Automatic ballast method in helicopter flight test

Abstract

The present application belongs to the technical field of helicopter overall design, and particularly relates to a method for automatically balancing weight in a helicopter test flight test. The method comprises the following steps: step one, determining the empty weight and gravity center data of the helicopter; step two, determining the position and weight information of all positions capable of being balanced on the helicopter; step three, determining the weight and gravity center data of the helicopter crew members; step four, determining the fuel weight and gravity center data of the helicopter; step five, confirming the task fuel quantity according to the requirements of the test flight subject task list; step six, determining the implementation workload of each balancing block; step seven, taking the data in steps one to five as the basis for calculation to calculate the total machine weight and gravity center data; step eight, determining the target weight and target gravity center as the constraint conditions according to the requirements of the test flight subject task list; step nine, taking the minimum value of the implementation workload in step six as the optimization target; and step ten, performing optimization calculation on the data in steps seven, eight and nine by using a genetic algorithm to obtain an optimal balancing scheme.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of helicopter overall design, and particularly relates to an automatic weight distribution method in helicopter flight test. BACKGROUND

[0002] In helicopter flight test, different flight subjects have different weight and gravity center requirements for the helicopter, so the helicopter needs to be weighted according to the flight test mission before each flight test, and the flight test data obtained in this flight is valid only when the flight test mission is met after weighting.

[0003] At present, a large number of helicopters have been designed in China, and in the past flight test of these helicopters, the weight engineers give the flight weighting sheet, and the maintenance personnel implement the weighting work according to the flight weighting sheet. The existing flight weighting method is manually calculated by weight engineers, and the workload of the maintenance personnel in the weighting design process is not considered, which often causes slow manual weighting and large workload of the maintenance personnel in implementing the weighting work. SUMMARY

[0004] The purpose of the present application is to solve the problems of complex original helicopter weighting process, large workload of the maintenance personnel in weighting, and low efficiency of weighting implementation in helicopter flight test. In this paper, an automatic weighting method in helicopter flight test is designed, and the computer algorithm is used to automatically give the weighting scheme with the minimum workload of the maintenance personnel as the optimization target, to meet the requirements of the flight test mission sheet, improve the weighting efficiency, reduce the weighting time, and increase the flight test efficiency.

[0005] To achieve the above purpose, the present application adopts the following technical solutions.

[0006] An automatic weighting method in helicopter flight test, the method comprising:

[0007] Step one, determining the empty weight and gravity center data of the helicopter;

[0008] Step two, determining all positions and weight information of the helicopter that can be weighted;

[0009] Step three, determining the weight and gravity center data of the helicopter crew members;

[0010] Step four, determining the fuel weight and gravity center data of the helicopter;

[0011] Step five, confirming the task fuel according to the requirements of the flight subject mission sheet;

[0012] Step six, determining the implementation workload of each weighting block;

[0013] Step seven, using the data in steps one to five as the calculation basis to calculate the total weight and gravity center data of the helicopter;

[0014] Step eight, according to the flight test subject task sheet requirements, determine the target weight, target gravity as a constraint condition;

[0015] Step nine, the minimum value of the implementation of step six as the optimization goal;

[0016] Step ten, step seven, eight, nine data using genetic algorithm optimization calculation, the optimal counterweight scheme.

[0017] Further, 1) determine the helicopter empty weight Wempty, empty longitudinal gravity position Xempty, empty lateral gravity position Yempty, empty vertical gravity position Zempty;

[0018] 2) determine all the information of the helicopter can be counterweight position and weight, including, counterweight block number i, counterweight block weight Wbalancei, counterweight block longitudinal position Xbalancei, counterweight block lateral position Ybalancei, counterweight block vertical position information Zbalancei, i∈(1,n);

[0019] 3) determine the crew weight W Pilot, crew longitudinal gravity position X Pilot, empty lateral gravity position YPilot, empty vertical gravity position Z Pilot.

[0020] Further, step four is:

[0021] According to the arrangement of the fuel tank on the machine and the fuel consumption sequence, determine the fuel gravity position function corresponding to different fuel weight, as follows:

[0022]

[0023] Where Xfule represents the longitudinal gravity of fuel, Yfuel represents the lateral gravity of fuel, Zfuel represents the vertical gravity of fuel, and Wfuel represents the weight of fuel.

[0024] Further, step five is:

[0025] According to the flight test subject task sheet requirements, determine the task fuel Wfuel, according to the fuel gravity position function corresponding to different fuel weight in step four, calculate the fuel gravity Xfule, Yfule, Zfule data in each direction from the task fuel Wfuel.

[0026] Further, step six is:

[0027] According to the sum of the results of the machine maintenance and installation time, the work quantity of each counterweight block is quantified, and the counterweight work time of each counterweight block is represented by Timei.

[0028] Further, step seven is specifically:

[0029] Calculate the total weight of the aircraft, the longitudinal center of gravity of the aircraft, the lateral center of gravity of the aircraft, the vertical center of gravity of the aircraft, the calculation formula is as follows, wherein W is the total weight of the helicopter, X is the longitudinal center of gravity of the helicopter, Y is the lateral center of gravity of the helicopter, and Z is the vertical center of gravity of the helicopter;

[0030] W=Wempty+∑Wbalancei+Wfuel+Wpilot

[0031] X=(Wempty*Xempty+∑(Wbalancei*Xbalancei)+Wfuel*Xfuel+Wpilot*Xpilot) / W

[0032] Y=(Wempty*Yempty+∑(Wbalancei*Ybalancei)+Wfuel*Yfuel+Wpilot*Ypilot) / W

[0033] Z=(Wempty*Zempty+∑(Wbalancei*Zbalancei)+Wfuel*Zfuel+Wpilot*Zpilot) / W.

[0034] Further, step eight is specifically:

[0035] According to the flight test subject task sheet, the target weight Wtarget, the target longitudinal center of gravity Xtarget, the target lateral center of gravity Ytarget, and the target vertical center of gravity Ztarget are determined; the target weight and the target center of gravity are taken as constraint conditions, and the specific constraint conditions are as follows

[0036]

[0037] The constraint condition specifically requires that the total weight W of the aircraft is equal to the target weight Wtarget, the longitudinal center of gravity X of the aircraft is within the target longitudinal center of gravity Xtarget±3mm, the lateral center of gravity Y of the aircraft is within the target lateral center of gravity Ytarget±3mm, and the vertical center of gravity Z of the aircraft is within the target vertical center of gravity Ztarget±3mm.

[0038] Further, step nine is specifically:

[0039] The minimum workload time of the maintenance counterweight is taken as the optimization target, and the optimization objective function is as follows:

[0040]

[0041] The present application provides an automatic ballast method in helicopter flight test, through compiling automatic ballast algorithm, using calculation program to implement automatic ballast, and taking minimum maintenance workload as optimization target in automatic ballast algorithm, ballast scheme is given. Through the above automatic ballast method, the workload of weight engineers can be reduced, the previous manual ballast scheme is changed into simple data input work, and the time for formulating ballast scheme is saved by using computer automatic calculation. In addition, since the automatic ballast algorithm takes maintenance workload as optimization target, the time for implementing ballast scheme by maintenance is also reduced, and the efficiency of each flight ballast is improved as a whole. BRIEF DESCRIPTION OF DRAWINGS

[0042] Figure 1 A flowchart of an automatic ballast method in helicopter flight test is provided for the embodiment of the present application.

[0043] Figure 2 A ballast workload diagram is provided for the embodiment of the present application. DETAILED DESCRIPTION

[0044] The technical solutions of the present application will be described in detail below with reference to the drawings.

[0045] The present application provides an automatic ballast method in helicopter flight test, which automatically gives flight ballast scheme:

[0046] Step one, determine the empty weight and gravity center data of the helicopter;

[0047] Step two, determine all positions and weight information of the helicopter which can be ballasted;

[0048] Step three, determine the weight and gravity center data of the helicopter crew members;

[0049] Step four, determine the weight and gravity center data of the helicopter fuel;

[0050] Step five, according to the requirements of the flight mission sheet, confirm the task fuel quantity;

[0051] Step six, determine the implementation workload of each ballast block;

[0052] Step seven, use the data in steps one to five as calculation basis to calculate the total weight and gravity center data of the helicopter;

[0053] Step eight, according to the requirements of the flight subject mission sheet, determine the target weight, target gravity center and other constraint conditions;

[0054] Step nine, take the minimum real-time workload in step six as the optimization target;

[0055] Step ten, use genetic algorithm to optimize the data in steps seven, eight and nine, and obtain the ballast calculation result, i.e. the ballast scheme.

[0056] Step eleven, the maintenance department implements the weight balancing on the helicopter according to the weight balancing scheme;

[0057] Step twelve, the weight balancing test flight is completed.

[0058] Specifically,

[0059] As Figure 1 shown, the automatic weight balancing method for the helicopter test flight test according to the application, the specific use process includes the following steps.

[0060] 1) Determine the empty weight of the helicopter Wempty, the longitudinal center of gravity position of the empty machine Xempty, the lateral center of gravity position of the empty machine Yempty, the vertical center of gravity position of the empty machine Zempty;

[0061] 2) Determine all positions and weight information of the helicopter that can be balanced, including, weight block number i, weight block weight Wbalancei, weight block longitudinal position Xbalancei, weight block lateral position Ybalancei, weight block vertical position information Zbalancei, i∈(1,n);

[0062] 3) Determine the weight of the crew W Pilot, the longitudinal center of gravity position of the crew X Pilot, the lateral center of gravity position of the empty machine Y Pilot, the vertical center of gravity position of the empty machine Z Pilot;

[0063] 4) According to the arrangement of the fuel tank on the machine and the fuel consumption sequence, determine the fuel center of gravity position function corresponding to different fuel weight, as shown below:

[0064]

[0065] Where Xfule represents the longitudinal center of gravity of the fuel, Yfuel represents the lateral center of gravity of the fuel, Zfuel represents the vertical center of gravity of the fuel, and Wfuel represents the fuel weight.

[0066] 5) According to the test flight subject task list requirements, the task fuel Wfuel is clear, and the fuel center of gravity Xfule, Yfule, Zfule data in each direction is calculated from the task fuel Wfuel according to the function in 4).

[0067] 6) According to the sum of the maintenance handling time and the installation time, the work load of each weight block is quantified, and the weight block work time is represented by Timei.

[0068] The weight balancing work load statistical table is issued to the maintenance department, and the implementation work load of each weight block is calculated. The main content of the weight balancing work load statistical table is as follows Figure 2The work load statistics table is sent to each maintenance worker, who fills in the carrying time and installation time, etc. and all the data filled in by the maintenance workers are counted.

[0069] 7) According to the data in the above 5 steps, the total weight of the machine, the longitudinal center of gravity of the machine, the lateral center of gravity of the machine, and the vertical center of gravity of the machine are calculated, and the calculation formula is as follows, wherein W is the total weight of the helicopter, X is the longitudinal center of gravity of the helicopter, Y is the lateral center of gravity of the helicopter, and Z is the vertical center of gravity of the helicopter;

[0070] W = Wempty + ∑Wbalancei + Wfuel + Wpilot

[0071] X = (Wempty * Xempty + ∑(Wbalancei * Xbalancei) + Wfuel * Xfuel + Wpilot * Xpilot) / W

[0072] Y = (Wempty * Yempty + ∑(Wbalancei * Ybalancei) + Wfuel * Yfuel + Wpilot * Ypilot) / W

[0073] Z = (Wempty * Zempty + ∑(Wbalancei * Zbalancei) + Wfuel * Zfuel + Wpilot * Zpilot) / W

[0074] 8) According to the requirements of the test flight subject task list, the target weight Wtarget, the target longitudinal center of gravity Xtarget, the target lateral center of gravity Ytarget, and the target vertical center of gravity Ztarget are determined; the target weight and the target center of gravity are taken as constraint conditions, and the specific constraint conditions are as shown below

[0075]

[0076] The specific requirements of the constraint conditions are that the total weight of the machine W is equal to the target weight Wtarget, the longitudinal center of gravity X of the machine is within the range of the target longitudinal center of gravity Xtarget ± 3 mm, the lateral center of gravity Y of the machine is within the range of the target lateral center of gravity Ytarget ± 3 mm, and the vertical center of gravity Z of the machine is within the range of the target vertical center of gravity Ztarget ± 3 mm.

[0077] 9) The minimum work load time of the maintenance weight is taken as the optimization target, and the optimization objective function is as shown below

[0078]

[0079] 10) According to the constraints in 9) above and the optimization objective function in 10), an optimization calculation is performed by using a genetic algorithm to obtain a calculation result, which can reflect the weight information at each position, i.e., a weight scheme is obtained.

[0080] 11) The maintenance personnel implement the weight on the helicopter according to the weight scheme;

[0081] 12) The weight test flight is completed.

[0082] The automatic weight method for a helicopter test flight test can reduce the workload of the weight engineer and reduce the time for preparing the weight list. The helicopter test flight weight can be quickly implemented, the working time of the maintenance personnel is reduced, and the efficiency of replacing the weight is improved. The helicopter test flight test efficiency is improved, and the weight and gravity preparation work and time between two flights are reduced. The present application can quickly evaluate whether the weight and gravity requirements in the task list can be achieved, and the test flight personnel can conveniently change the test flight subject. The present application can implement the weight in advance, and the test flight flight plan is given in advance, thereby improving the test flight efficiency.

Claims

1. A method for automatically ballasting a helicopter during flight test, characterized in that, The method comprises: Step one, determining the helicopter empty weight gravity center data; determining the helicopter empty weight Wempty, the empty longitudinal gravity center position Xempty, the empty lateral gravity center position Yempty, and the empty vertical gravity center position Zempty; Step two, determining all the positions and weight information of the helicopter that can be balanced; determining all the positions and weight information of the helicopter that can be balanced, specifically including the balance block number i, the balance block weight Wbalancei, the balance block longitudinal position Xbalancei, the balance block lateral position Ybalancei, and the balance block vertical position Zbalancei, i∈(1,n); Step three, determining the helicopter crew member weight gravity center data; determining the crew member weight Wpilot, the crew longitudinal gravity center position Xpilot, the empty lateral gravity center position Ypilot, and the empty vertical gravity center position Zpilot; Step four, determining the helicopter fuel weight gravity center data; step four specifically comprises: According to the fuel tank arrangement on the aircraft and the fuel consumption sequence, the fuel gravity center position function corresponding to different fuel weights is determined, as shown below: Wherein Xfule represents the fuel longitudinal gravity center, Yfuel represents the fuel lateral gravity center, Zfuel represents the fuel vertical gravity center, and Wfuel represents the fuel weight; Step five, confirming the task fuel quantity according to the test flight subject task list requirements; step five specifically comprises: According to the test flight subject task list requirements, the task fuel quantity Wfuel is determined, and the fuel gravity center Xfule, Yfule, and Zfule data in each direction are calculated from the task fuel quantity Wfuel according to the fuel gravity center position function corresponding to different fuel weights in step four; Step six, determining the implementation workload of each balance block; step six specifically comprises: According to the sum of the maintenance and installation time, the workload of each balance block is quantified, and the balance block work time is represented by Timei; Step seven, using the data in steps one to five as the basis for calculation to calculate the total machine weight gravity center data; Step eight, determining the target weight and target gravity center as the constraint condition according to the test flight subject task list requirements; Step nine, taking the minimum work load in step six as the optimization goal; step nine is specifically: taking the minimum work load time of the service counterweight as the optimization goal, and the optimization goal function is as follows: ; Step ten, using the genetic algorithm to optimize the data in steps seven, eight, and nine to obtain the optimal balance scheme.

2. A method of automatically ballasting a helicopter during flight test, according to claim 1, wherein, Step seven specifically comprises: The total machine weight, the total machine longitudinal gravity center, the total machine lateral gravity center, and the total machine vertical gravity center are calculated, and the calculation formula is as follows, wherein W is the total weight of the helicopter, X is the total machine longitudinal gravity center of the helicopter, Y is the total machine lateral gravity center of the helicopter, and Z is the total machine vertical gravity center of the helicopter; 。 3. A method of automatically ballasting a helicopter during flight test, according to claim 2, wherein, Step eight specifically comprises: According to the test flight subject task list requirements, the target weight Wtarget, the target longitudinal gravity center Xtarget, the target lateral gravity center Ytarget, and the target vertical gravity center Ztarget are determined; the target weight and the target gravity center are used as the constraint condition, and the specific constraint condition is shown below The constraints specifically require that the total aircraft weight W is equal to the target weight Wtarget, the total aircraft longitudinal center of gravity X is within the target longitudinal center of gravity Xtarget ± 3 mm, the total aircraft lateral center of gravity Y is within the target lateral center of gravity Ytarget ± 3 mm, and the total aircraft vertical center of gravity Z is within the target vertical center of gravity Ztarget ± 3 mm.

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