Longitudinal gravity center control method of helicopter

Abstract

The invention belongs to the technical field of helicopter design, and particularly relates to a helicopter longitudinal gravity center control method. The method comprises the following steps: acquiring characteristic data of a helicopter; determining a fuel oil combined weight G oil front and a gravity center C oil front in a front limit loading state; determining the combined weight G oil and the gravity center C oil of the fuel oil in the rear limit loading state; the minimum oil receiving value of the oil consumption delta G of the oil receiving tank at the beginning of transmission is determined; the maximum oil receiving value of the oil consumption delta G of the oil receiving tank at the beginning of transmission is determined; the oil transportation minimum value of the transfer oil transportation amount delta G is determined; determining the maximum oil transportation value of the transfer oil transportation quantity delta G; deltaG oil receiving and deltaG oil conveying are provided for the design of a fuel oil system, and the automatic transfer function is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of helicopter design, and in particular relates to a method for controlling the longitudinal center of gravity of a helicopter. Background Art

[0002] The center of gravity of a helicopter is related to flight safety, flight quality, airframe life, development cycle and cost, etc., so it must be limited within a certain range during use. Conventional methods for controlling the center of gravity of a helicopter include empty center of gravity adjustment and payload limitation, mainly through equipment layout adjustment, local weight adjustment, payload position and order limitation, etc., which have the disadvantages of large workload and difficulty, increased development cycle and cost, and many usage restrictions. Summary of the invention

[0003] The technical problem solved by the present invention is that the center of gravity of a helicopter can be effectively limited within an envelope range through automatic control of a variable load during flight.

[0004] The technical solution of the present invention:

[0005] A method for controlling the longitudinal center of gravity of a helicopter, the method comprising:

[0006] Step 1: Obtain the characteristic data of the helicopter;

[0007] Step 2: Determine the total fuel weight G at the front limit loading state 油前 , Center of Gravity C 油前 ;

[0008] Step 3: Determine the total fuel weight G at the rear limit loading state 油后 , Center of Gravity C 油后 ;

[0009] Step 4: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Minimum value;

[0010] Step 5: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Maximum value;

[0011] Step 6: Determine the oil transfer volume ΔG 输油 Minimum value;

[0012] Step 7: Determine the oil transfer volume ΔG 输油 Maximum value;

[0013] Step 8: ΔG 受油 , ΔG 输油 Provide fuel system design to realize automatic transfer function.

[0014] Furthermore, in the first step, the characteristic data at least includes the weight center of gravity envelope front limit C 前 and rear limit C后 , Empty weight G 空 and the center of gravity C 空 , Unit weight G 机组 and the center of gravity C 机组 , Commercial load weight G 商 and the center of gravity C 商 , the weight of fuel in the fuel tank G 输油 , Center of Gravity C 输油 and fuel consumption V 输油耗 、The weight of the fuel in the fuel tank G 受油 , Center of Gravity C 受油 and fuel consumption V 受油耗 , fuel transfer rate V 转 .

[0015] Furthermore, in the second step,

[0016] G 油前 *C 油前 ≥(G 空 +G 机组 +G 商 +G 油前 )*C 前 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 ).

[0017] Furthermore, in the third step,

[0018] G 油后 *C 油后 ≤(G 空 +G 机组 +G 商 +G 油后 )*C 后 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 ).

[0019] Furthermore, in the fourth step,

[0020] ΔG 受油 ≥(G 输油 *C 输油 +G 受油 *C 受油 -G 油后 *C 油后 )*V 受油耗 / (V 输油耗 *C 输油 +V受油耗

[0021] *C 受油 ).

[0022] Furthermore, in the fifth step,

[0023] ΔG 受油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 )*V 受油耗 / (V 输油耗 *C 输油 +V 受油耗

[0024] *C 受油 ).

[0025] Furthermore, in the sixth step,

[0026] ΔG 输油 ≥(G 输油 *C 输油 +G 受油 *C 受油 -G 油后 *C 油后 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输

[0027] 油耗 / V 受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗 *C 受油 / V 转 ).

[0028] ΔG 输油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输

[0029] 油耗 / V受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗 *C 受油 / V 转 ).

[0030] Furthermore, in the eighth step,

[0031] The fuel transfer start conditions determined in the fourth and fifth steps, and the fuel transfer amounts determined in the sixth and seventh steps are used as inputs for the fuel system design to realize the automatic transfer function.

[0032] For helicopters with fuel tanks distributed front and back, the transfer start conditions and transfer amount are determined based on the weight center of gravity envelope and loading data. Through automatic transfer of fuel, the purpose of controlling the helicopter's center of gravity during flight is achieved, thereby ensuring that the helicopter's center of gravity does not exceed the limit within the entire flight profile. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a flow chart of a method for controlling the longitudinal center of gravity of a helicopter;

[0034] Figure 2 Schematic diagram of the relationship between longitudinal center of gravity and weight. DETAILED DESCRIPTION

[0035] The technical solution of the present invention is described in detail below in conjunction with the accompanying drawings.

[0036] In addition to commercial load, variable loads during flight also include fuel. For helicopters with fuel tanks distributed front and back, the transfer start conditions and transfer amount are determined based on the weight center of gravity envelope and loading data. Through automatic fuel transfer, the purpose of controlling the helicopter's center of gravity during flight is achieved, thereby ensuring that the helicopter's center of gravity does not exceed the limit within the entire flight profile. Figure 1 As shown, the specific steps are as follows:

[0037] Step 1: Obtain the helicopter's characteristic data, which should include at least the weight and center of gravity envelope front limit 6.2C 前 and the latter limit is 6.6C 后 、Empty weight 2000G 空 and center of gravity 6.6C 空 、Unit weight 200G 机组 and center of gravity 2C 机组 、Commercial load weight 1000G 商 and center of gravity 7C 商 , The weight of the fuel in the fuel tank is 400G 输油 、Center of gravity 6C 输油 and fuel consumption rate 200V输油耗 、The weight of the fuel in the fuel tank is 400G 受油 、Center of gravity 7C 受油 and fuel consumption rate 200V 受油耗 , fuel transfer rate 400V 转 wait;

[0038] Step 2: Determine the total fuel weight G at the front limit loading state 油前 , Center of Gravity C 油前 ;

[0039] G 油前 *C 油前 ≥(G 空 +G 机组 +G 商 +G 油前 )*C 前 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 )

[0040] (2000+200+1000+400)*6.2-(2000*6.6+200*2+1000*7)=1720

[0041] Step 3: Determine the total fuel weight G at the rear limit loading state 油后 , Center of Gravity C 油后 ;

[0042] G 油后 *C 油后 ≤(G 空 +G 机组 +G 商 +G 油后 )*C 后 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 )

[0043] (2000+200+1000+400)*6.6-(2000*6.6+200*2+1000*7)=3160

[0044] Step 4: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Minimum value;

[0045] ΔG 受油 ≥(G 输油 *C 输油 +G受油 *C 受油 -G 油后 *C 油后 )*V 受油耗 / (V 输油耗 *C 输油 +V 受油耗

[0046] *C 受油 )

[0047] (400*6+400*7-400*7)*200 / (200*6+200*7)=185

[0048] Step 5: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Maximum value;

[0049] ΔG 受油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 )*V 受油耗 / (V 输油耗 *C 输油 +V 受油耗

[0050] *C 受油 )

[0051] (400*6+400*7-400*6)*200 / (200*6+200*7)=215

[0052] Step 6: Determine the oil transfer volume ΔG 输油 Minimum value;

[0053] ΔG 输油 ≥(G 输油 *C 输油 +G 受油 *C 受油 -G 油后 *C 油后 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输

[0054] 油耗 / V 受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗*C 受油 / V 转 )

[0055] (400*6+400*7-400*7-200*7-200*6*200 / 200) / (6-7+200*6 / 400+200*7 / 400)=-36

[0056] Step 7: Determine the oil transfer volume ΔG 输油 Maximum value;

[0057] ΔG 输油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输

[0058] 油耗 / V 受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗 *C 受油 / V 转 )

[0059] (400*6+400*7-400*6-200*7-200*6*200 / 200) / (6-7+200*6 / 400+200*7 / 400)=36

[0060] Step 8: ΔG 受油 , ΔG 输油 Provide fuel system design to realize automatic transfer function.

[0061] The fuel transfer start conditions determined in steps 4 and 5, and the fuel transfer amounts determined in steps 6 and 7 are used as inputs for fuel system design to implement the automatic transfer function.

[0062] like Figure 2 Shown is a schematic diagram of the relationship between the longitudinal center of gravity and weight.

[0063] The present invention has found a design method for controlling the center of gravity of a helicopter during flight. This design method is simple and quick, can be quickly adjusted and updated according to usage requirements, and effectively reduces the control pressure of the helicopter center of gravity. It has been successfully applied to a certain helicopter and has great engineering application value.

Claims

1. A method for controlling the longitudinal center of gravity of a helicopter, characterized in that: The method comprises: Step 1: Obtain the characteristic data of the helicopter; Step 2: Determine the total fuel weight G at the front limit loading state 油前 , Center of Gravity C 油前 ; Step 3: Determine the total fuel weight G at the rear limit loading state 油后 , Center of Gravity C 油后 ; Step 4: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Minimum value; Step 5: Determine the fuel consumption ΔG of the receiving tank at the beginning of transfer 受油 Maximum value; Step 6: Determine the oil transfer volume ΔG 输油 Minimum value; Step 7: Determine the oil transfer volume ΔG 输油 Maximum value; Step 8: ΔG 受油 , ΔG 输油 Provide fuel system design to realize automatic transfer function.

2. A method for controlling the longitudinal center of gravity of a helicopter according to claim 1, characterized in that: In the first step, the characteristic data at least includes the weight center of gravity envelope front limit C 前 and rear limit C 后 , Empty weight G 空 and the center of gravity C 空 , Unit weight G 机组 and the center of gravity C 机组 , Commercial load weight G 商 and the center of gravity C 商 , the weight of fuel in the fuel tank G 输油 , Center of Gravity C 输油 and fuel consumption V 输油耗 、The weight of the fuel in the fuel tank G 受油 , Center of Gravity C 受油 and fuel consumption V 受油耗 , fuel transfer rate V 转 .

3. A method for controlling the longitudinal center of gravity of a helicopter according to claim 2, characterized in that: In the second step, G 油前 *C 油前 ≥(G 空 +G 机组 +G 商 +G 油前 )*C 前 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 )。 4. A method for controlling the longitudinal center of gravity of a helicopter according to claim 3, characterized in that: In the third step, G 油后 *C 油后 ≤(G 空 +G 机组 +G 商 +G 油后 )*C 后 -(G 空 *C 空 +G 机组 *C 机组 +G 商 *C 商 )。 5. A method for controlling the longitudinal center of gravity of a helicopter according to claim 4, characterized in that: In the fourth step, ΔG 受油 ≥(G 输油 *C 输油 +G 受油 *C 受油 -G 油后 *C 油后 )*V 受油耗 / (V 输油耗 *C 输油 +V 受油耗 *C 受油 )。 6. A method for controlling the longitudinal center of gravity of a helicopter according to claim 5, characterized in that: In the fifth step, ΔG 受油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 )*V 受油耗 / (V 输油耗 *C 输油 +V 受油耗 *C 受油 )。 7. A method for controlling the longitudinal center of gravity of a helicopter according to claim 6, characterized in that: In the sixth step, ΔG 输油 ≥(G 输油 *C 输油 +G 受油 *C 受油 -G 油后 *C 油后 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输 油耗 / V 受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗 *C 受油 / V 转 )。 ΔG 输油 ≤(G 输油 *C 输油 +G 受油 *C 受油 -G 油前 *C 油前 -ΔG 受油 *C 受油 -ΔG 受油 *C 输油 *V 输 油耗 / V 受油耗 ) / (C 输油 -C 受油 +V 输油耗 *C 输油 / V 转 +V 受油耗 *C 受油 / V 转 )。 8. A method for controlling the longitudinal center of gravity of a helicopter according to claim 7, characterized in that: In the eighth step, The fuel transfer start conditions determined in the fourth and fifth steps, and the fuel transfer amounts determined in the sixth and seventh steps, are used as inputs for the fuel system design to realize the automatic transfer function.

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