_0The relatively initial forward speed of axle when being delivered for empty auxiliary fuel tank；
VyE_0The relatively initial normal velocity of axle when being delivered for empty auxiliary fuel tank；
V1For aircraft equals winged true air speed；
VwxHorizontal component for air wind speed with respect to the earth's axis；
VwyVertical component for air wind speed with respect to the earth's axis；
When empty auxiliary fuel tank is delivered, the true air speed V of empty auxiliary fuel tankqInitial velocity V for empty auxiliary fuel tank relative to winged axis0It is flat with aircraft
Fly true air speed V1Vector, i.e., the relatively forward speed V of axle when empty auxiliary fuel tank is deliveredxE_0With the normal velocity of the relative earth's axis
VyE_0Vector,
After empty auxiliary fuel tank is delivered, due to being influenceed by aerodynamic force and own wt, horizontal velocity reduces, and decrease speed gradually increases
Plus, height declines, untill empty auxiliary fuel tank lands；
Aerodynamics evaluation of the empty auxiliary fuel tank in whole flight course be：
D=cx×q×S；L=cy×q×S；
Wherein, the aerodynamic coefficient c of empty auxiliary fuel tankx、cyAccording to the Mach number M numerical value of current state, interpolation calculation is obtained；Ram compressionρ is the atmospheric density of place pressure altitude；
Track angle φ of the empty auxiliary fuel tank in whole flight course is calculated as：
Wherein, VxEIt is the horizontal velocity that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
VyEIt is the vertical speed that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
What empty auxiliary fuel tank was subject in whole flight course makes a concerted effort, and decomposes to the component that the earth's axis fastens and is：
FxE=-L × sin φ-D × cos φ；
FyE=L × cos φ-D × sin φ-G；
Wherein, FxEIt is empty auxiliary fuel tank stress in the horizontal component of ground shafting, it is horizontal forward for just；
FyEIt is empty auxiliary fuel tank stress in the vertical component of ground shafting, vertically upward for just；
Then in whole flight course, the Flight Acceleration fastened in the earth's axis is empty auxiliary fuel tank：
axE=FxE/m；
ayE=FyE/m；
Wherein, m is the quality of sky auxiliary fuel tank；
axEIt is the horizontal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, it is horizontal forward for just；
ayEIt is the normal acceleration that empty auxiliary fuel tank is fastened in the earth's axis, vertically upward for just；
Acceleration in the shafting of base area, integration obtains the flying speed fastened in the earth's axis and is：
VxE=∫ axEdt；
VyE=∫ ayEdt；
Then the speed of base area shafting, integration obtains the flying distance fastened in the earth's axis and is：
Lx=∫ VxEdt；
Ly=∫ VyEdt；
By numerical integration iteration, as the vertical range L of empty auxiliary fuel tankyVariable quantity be equal to initial height when empty auxiliary fuel tank is delivered
When spending, then empty auxiliary fuel tank landing, the horizontal range of this space-time auxiliary fuel tank flight is Lx；
The computational methods of the lateral distance of empty auxiliary fuel tank are consistent with the computational methods of the horizontal range that empty auxiliary fuel tank flies, it is only necessary to will
Initial level speed replaces with corresponding initial side velocity and is superimposed atmospheric side wind effect, is thrown so as to set up Aircraft Air
The flight path simulating model of space-time auxiliary fuel tank is put, then simulation parameter is input into flight path simulating model, that is, is flown
Machine delivers empty auxiliary fuel tank landing scope in the air.
2. a kind of Aircraft Air according to claim 1 delivers the emulation mode that empty auxiliary fuel tank lands scope, and its feature exists
In step 1) in, the area of reference of the geometric shape of auxiliary fuel tank takes auxiliary fuel tank the maximum cross-section area, and it is total that reference length takes auxiliary fuel tank
Length.
3. a kind of Aircraft Air according to claim 1 delivers the emulation mode that empty auxiliary fuel tank lands scope, and its feature exists
In step 1) in, auxiliary fuel tank correlation aerodynamic characteristic can be obtained by wind tunnel test.
4. a kind of Aircraft Air according to claim 1 delivers the emulation mode that empty auxiliary fuel tank lands scope, and its feature exists
In step 2) in, the Halo vest characteristic that aircraft delivers empty auxiliary fuel tank can be obtained by wind tunnel test.
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2016
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009101841A1 (en) * | 2008-02-14 | 2009-08-20 | Sumitomo Rubber Industries, Ltd. | Method of determining parameter used in air pressure reduction detecting method |
| CN102789526A (en) * | 2012-07-12 | 2012-11-21 | 中国人民解放军装甲兵工程学院 | Analog calculating method for landing buffering process of equipment air drop |
| CN105260508A (en) * | 2015-09-16 | 2016-01-20 | 南京航空航天大学 | Method for predicting optimal release point of airdropped material |
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| PRADEEP KUMAR 等: "GPS Based Navigation Design For a Bio Inspired Precision Air Drop System", 《INTERNATIONAL CONFERENCE ONCOMPUTING，COMMUNICATION AND AUTOMATION》 * |
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