CN113609634A - Method for rapidly determining loading scheme of helicopter - Google Patents
Method for rapidly determining loading scheme of helicopter Download PDFInfo
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- CN113609634A CN113609634A CN202110433045.8A CN202110433045A CN113609634A CN 113609634 A CN113609634 A CN 113609634A CN 202110433045 A CN202110433045 A CN 202110433045A CN 113609634 A CN113609634 A CN 113609634A
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- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000005484 gravity Effects 0.000 claims abstract description 82
- 239000000446 fuel Substances 0.000 claims abstract description 31
- 239000000295 fuel oil Substances 0.000 claims abstract description 20
- 238000004364 calculation method Methods 0.000 claims description 4
- 239000003921 oil Substances 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000013502 data validation Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The invention belongs to the technical field of weight gravity center design of helicopters, and particularly relates to a method for quickly determining a loading scheme of a helicopter. The method specifically comprises the following steps: s1: forming a helicopter empty weight gravity center, a helicopter gravity center limit, a helicopter maximum weight limit, a set weight limit and gravity center position, a fuel weight limit and gravity center position, a load weight limit and gravity center position database; s2: estimating the fuel oil requirement under the flight mission according to the flight distance or flight time requirement; s3: confirming the weight of the unit, the loading weight and the fuel oil weight of the flight mission in the formed database; s4: calculating and determining the gravity center range of task loading according to the weight gravity center of the helicopter in the air, the weight gravity center of the set, the weight gravity center of fuel oil and the gravity center limit of the helicopter; s5: selecting loading type and determining loading scheme. The invention can be comprehensively applied to other helicopters in the future, can improve the attendance efficiency and safety of the helicopters, and has certain engineering application value.
Description
Technical Field
The invention belongs to the technical field of weight gravity center design of helicopters, and particularly relates to a method for quickly determining a loading scheme of a helicopter.
Background
Before the helicopter performs a flight mission, loading of fuel and mission load is carried out according to a loading scheme given by ground staff, including how much fuel is added, where the mission load is arranged, and the like. The loading scheme is determined according to the content and the method of the flight manual weight and balance chapters, and the calculation of the total center of gravity of the helicopter in the whole process of flying, flying and landing is carried out on the scheme, so that the safety of the helicopter in the whole flying process is ensured. The work is important, but is more complicated, whether the center of gravity of the whole aircraft in the states of before flight, during flight, landing and the like is in the center of gravity limiting range needs to be checked and calculated every time, the workload is large, and the efficiency is low.
Therefore, the invention provides a method for determining the loading scheme, which can rapidly complete the customization of the loading scheme and ensure that the center of gravity of the whole aircraft before flight, in flight and in the landing process is within the gravity center limit range.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to calculate the range of the loading center of gravity of a task meeting the requirement of center of gravity limitation by analyzing the influence of fuel consumption on the center of gravity of the whole helicopter based on the constraint condition of the center of gravity of the helicopter, and then quickly form a loading scheme meeting the requirements of loading and voyage.
The technical scheme of the invention is as follows: in order to achieve the above object, a method for quickly determining a loading scheme of a helicopter is provided, which is characterized by comprising the following steps:
s1: forming a helicopter empty weight gravity center, a helicopter gravity center limit, a helicopter maximum weight limit, a set weight limit and gravity center position, a fuel weight limit and gravity center position, a load weight limit and gravity center position database;
s2: estimating the fuel oil requirement under the flight mission according to the flight distance or flight time requirement;
s3: confirming the weight of the unit, the loading weight and the fuel oil weight of the flight mission in the formed database;
s4: calculating and determining the gravity center range of task loading according to the weight gravity center of the helicopter empty aircraft, the weight gravity center of the unit, the weight gravity center of fuel oil and the weight gravity center limit of the helicopter;
s5: selecting loading type and determining loading scheme.
In a possible embodiment, in the step S1, the database is formed, and only when the module is used for the first time, the input of relevant data is needed.
In a possible embodiment, in step S1, the helicopter airborne weight center of gravity is an airborne weight center of gravity on a helicopter crawler.
In one possible embodiment, in step S1, the helicopter center of gravity limits include a helicopter center of gravity front limit, a helicopter center of gravity rear limit, a helicopter center of gravity left limit, and a helicopter center of gravity right limit.
In one possible embodiment, in said step S2, the fuel demand is estimated according to the following empirical formula (1),
Gfuel oil＝k1X T or GFuel oil＝k2×L (1)
Wherein: gFuel oilFor fuel demand, k1Estimated fuel consumption per flight hour, k, for a helicopter2And F, flying the fuel consumption estimated value of kilometers for the helicopter, wherein T is the flight time of the flight mission of the helicopter, and L is the flight distance of the flight mission of the helicopter.
In one possible embodiment, in the step S4, the fuel weight center of gravity includes a mission required fuel condition, a 0 fuel condition.
In a possible embodiment, in step S4, the determined task load barycentric range is the intersection of the multi-state computed barycentric ranges.
In one possible embodiment, in said step S4, the center of gravity of the task load is calculated according to the following formula (2):
wherein G isAir machineFor empty requirement, GMachine setFor the unit requirements, GFuel oilFor fuel demand, GLoad(s)For load requirements, X is the center of gravity of the helicopter, XAir machineIs the weight center of gravity, X, of the empty aircraftMachine setIs the weight center of gravity, X, of the unitFuel oilIs the weight center of gravity of the fuel.
In a possible embodiment, in the step S5, the method specifically includes the following steps:
s501: selecting a task loading type;
s502: primarily determining a task loading gravity center;
s503: and determining the loading arrangement according to the priority level of the minimum distance between the single task loading gravity center and the task loading gravity center.
The invention has the beneficial technical effects that: the invention provides a method for quickly determining a loading scheme of a helicopter based on a gravity center constraint condition of the helicopter, explores the application of the method to a certain military transport helicopter, can be comprehensively applied to other helicopters in the future, can improve the attendance efficiency and safety of the helicopter, and has a certain engineering application value.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Take a weight-balancing scheme for a flight test as an example.
The flight mission is 400km in voyage, 2000kg of goods are carried, and a loading scheme is given
Step one, forming known data in a database module, wherein the known data are shown in a table 1;
TABLE 1 database Module related data
Step two, in the fuel estimation module, knowing the flight to solve the fuel requirement, and utilizing a formula GOil＝k2The X L inputs the flight requirement of 400km, and the helicopter flies fuel consumption k of kilometers25, calculating the requirement that the fuel oil is not less than 2000 kg;
step three, modifying and determining the known data of the database, and determining the weight of the unit of 270kg, the weight of the fuel oil of 2000kg and the weight of the load of 2000kg, which are shown in a table 2;
TABLE 2 database Module related data validation
In table 1, 270kg of the unit, 2000kg of fuel and 2000kg of load are input.
The gravity center calculation module is used for calculating the load gravity centers which correspond to the conditions of meeting the requirements of a front limit, a rear limit, 0 fuel and task fuel;
Xbefore loading＝((8000+270+2000+2000)×6-(8000×6.6+270×2.15+2000×7)) /2000＝3.120m
XAfter loading＝((8000+270+2000+2000)×6.5-(8000×6.6+270×2.15+2000×7)) /2000＝6.187m
XBefore loading＝((8000+270+2000+0)×6-(8000×6.6+270×2.15+0×7)) /2000＝4.119m
XAfter loading＝((8000+270+2000+0)×6.5-(8000×6.6+270×2.15+0×7)) /2000＝6.688m
Taking the intersection of the above calculation results, the gravity center range of the load is 4.119m to 6.187m, and the optimal gravity center is (4.119+6.187)/2 which is 5.153 m.
The loading scenario determines that a selection of the type of loading task (passenger or cargo) is made, where cargo transport is selected. The cargo loading takes the minimum distance from the center of gravity of the task loading as the priority, namely the cargo loading with 800kg at the cargo 2, 800kg at the cargo 3 and 400kg at the cargo 1 has the combined center of gravity of 5.42m, and the following loading scheme is obtained, and is shown in table 3.
TABLE 3 Loading scheme
| Name (R) | Weight/limit kg | Longitudinal center of gravity/limit m |
| Air machine | 8000 | 6.600 |
| Machine set | 270 | 2.150 |
| Fuel oil | 2000 | 7.000 |
| Cargo 1 | 400 | 3.500 |
| Goods 2 | 800 | 4.800 |
| Goods 3 | 800 | 7.000 |
| Takeoff state | 12270 | 6.375 |
| 0 fuel condition | 10270 | 6.253 |
The gravity center of the helicopter in the take-off state and the fuel oil state of the loading scheme is 6.375m, 6.253m and meets the requirement.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A method for rapidly determining a loading scheme of a helicopter is characterized by comprising the following steps:
s1: forming a helicopter empty weight gravity center, a helicopter gravity center limit, a helicopter maximum weight limit, a set weight limit and gravity center position, a fuel weight limit and gravity center position, a load weight limit and gravity center position database;
s2: estimating the fuel oil requirement under the flight mission according to the flight distance or flight time requirement;
s3: confirming the weight of the unit, the loading weight and the fuel oil weight of the flight mission in the formed database;
s4: calculating and determining the gravity center range of task loading according to the weight gravity center of the helicopter in the air, the weight gravity center of the set, the weight gravity center of fuel oil and the gravity center limit of the helicopter;
s5: selecting loading type and determining loading scheme.
2. A method for rapidly determining a loading scheme for a helicopter according to claim 1 wherein said database is created in step S1 only requiring the input of relevant data the first time the module is used.
3. A method for rapidly determining a loading scheme for a helicopter as claimed in claim 1 wherein in said step S1 said helicopter empty weight center is an empty weight center on a helicopter almanac.
4. A method for rapidly determining a loading plan for a helicopter as claimed in claim 1 wherein in said step S1 said helicopter center of gravity limits include a forward helicopter center of gravity limit, a rearward helicopter center of gravity limit, a left helicopter center of gravity limit and a right helicopter center of gravity limit.
5. A method for the rapid determination of the loading scheme of helicopters, according to claim 1, characterized in that, in said step S2, the fuel demand is estimated according to the following empirical formula (1),
Goil＝k1X T or GOil＝k2×L (1)
Wherein: gOilFor fuel demand, k1Estimated fuel consumption per flight hour, k, for a helicopter2And F, flying the fuel consumption estimation value of kilometers for the helicopter, wherein T is the flight time of the flight task of the helicopter, and L is the flight distance of the flight task of the helicopter.
6. A method for quickly determining a loading schedule for a helicopter as set forth in claim 1 wherein said fuel weight center of gravity comprises a mission required fuel condition, a 0 fuel condition in said step S4.
7. A method for rapidly determining a loading solution for a helicopter according to claim 1 and characterized in that in said step S4, said determining the range of centers of gravity of mission loading is the intersection of the ranges of centers of gravity of multi-state calculation.
8. A method for rapidly determining a loading solution for a helicopter according to claim 1 wherein in said step S4, the center of gravity of the mission loading is calculated according to the following equation (2):
wherein G isAir machineFor empty requirement, GMachine setFor the unit requirements, GFuel oilFor fuel demand, GLoad(s)For load requirements, X is the center of gravity of the helicopter, XAir machineIs the weight center of gravity, X, of the empty aircraftMachine setIs the weight center of gravity, X, of the unitFuel oilIs the weight center of gravity of the fuel.
9. The method for rapidly determining a loading scheme of a helicopter of claim 1, wherein in said step S5, the method specifically comprises the following steps:
s501: selecting a task loading type;
s502: primarily determining a task loading gravity center;
s503: and determining the loading arrangement according to the priority level of the minimum distance between the single task loading gravity center and the task loading gravity center.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110433045.8A CN113609634A (en) | 2021-04-20 | 2021-04-20 | Method for rapidly determining loading scheme of helicopter |
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| CN202110433045.8A CN113609634A (en) | 2021-04-20 | 2021-04-20 | Method for rapidly determining loading scheme of helicopter |
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| CN202110433045.8A Pending CN113609634A (en) | 2021-04-20 | 2021-04-20 | Method for rapidly determining loading scheme of helicopter |
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| CN110316362A (en) * | 2018-03-28 | 2019-10-11 | 刘保伸 | Double cabin structures of polynary purposes helicopter |
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2021
- 2021-04-20 CN CN202110433045.8A patent/CN113609634A/en active Pending
Patent Citations (7)
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| US20110283178A1 (en) * | 2009-12-03 | 2011-11-17 | Hook Grant | Facilitating electronic collection and maintenance of preflight documentation in helicopter air ambulance industry |
| CN104743111A (en) * | 2013-12-17 | 2015-07-01 | 空客直升机 | Rotorcraft fitted with an anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion |
| CN104229157A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Limit gravity center loading method of helicopter |
| CN108069047A (en) * | 2017-12-01 | 2018-05-25 | 中国直升机设计研究所 | A kind of method that helicopter is controlled to use center of gravity envelope curve |
| DE102018000037A1 (en) * | 2018-01-03 | 2019-07-04 | Klaus Mayer | Aircraft longitudinally displaceable propulsion turbines / propulsion turbine for weight balance and relocation of the aircraft's center of gravity during flight for single and multi-fuselage aircraft |
| CN110316362A (en) * | 2018-03-28 | 2019-10-11 | 刘保伸 | Double cabin structures of polynary purposes helicopter |
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