Automatic weight balancing method in helicopter test flight test

Abstract

The invention belongs to the technical field of overall design of helicopters, and particularly relates to an automatic weight balancing method in a helicopter flight test. Comprising the following steps: 1, determining empty helicopter weight gravity center data; 2, determining all positions and weight information capable of being subjected to counterweight on the helicopter; 3, determining the weight gravity center data of the helicopter crew members; 4, determining helicopter fuel oil weight center-of-gravity data; 5, according to the requirement of the test flight subject task list, the task oil quantity is confirmed; 6, the implementation workload of each balancing weight is determined; step 7, using the data in the step 1 to the step 5 as a calculation basis to calculate the gravity center data of the whole aircraft weight; 8, determining the target weight and the target gravity center as constraint conditions according to the requirements of the test flight subject task list; 9, taking the minimum value of the implementation workload in the step 6 as an optimization target; and 10, carrying out optimization calculation on the data in the steps 7, 8 and 9 by adopting a genetic algorithm to obtain an optimal weight balancing scheme.

Description

Technical Field

[0001] The invention belongs to the technical field of overall helicopter design, and in particular relates to an automatic weight balancing method in a helicopter flight test. Background Art

[0002] In helicopter flight tests, different flight test subjects have different weight and center of gravity requirements for the helicopter. Therefore, the helicopter must be counterweighted in accordance with the requirements of the flight test mission book before each flight test. After counterweighting, the requirements of the flight test mission book are met, and the flight test data obtained from this flight is valid.

[0003] At present, my country has designed many helicopters. In the past, during the flight tests of these helicopters, the weighting work was done by the weight engineer who gave the flight test weighting list, and the maintenance personnel carried out the weighting work according to the flight test weighting list. In the past, the existing flight test weighting methods were all calculated manually by the weight engineer. In the weighting design process, the weighting workload of the maintenance personnel was not considered enough, which often resulted in slow manual weighting speed and heavy weighting workload for the maintenance personnel. Summary of the invention

[0004] The purpose of the present invention is to solve the problems of complicated original helicopter balancing process, heavy balancing workload and low balancing efficiency in helicopter flight test. This paper designs an automatic balancing method in helicopter flight test. Through computer algorithm, the balancing scheme is automatically given with the minimum workload of maintenance as the optimization goal, which meets the requirements of the flight test task list, improves the balancing efficiency, reduces the balancing time and increases the flight test efficiency.

[0005] In order to achieve the above object, the present invention adopts the following technical solution to achieve it.

[0006] An automatic weight balancing method in a helicopter flight test, the method comprising:

[0007] Step 1: Determine the helicopter's empty weight and center of gravity data;

[0008] Step 2: Determine the positions and weight information of all the weights that can be placed on the helicopter;

[0009] Step 3, determine the weight center of gravity data of the helicopter crew members;

[0010] Step 4: Determine the helicopter fuel weight center of gravity data;

[0011] Step 5: Confirm the mission fuel quantity according to the requirements of the flight test subject task list;

[0012] Step 6: Determine the implementation workload of each counterweight block;

[0013] Step 7: Use the data from step 1 to step 5 as the basis for calculating the weight and center of gravity data of the whole aircraft;

[0014] Step 8. According to the requirements of the flight test task list, determine the target weight and target center of gravity as constraints;

[0015] Step 9: Taking the minimum value of the workload implemented in step 6 as the optimization goal;

[0016] Step 10: Using the data from steps 7, 8 and 9, a genetic algorithm is used to perform optimization calculations to obtain the optimal weight distribution scheme.

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

[0018] 2) Determine the positions and weight information of all ballasts on the helicopter, including the ballast block number i, ballast block weight Wbalancei, ballast block longitudinal position Xbalancei, ballast block lateral position Ybalancei, ballast block vertical position Zbalancei, i∈(1,n);

[0019] 3) Determine the crew weight W Pilot, the crew longitudinal center of gravity position X Pilot, the empty aircraft lateral center of gravity position Y Pilot, and the empty aircraft vertical center of gravity position Z Pilot.

[0020] Furthermore, step four is specifically as follows:

[0021] According to the layout of the onboard fuel tanks and the order of fuel consumption, the fuel center of gravity position function corresponding to different fuel weights is determined as follows:

[0022]

[0023] Among them, Xfuel 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 weight of the fuel.

[0024] Furthermore, step five is specifically as follows:

[0025] According to the requirements of the flight test subject task list, determine the mission fuel quantity Wfuel, and calculate the center of gravity Xfule, Yfule, and Zfule data of the fuel in each direction based on the fuel center of gravity position function corresponding to different fuel weights in step 4 from the mission fuel quantity Wfuel.

[0026] Furthermore, step six is ​​specifically as follows:

[0027] The workload of each counterweight block is quantified according to the sum of the maintenance handling time and the installation time, and the counterweight working time of each counterweight block is represented by Timei.

[0028] Furthermore, step seven is specifically as follows:

[0029] Calculate the total weight, longitudinal center of gravity, transverse center of gravity, and vertical center of gravity of the helicopter using the following formula, where W is the total weight of the helicopter, X is the longitudinal center of gravity of the helicopter, Y is the transverse 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] Furthermore, step eight is specifically as follows:

[0035] According to the requirements of the flight test subject task list, the target weight Wtarget, target longitudinal center of gravity Xtarget, target lateral center of gravity Ytarget, and target vertical center of gravity Ztarget are clearly defined; the target weight and target center of gravity are used as constraints. The specific constraints are as follows

[0036]

[0037] The specific requirements of the constraint conditions are that the weight W of the whole machine must be equal to the target weight Wtarget, the longitudinal center of gravity X of the whole machine must be within the range of the target longitudinal center of gravity Xtarget±3mm, the lateral center of gravity Y of the whole machine must be within the range of the target lateral center of gravity Ytarget±3mm, and the vertical center of gravity Z of the whole machine must be within the range of the target vertical center of gravity Ztarget±3mm.

[0038] Furthermore, step nine is specifically as follows:

[0039] Taking the minimum time of maintenance counterweight workload as the optimization goal, the optimization objective function is as follows:

[0040]

[0041] The present invention proposes an automatic weight balancing method in a helicopter flight test. The automatic weight balancing algorithm is compiled, and a calculation program is used to implement the automatic weight balancing. In the automatic weight balancing algorithm, the minimum workload of the maintenance personnel is taken as the optimization target, and a weight balancing plan is given. The above-mentioned automatic weight balancing method can reduce the workload of the weight engineer, and the previous manual preparation of the weight balancing plan is changed into a simple data input work. The use of computer automatic calculation also saves the time for formulating the weight balancing plan. In addition, since the automatic weight balancing algorithm takes the maintenance workload as the optimization target, it also reduces the time for the maintenance personnel to implement the weight balancing plan, and improves the efficiency of the weight balancing for each flight test as a whole. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 A schematic flow chart of an automatic weight balancing method in a helicopter flight test is provided for an embodiment of the present invention;

[0043] Figure 2 A schematic diagram of the counterweight workload provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0044] The technical solution of the present invention is described in detail below with reference to the accompanying drawings.

[0045] The present invention designs an automatic weight balancing method in a helicopter flight test and automatically provides a flight test weight balancing scheme:

[0046] Step 1: Determine the helicopter's empty weight and center of gravity data;

[0047] Step 2: Determine the positions and weight information of all the weights that can be placed on the helicopter;

[0048] Step 3, determine the weight center of gravity data of the helicopter crew members;

[0049] Step 4: Determine the helicopter fuel weight center of gravity data;

[0050] Step 5: Confirm the mission fuel quantity according to the requirements of the flight test mission order;

[0051] Step 6: Determine the implementation workload of each counterweight block;

[0052] Step 7: Use the data from step 1 to step 5 as the basis for calculating the weight and center of gravity data of the whole aircraft;

[0053] Step 8. According to the requirements of the flight test task list, determine the target weight, target center of gravity, etc. as constraints;

[0054] Step 9: Taking the minimum value of the real-time workload in step 6 as the optimization target;

[0055] Step 10: Using the data from steps 7, 8 and 9, a genetic algorithm is used to perform an optimization calculation to obtain a weight calculation result, that is, to provide a weight solution;

[0056] Step 11: The maintenance personnel shall apply counterweight to the helicopter according to the counterweight plan;

[0057] Step 12: The weight test flight is completed.

[0058] Specifically,

[0059] like Figure 1 As shown, for the automatic weight balancing method in a helicopter flight test proposed by the present invention, the specific use process includes the following steps.

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

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

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

[0063] 4) According to the layout of the onboard fuel tanks and the order of fuel consumption, determine the fuel center of gravity position function corresponding to different fuel weights, as shown below:

[0064]

[0065] Among them, Xfuel 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 weight of the fuel.

[0066] 5) According to the requirements of the flight test subject task list, clarify the mission fuel quantity Wfuel, and calculate the center of gravity Xfule, Yfule, and Zfule data of the fuel in each direction based on the mission fuel quantity Wfuel according to the function in 4).

[0067] 6) Quantify the workload of each counterweight block according to the sum of the maintenance handling time and installation time, and the counterweight working time of each counterweight block is represented by Timei;

[0068] Issue a counterweight workload statistics table to the maintenance personnel to count the workload of each counterweight block. The main contents of the counterweight workload statistics table are as follows: Figure 2As shown, the workload statistics form is sent to each maintenance person, who fills in items such as the transportation time and installation time, and all the data filled in by the maintenance people are counted.

[0069] 7) Based on the data in the above 5 steps, calculate the total weight, the longitudinal center of gravity of the whole helicopter, the lateral center of gravity of the whole helicopter, and the vertical center of gravity of the whole helicopter. The calculation formula is as follows, where W is the total weight of the helicopter, X is the longitudinal center of gravity of the whole helicopter, Y is the lateral center of gravity of the whole helicopter, and Z is the vertical center of gravity of the whole 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 flight test task list, specify the target weight Wtarget, target longitudinal center of gravity Xtarget, target lateral center of gravity Ytarget, and target vertical center of gravity Ztarget; use the target weight and target center of gravity as constraints. The specific constraints are as follows

[0075]

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

[0077] 9) Taking the minimum time of the maintenance counterweight workload as the optimization goal, the optimization objective function is as follows:

[0078]

[0079] 10) According to the constraints in 9) and the optimization objective function in 10), a genetic algorithm is used to perform optimization calculations to obtain calculation results. The calculation results can reflect the weight information of each position, that is, a weighting plan is obtained.

[0080] 11) The maintenance personnel shall apply counterweight to the helicopter according to the counterweight plan;

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

[0082] The automatic weight balancing method in a helicopter flight test of the present invention can reduce the workload of weight engineers and reduce the time for compiling weight balancing lists. The present invention can realize rapid weight balancing for helicopter flight tests, reduce the working time of maintenance personnel, and improve the efficiency of replacing weights. The present invention increases the efficiency of helicopter flight tests and reduces the weight balancing preparation work and time between two sorties. The present invention can quickly evaluate whether the weight center of gravity requirements in the task list can be achieved, making it convenient for test flight personnel to change test flight subjects. The present invention can realize early weight balancing, provide a test flight sortie plan in advance, and improve test flight efficiency.

Claims

1. An automatic weight balancing method in a helicopter flight test, characterized in that: The method comprises: Step 1: Determine the helicopter's empty weight and center of gravity data; Step 2: Determine the positions and weight information of all the weights that can be placed on the helicopter; Step 3, determine the weight center of gravity data of the helicopter crew members; Step 4: Determine the helicopter fuel weight center of gravity data; Step 5: Confirm the mission fuel quantity according to the requirements of the flight test subject task list; Step 6: Determine the implementation workload of each counterweight block; Step 7: Use the data from step 1 to step 5 as the basis for calculating the weight and center of gravity data of the whole aircraft; Step 8. According to the requirements of the flight test task list, determine the target weight and target center of gravity as constraints; Step 9: Taking the minimum value of the workload implemented in step 6 as the optimization goal; Step 10: Using the data from steps 7, 8 and 9, a genetic algorithm is used to perform optimization calculations to obtain the optimal weight distribution scheme.

2. The automatic weight balancing method in a helicopter flight test according to claim 1, characterized in that: 1) Determine the helicopter's empty weight Wempty, empty longitudinal center of gravity position Xempty, empty lateral center of gravity position Yempty, and empty vertical center of gravity position Zempty; 2) Determine the positions and weight information of all ballasts on the helicopter, including the ballast block number i, ballast block weight Wbalancei, ballast block longitudinal position Xbalancei, ballast block lateral position Ybalancei, ballast block vertical position Zbalancei, i∈(1,n); 3) Determine the crew weight W Pilot, the crew longitudinal center of gravity position X Pilot, the empty aircraft lateral center of gravity position Y Pilot, and the empty aircraft vertical center of gravity position Z Pilot.

3. The automatic weight balancing method in a helicopter flight test according to claim 1, characterized in that: Step 4 is as follows: According to the layout of the onboard fuel tanks and the order of fuel consumption, the fuel center of gravity position function corresponding to different fuel weights is determined as follows: Among them, Xfuel 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 weight of the fuel.

4. The automatic weight balancing method in a helicopter flight test according to claim 3 is characterized in that: Step 5 is as follows: According to the requirements of the flight test subject task list, determine the mission fuel quantity Wfuel, and calculate the center of gravity Xfule, Yfule, and Zfule data of the fuel in each direction based on the fuel center of gravity position function corresponding to different fuel weights in step 4 from the mission fuel quantity Wfuel.

5. The automatic weight balancing method in a helicopter flight test according to claim 4 is characterized in that: Step 6 is as follows: The workload of each counterweight block is quantified according to the sum of the maintenance handling time and the installation time, and the counterweight working time of each counterweight block is represented by Timei.

6. The automatic weight balancing method in a helicopter flight test according to claim 5, characterized in that: Step 7 is as follows: Calculate the total weight, longitudinal center of gravity, transverse center of gravity, and vertical center of gravity of the helicopter using the following formula, where W is the total weight of the helicopter, X is the longitudinal center of gravity of the helicopter, Y is the transverse center of gravity of the helicopter, and Z is the vertical center of gravity of the helicopter; W ＝ W in p t y + ∑ Wb the l ance i+Wf ue l+W p il the t X ＝ (W emp t y *X emp t y + ∑ (Wb a l ance i*Xb a l ance i)+Wf ue l*Xf ue l+W p il o t*X p il o t) / W Y ＝ (Wem p t y *Yem p t y + ∑ (Wbalancei*Ybalancei)+Wfuel*Yfuel+W p ilot*Y p ilot) / W Z＝(Wempty*Zempty+ ∑ (Wbalancei*Zbalancei)+Wfuel*Zfuel+Wpilot*Zpilot) / W 。 7. The automatic weight balancing method in a helicopter flight test according to claim 6, characterized in that: Step 8 is as follows: According to the requirements of the flight test subject task list, the target weight Wtarget, target longitudinal center of gravity Xtarget, target lateral center of gravity Ytarget, and target vertical center of gravity Ztarget are clearly defined; the target weight and target center of gravity are used as constraints. The specific constraints are as follows The specific requirements of the constraint conditions are that the weight W of the whole machine must be equal to the target weight Wtarget, the longitudinal center of gravity X of the whole machine must be within the range of the target longitudinal center of gravity Xtarget±3mm, the lateral center of gravity Y of the whole machine must be within the range of the target lateral center of gravity Ytarget±3mm, and the vertical center of gravity Z of the whole machine must be within the range of the target vertical center of gravity Ztarget±3mm.

8. The automatic weight balancing method in a helicopter flight test according to claim 7, characterized in that: Step nine is as follows: Taking the minimum time of maintenance counterweight workload as the optimization goal, the optimization objective function is as follows:

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