A flight / engine matching verification method for a compound thrust configuration helicopter

Abstract

The present application provides a flight / engine matching verification method for a composite thrust configuration helicopter, the method comprising: step 1: when the helicopter is tethered on the ground, performing a rotor-transmission-engine link collective pitch calibration; step 2: when the helicopter is tethered on the ground, starting the engine to slow down, manipulating the helicopter collective pitch, and performing a rotor-transmission-engine link ramp scan; step 3: when the helicopter is tethered on the ground, starting the engine to slow down, manipulating the helicopter collective pitch, and performing a rotor-transmission-engine link step scan; step 4: when the helicopter is tethered on the ground, starting the engine to slow down, manipulating the helicopter collective pitch back and forth between specified collective pitch values, and completing a rotor-transmission-engine link acceleration and deceleration characteristic check; step 5: when the helicopter is tethered on the ground, performing a thrust propeller calibration of the thrust propeller-transmission-engine link.

Description

Technical Field

[0001] The invention belongs to the field of helicopters, and in particular relates to a flight / engine matching verification method for a helicopter with a compound thrust configuration. Background Art

[0002] With the continuous development of new-generation helicopters, performance requirements are constantly increasing. This is especially true for propeller-driven helicopters, where the main rotor and propellers can be independently controlled and draw power from the engine. Flight characteristics and control methods are more complex. The design of these helicopters and engines often adopts a flight / engine integration approach, achieving integrated control of the engine and helicopter through the establishment of a helicopter / engine model to ensure maximum compatibility between the engine and helicopter. This has also led to increased complexity in various subsystems, such as the helicopter's flight control system and engine, and significantly increased coupling between systems.

[0003] To ensure flight safety, helicopters often require extensive ground and flight testing to verify the operation of various systems. Traditional helicopters, due to their simplicity of operation, use bench testing to verify the functionality and performance of their engines. Random verification is then conducted after installation. However, specialized verification methods for flight / engine compatibility are limited, and these methods are inadequate for the verification needs of these newly configured helicopters. Summary of the Invention

[0004] The present application provides a flight / engine matching verification method for a helicopter with a composite thrust configuration, which meets the ground test verification requirements of the helicopter, verifies the working compatibility of the helicopter and the engine, provides a basis for system optimization and improvement and test flights, and ultimately ensures the helicopter's control stability, maneuverability and safety.

[0005] Technical solution: A flight / engine matching verification method for a compound thrust configuration helicopter, the method comprising:

[0006] Step 1: With the helicopter tethered on the ground, perform rotor-transmission-engine link collective distance calibration;

[0007] Step 2: With the helicopter tethered on the ground, start the engine and slow down the flight, operate the helicopter collective pitch, and perform a ramp scan of the rotor-transmission-engine link.

[0008] Step 3: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter's collective pitch and perform a step-by-step scan of the rotor-transmission-engine link.

[0009] Step 4: With the helicopter tethered on the ground, start the engine and slow down the helicopter. Maneuver the helicopter collective pitch back and forth between the specified collective pitch values ​​to complete the acceleration and deceleration characteristics check of the rotor-transmission-engine link.

[0010] Step 5: With the helicopter tethered on the ground, perform thrust propeller calibration of the thrust propeller-transmission-engine link.

[0011] Step 6: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a ramp scan of the thrust propeller-transmission-engine link.

[0012] Step 7: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a step-by-step scan of the thrust-transmission-engine link.

[0013] Step 8: With the helicopter tethered on the ground, start the engine and slow down to a crawl. Maneuver the helicopter thrust pitch back and forth between the specified thrust pitch values ​​to complete the acceleration and deceleration characteristic check of the thrust propeller-transmission-engine link.

[0014] Specifically, step 1 includes:

[0015] Step 1-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current collective pitch value as Clp1 and torque value as Q1.

[0016] Step 1-2: Slowly increase the collective distance until the torque reaches Q1+10%. Record the current collective distance value as Clp2 and the torque value as Q2 (Q2=Q1+10%).

[0017] Step 1-3: Continue to slowly increase the collective distance until the torque reaches Q2 + 10%. Record the current collective distance value as Clp3 and the torque value as Q3 (Q3 = Q2 + 10%).

[0018] Steps 1-4: Increase in sequence until the maximum engine torque Q is reached max , and record the total distance value at maximum torque as Clp max ; Among them, the maximum torque Q max is the torque limit of the engine or helicopter, whichever occurs first;

[0019] Step 1-5: Based on the torque values ​​Q1, Q2, Q3 ... the maximum engine torque Q max , and helicopter total distance values ​​Clp1, Clp2, Clp3…Clp max , obtain the first engine torque value and helicopter collective pitch table;

[0020] Step 1-6: With collective and thrust pitch at low, start the engines to flight idle.

[0021] Step 1-7: Slowly increase the total distance until the torque reaches 30%, and record the current total distance value as clp x ;

[0022] Step 1-8: Continue to slowly increase the total distance until the torque reaches 50%, and record the current total distance value as clp y ;

[0023] Step 1-9: According to clp x and clp y , get the second engine torque value and helicopter collective pitch table.

[0024] Specifically, step 2 includes:

[0025] Step 2-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0026] Step 2-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula a=(Clp max -Clp1) / 30s, calculate the rate a, and increase the helicopter's collective pitch at rate a until the engine torque is Q max ;

[0027] Step 2-3: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0028] Step 2-4: Reduce the helicopter's collective pitch at a rate a until the engine torque is Q1; where a = (Clp max -Clp1) / 30s;

[0029] Step 2-5: The collective pitch and thrust pitch are in a low state to maintain stable engine operation.

[0030] Specifically, step 3 includes:

[0031] Step 3-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0032] Step 3-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula b = (Clp2 - Clp1) / 5s to calculate the rate b, and increase the helicopter collective pitch at the rate b until the engine torque reaches Q2;

[0033] Step 3-3: Maintain the helicopter collective pitch at Clp2 and allow the engine to maintain a torque of Q2 for 30 seconds.

[0034] Step 3-4: Repeat steps 3-2 and 3-3, increasing the engine torque by 10% each time until the engine torque is Q max ;

[0035] Step 3-5: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0036] Step 3-5: Reverse the steps 3-2 and 3-3, reducing the engine torque by 10% each time until the engine torque reaches Q1;

[0037] Step 3-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0038] Specifically, step 4 includes:

[0039] Step 4-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0040] Step 4-2: Slowly increase the collective pitch to clp x , so that the engine can work stably at 30% torque;

[0041] Step 4-3: According to the formula e1=(clp y -clp x ) / 5s, calculate the rate e1, and increase the helicopter collective pitch at the rate e1 until the engine torque reaches 50%;

[0042] Step 4-4: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0043] Step 4-5: Reduce the helicopter collective pitch at rate e1 until the engine torque is 30%;

[0044] Step 4-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0045] Step 4-7: According to the formula e2=(clp y -clp x ) / 2s calculation rate e 2， Increase the helicopter collective pitch at rate e2 until the engine torque reaches 50%;

[0046] Step 4-8: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0047] Step 4-9: Reduce the helicopter collective pitch at rate e2 until the engine torque is 30%;

[0048] Step 4-10: Maintain helicopter collective pitch clpx , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0049] Step 4-11: According to the formula e3=(clp y -clp x ) / 1s, calculate the rate e3, and increase the helicopter collective pitch at the rate e3 until the engine torque reaches 50%;

[0050] Step 4-12: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0051] Step 4-13: Decrease the helicopter collective pitch at a rate of e3 until the engine torque is 30%;

[0052] Step 4-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0053] Specifically, step 5 includes:

[0054] Step 5-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current thrust pitch value as Cla1 and the torque value as Q1.

[0055] Step 5-2: Slowly increase the thrust pitch until the torque reaches Q1+10%. Record the current thrust pitch value as Cla2 and the torque value as Q2 (Q2=Q1+10%).

[0056] Step 5-3: Continue to slowly increase the thrust pitch until the torque reaches Q2 + 10%. Record the current thrust pitch value as Cla3 and the torque value as Q3 (Q3 = Q2 + 10%).

[0057] Step 5-4: Increase gradually until the maximum engine torque Q is reached max , and record the thrust pitch value at maximum torque as Cla max ; Among them, the maximum torque Q max is the torque limit of the engine or helicopter, whichever occurs first;

[0058] Step 5-5: According to the torque values ​​Q1, Q2, Q3...Q max , helicopter thrust pitch Cla1, Cla2, Cla3, Cla max , obtaining a first engine torque value and a helicopter thrust pitch table;

[0059] Steps 5-6: With collective and thrust pitch at low, start the engines to flight idle.

[0060] Step 5-7: Slowly increase the thrust pitch until the torque reaches 30%, and record the current thrust pitch value as cla x ;

[0061] Step 5-8: Continue to slowly increase the thrust pitch until the torque reaches 50%, and record the current thrust pitch value as cla y ;

[0062] Step 5-9: According to Cla x and Cla y , obtain the second engine torque value and helicopter thrust pitch table.

[0063] Specifically, step 6 includes:

[0064] Step 6-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0065] Step 6-2: Based on the data in the first engine torque value and helicopter thrust pitch table and the second engine torque value and helicopter thrust pitch table, use the formula c=(Cla max -Cla1) / 30s calculate the rate c, and increase the helicopter thrust pitch at rate c until the engine torque is Q max ;

[0066] Step 6-3: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0067] Step 6-4: Reduce the helicopter thrust pitch at a rate c until the engine torque is Q1;

[0068] Step 6-5: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0069] Specifically, step 7 includes:

[0070] Step 7-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0071] Step 7-2: Calculate the rate d using the formula d = (Cla2 - Cla1) / 5s, and increase the helicopter thrust pitch at the rate d until the engine torque reaches Q2;

[0072] Step 7-3: Maintain the helicopter thrust pitch at Cla2 and the engine torque at Q2 for 30 seconds.

[0073] Step 7-4: Repeat steps 7-2 and 7-3, increasing the engine torque by 10% each time until the engine torque reaches Qmax;

[0074] Step 7-5: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0075] Step 7-6: Reverse the steps 7-2 and 7-3, reducing the engine torque by 10% each time until the engine torque reaches Q1;

[0076] Step 7-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0077] Specifically, step 8 includes:

[0078] Step 8-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0079] Step 8-2: Slowly raise the collective distance to cla x , so that the engine can work stably at 30% torque;

[0080] Step 8-3: Use the formula f1=(cla y -cla x ) / 5s, calculate the rate f1, and increase the helicopter collective pitch at the rate f1 until the engine torque reaches 50%;

[0081] Step 8-4: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0082] Step 8-5: Reduce the helicopter collective pitch at a rate of f1 until the engine torque reaches 30%;

[0083] Step 8-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0084] Step 4-7: Use the formula f2 = (cla y -cla x ) / 2s, calculate the rate f2, and increase the helicopter collective pitch at the rate f2 until the engine torque reaches 50%;

[0085] Step 8-8: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0086] Steps 8-9: Decrease the helicopter collective pitch at rate f2 until the engine torque is 30%;

[0087] Steps 8-10: Maintain helicopter collective distance cla x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0088] Step 8-11: Use the formula f3 = (cla y -cla x ) / 1s, calculate the rate f3, and increase the helicopter collective pitch at the rate f3 until the engine torque reaches 50%;

[0089] Steps 8-12: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0090] Step 8-13: Decrease the helicopter collective pitch at rate f3 until the engine torque is 30%;

[0091] Step 8-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0092] In summary, the present invention provides a flight / engine matching verification method for a compound thrust configuration helicopter, which is suitable for a ground test of a compound thrust configuration helicopter. BRIEF DESCRIPTION OF THE DRAWINGS

[0093] Figure 1 It is the collective pitch / thrust pitch ramp scan diagram;

[0094] Figure 2 It is the collective pitch / thrust pitch step scan diagram;

[0095] Figure 3 This is a schematic structural diagram of a compound thrust configuration helicopter applicable to this application;

[0096] Figure 4 Flowchart of a flight / engine matching verification method provided in this application DETAILED DESCRIPTION

[0097] like Figure 3 As shown, the present application provides a flight / engine matching verification method, which is applied to a compound thrust configuration helicopter. The main feature of the compound thrust configuration helicopter is the use of a coaxial rigid rotor and thrust propeller configuration. The compound configuration helicopter is similar to a conventional helicopter in low-speed and hovering states. The engine drives the rotor through the transmission system to provide flight power to the helicopter; while in high-speed states, the engine mainly drives the thrust propeller through the transmission system to provide thrust to the helicopter. The main features of the compound thrust configuration helicopter also include that the rotor and thrust propeller speeds can be adjusted according to the flight speed of the helicopter. At the same time, the transmission system contains a clutch, which can realize the selection and decoupling of the power transmission route.

[0098] Because this compound thrust helicopter has two relatively independent transmission chains: the rotor-transmission-engine chain and the thrust propeller-transmission-engine chain, the engine transmits power primarily through the rotor-transmission-engine chain in low-speed mode. In high-speed mode, the engine transmits power primarily through the thrust propeller-transmission-engine chain. The engine power is the sum of the power requirements of the rotor-transmission-engine chain and the thrust propeller-transmission-engine chain, namely:

[0099] P Eng =P rot +P pro

[0100] Among them, P Eng is the engine power, P rot P is the power requirement of the rotor-transmission-engine link, which is mainly determined by the collective pitch and rotor speed; pro The power required by the propeller-transmission-engine link is mainly determined by the thrust pitch and propeller speed.

[0101] like Figure 4 As shown, the flight / engine matching verification method provided in this application uses two separate transmission chains, rotor-transmission-engine and thrust propeller-transmission-engine, and is performed at any speed within the rotor / thrust propeller speed variation range.

[0102] The present application provides a flight / engine matching verification method for a compound thrust configuration helicopter, the method comprising:

[0103] Step 1: With the helicopter tethered on the ground, perform rotor-transmission-engine link collective distance calibration;

[0104] Step 2: With the helicopter tethered on the ground, start the engine and slow down the flight, operate the helicopter collective pitch, and perform a ramp scan of the rotor-transmission-engine link.

[0105] Step 3: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter's collective pitch and perform a step-by-step scan of the rotor-transmission-engine link.

[0106] Step 4: With the helicopter tethered on the ground, start the engine and slow down the flight. Maneuver the helicopter's collective pitch back and forth between the specified collective pitch values ​​to complete the acceleration and deceleration characteristics check of the rotor-transmission-engine link.

[0107] For example, step 4 can complete the acceleration and deceleration characteristics check of the rotor-transmission-engine link according to Table 1.

[0108] Table 1

[0109] Increased total distance Stablize Reduced collective distance First transient 5s 15s 5s Second transient 2s 15s 2s The third transient 1s 15s 1s

[0110] Step 5: With the helicopter tethered on the ground, perform thrust propeller calibration of the thrust propeller-transmission-engine link.

[0111] Step 6: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a ramp scan of the thrust propeller-transmission-engine link.

[0112] Step 7: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a step-by-step scan of the thrust-transmission-engine link.

[0113] Step 8: With the helicopter tethered on the ground, start the engine and slow down to a crawl. Maneuver the helicopter thrust pitch back and forth between the specified thrust pitch values ​​to complete the acceleration and deceleration characteristic check of the thrust propeller-transmission-engine link.

[0114] For example, the acceleration and deceleration characteristics of the propeller-transmission-engine link can be checked according to Table 2.

[0115] Table 2

[0116] Thrust pitch increase Stablize Thrust pitch reduction First transient 5s 15s 5s Second transient 2s 15s 2s The third transient 1s 15s 1s

[0117] In practice, steps 2 and 3 check the operating stability of the rotor-transmission-engine link, step 4 checks the acceleration and deceleration characteristics of the rotor-transmission-engine link, steps 6 and 7 check the operating stability of the thruster-transmission-engine link, and step 8 checks the acceleration and deceleration characteristics of the thruster-transmission-engine link. For multi-engine helicopters, each engine can be tested separately, with the final test performed with all engines operating simultaneously.

[0118] Specifically, step 1 includes:

[0119] Step 1-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current collective pitch value as Clp1 and torque value as Q1.

[0120] Step 1-2: Slowly increase the collective distance until the torque reaches Q1+10%. Record the current collective distance value as Clp2 and the torque value as Q2 (Q2=Q1+10%).

[0121] Step 1-3: Continue to slowly increase the collective distance until the torque reaches Q2 + 10%. Record the current collective distance value as Clp3 and the torque value as Q3 (Q3 = Q2 + 10%).

[0122] Steps 1-4: Increase in sequence until the maximum engine torque Q is reached max , and record the total distance value at maximum torque as Clp max Among them, the maximum torque Q maxis the torque limit of the engine or helicopter, whichever occurs first.

[0123] Step 1-5: Based on the torque values ​​Q1, Q2, Q3 ... the maximum engine torque Q max , and helicopter total distance values ​​Clp1, Clp2, Clp3…Clp max , get the first engine torque value and helicopter collective pitch table.

[0124] For example, the engine torque value and helicopter collective pitch table are shown in Table 3:

[0125] Table 3

[0126]

[0127]

[0128] In addition, step 1 also includes:

[0129] Step 1-6: With collective and thrust pitch at low, start the engines to flight idle.

[0130] Step 1-7: Slowly increase the total distance until the torque reaches 30%, and record the current total distance value as clp x ;

[0131] Step 1-8: Continue to slowly increase the total distance until the torque reaches 50%, and record the current total distance value as clp y ;

[0132] Step 1-9: According to clp x and clp y , get the second engine torque value and helicopter collective pitch table.

[0133] For example, the second engine torque value and helicopter collective pitch table is shown in Table 4:

[0134] Table 4

[0135] Engine torque 30％ 50％ Helicopter collective pitch (°) <![CDATA[Clp x =]]> <![CDATA[Clp y =]]>

[0136] Specifically, step 2 includes:

[0137] Step 2-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0138] Step 2-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula a=(Clp max -Clp1) / 30s, calculate the rate a, and increase the helicopter's collective pitch at rate a until the engine torque is Q max .

[0139] Step 2-3: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0140] Step 2-4: Reduce the helicopter's collective pitch at a rate a until the engine torque is Q1. Where a = (Clp max -Clp1) / 30s.

[0141] Step 2-5: The collective pitch and thrust pitch are in a low state to maintain stable engine operation.

[0142] Specifically, step 3 includes:

[0143] Step 3-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0144] Step 3-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula b = (Clp2 - Clp1) / 5s to calculate the rate b, and increase the helicopter collective pitch at the rate b until the engine torque reaches Q2;

[0145] Step 3-3: Maintain the helicopter collective pitch at Clp2 and allow the engine to maintain a torque of Q2 for 30 seconds.

[0146] Step 3-4: Repeat steps 3-2 and 3-3, increasing the engine torque by 10% each time until the engine torque is Q max ;

[0147] Step 3-5: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0148] Step 3-5: Reverse the steps 3-2 and 3-3, reducing the engine torque by 10% each time until the engine torque reaches Q1.

[0149] Step 3-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0150] Specifically, step 4 includes:

[0151] Step 4-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0152] Step 4-2: Slowly increase the collective pitch to clp x , so that the engine can work stably at 30% torque;

[0153] Step 4-3: According to the formula e1=(clp y -clp x ) / 5s, calculate the rate e1, and increase the helicopter collective pitch at the rate e1 until the engine torque reaches 50%.

[0154] Step 4-4: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0155] Step 4-5: Reduce the helicopter collective pitch at rate e1 until the engine torque is 30%.

[0156] Step 4-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0157] Step 4-7: According to the formula e2=(clp y -clp x ) / 2s calculation rate e 2， Increase the helicopter collective pitch at rate e2 until the engine torque is 50%.

[0158] Step 4-8: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0159] Step 4-9: Decrease the helicopter collective pitch at rate e2 until the engine torque is 30%.

[0160] Step 4-10: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0161] Step 4-11: According to the formula e3=(clp y -clp x ) / 1s, calculate the rate e3, and increase the helicopter collective pitch at the rate e3 until the engine torque reaches 50%.

[0162] Step 4-12: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0163] Step 4-13: Decrease the helicopter collective pitch at rate e3 until the engine torque is 30%.

[0164] Step 4-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0165] Similarly, step 5 includes:

[0166] Step 5-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current thrust pitch value as Cla1 and the torque value as Q1.

[0167] Step 5-2: Slowly increase the thrust pitch until the torque reaches Q1+10%. Record the current thrust pitch value as Cla2 and the torque value as Q2 (Q2=Q1+10%).

[0168] Step 5-3: Continue to slowly increase the thrust pitch until the torque reaches Q2 + 10%. Record the current thrust pitch value as Cla3 and the torque value as Q3 (Q3 = Q2 + 10%).

[0169] Step 5-4: Increase gradually until the maximum engine torque Q is reached max , and record the thrust pitch value at maximum torque as Cla max Among them, the maximum torque Q max is the torque limit of the engine or helicopter, whichever occurs first.

[0170] Step 5-5: According to the torque values ​​Q1, Q2, Q3...Q max , helicopter thrust pitch Cla1, Cla2, Cla3, Cla max , obtain the first engine torque value and helicopter thrust pitch table.

[0171] For example, the first engine torque value and helicopter thrust pitch table are shown in Table 5:

[0172] Table 5

[0173]

[0174] In addition, step 5 also includes:

[0175] Steps 5-6: With collective and thrust pitch at low, start the engines to flight idle.

[0176] Step 5-7: Slowly increase the thrust pitch until the torque reaches 30%, and record the current thrust pitch value as cla x ;

[0177] Step 5-8: Continue to slowly increase the thrust pitch until the torque reaches 50%, and record the current thrust pitch value as cla y ;

[0178] Step 5-9: According to Cla x and Cla y , obtain the second engine torque value and helicopter thrust pitch table.

[0179] For example, the second engine torque value and helicopter thrust pitch table are shown in Table 6:

[0180] Table 6

[0181] Engine torque 30％ 50％ Helicopter thrust pitch (°) <![CDATA[Cla x =]]> <![CDATA[Cla y =]]>

[0182] Specifically, step 6 includes:

[0183] Step 6-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0184] Step 6-2: Based on the data in the first engine torque value and helicopter thrust pitch table and the second engine torque value and helicopter thrust pitch table, use the formula c=(Cla max -Cla1) / 30s calculate the rate c, and increase the helicopter thrust pitch at rate c until the engine torque is Q max .

[0185] Step 6-3: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0186] Step 6-4: Reduce the helicopter thrust pitch at rate c until the engine torque is Q1.

[0187] Step 6-5: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0188] Specifically, step 7 includes:

[0189] Step 7-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0190] Step 7-2: Calculate the rate d using the formula d = (Cla2 - Cla1) / 5s, and increase the helicopter thrust pitch at the rate d until the engine torque reaches Q2.

[0191] Step 7-3: Maintain the helicopter thrust pitch at Cla2 and the engine torque at Q2 for 30 seconds.

[0192] Step 7-4: Repeat steps 7-2 and 7-3, increasing the engine torque by 10% each time until the engine torque reaches Qmax;

[0193] Step 7-5: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds;

[0194] Step 7-6: Reverse the steps 7-2 and 7-3 to reduce the engine torque by 10% each time until the engine torque reaches Q1.

[0195] Step 7-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0196] Specifically, step 8 includes:

[0197] Step 8-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation.

[0198] Step 8-2: Slowly raise the collective distance to cla x , so that the engine can work stably at 30% torque;

[0199] Step 8-3: Use the formula f1=(cla y -cla x ) / 5s, the rate f1 is calculated, and the helicopter collective pitch is increased at the rate f1 until the engine torque reaches 50%.

[0200] Step 8-4: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0201] Step 8-5: Reduce the helicopter collective pitch at rate f1 until the engine torque is 30%.

[0202] Step 8-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0203] Step 4-7: Use the formula f2 = (cla y -cla x ) / 2s, calculate the rate f2, and increase the helicopter collective pitch at the rate f2 until the engine torque reaches 50%.

[0204] Step 8-8: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0205] Steps 8-9: Reduce the helicopter collective pitch at rate f2 until the engine torque is 30%.

[0206] Steps 8-10: Maintain helicopter collective distance cla x , so that the engine maintains a torque of 30% and works stably for 15 seconds;

[0207] Step 8-11: Use the formula f3 = (cla y -cla x) / 1s, calculate the rate f3, and increase the helicopter collective pitch at the rate f3 until the engine torque reaches 50%.

[0208] Steps 8-12: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds;

[0209] Step 8-13: Decrease the helicopter collective pitch at rate f3 until the engine torque is 30%.

[0210] Step 8-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

[0211] During the test, the engine parameters, as well as the helicopter rotor speed, thrust propeller speed, collective pitch, and thrust pitch are recorded throughout the test to check whether the engine working status and engine control accuracy meet the helicopter index requirements during the entire test process.

[0212] Advantages of the present invention:

[0213] a) The present invention provides a flight / engine matching verification method applicable to a composite helicopter, which meets the ground test verification requirements of the helicopter, verifies the working compatibility between the helicopter and the engine, provides a basis for design improvement and test flight, and ultimately ensures the helicopter's control stability, maneuverability and safety.

[0214] b) The flight / engine matching verification method provided by the present invention includes the working stability check and acceleration and deceleration characteristic check of the helicopter, and is also applicable to conventional configuration helicopters through appropriate tailoring.

[0215] This paper presents a test method for engine-to-helicopter compatibility under simulated common and harsh helicopter operating conditions for a propeller-powered helicopter. This method can be used to verify the compatibility of a propeller-powered helicopter and its engine. If the engine and helicopter operate well during the test, and the engine parameters and rotor speed control accuracy meet the helicopter's design requirements, the aircraft / engine compatibility is considered good.

Claims

1. A flight / engine matching verification method for a compound thrust configuration helicopter, characterized in that: Methods include: Step 1: With the helicopter tethered on the ground, perform rotor-transmission-engine link collective distance calibration; Step 2: With the helicopter tethered on the ground, start the engine and slow down the flight, operate the helicopter collective pitch, and perform a ramp scan of the rotor-transmission-engine link. Step 3: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter's collective pitch and perform a step-by-step scan of the rotor-transmission-engine link. Step 4: With the helicopter tethered on the ground, start the engine and slow down the helicopter. Maneuver the helicopter collective pitch back and forth between the specified collective pitch values ​​to complete the acceleration and deceleration characteristics check of the rotor-transmission-engine link. Step 5: With the helicopter tethered on the ground, perform thrust propeller calibration of the thrust propeller-transmission-engine link. Step 6: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a ramp scan of the thrust propeller-transmission-engine link. Step 7: With the helicopter tethered on the ground, start the engine and slow down the flight. Operate the helicopter thrust pitch and perform a step-by-step scan of the thrust-transmission-engine link. Step 8: With the helicopter tethered on the ground, start the engine and slow down to a crawl. Maneuver the helicopter thrust pitch back and forth between the specified thrust pitch values ​​to complete the acceleration and deceleration characteristic check of the thrust propeller-transmission-engine link.

2. The method according to claim 1, characterized in that Step 1 includes: Step 1-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current collective pitch value as Clp1 and torque value as Q1. Step 1-2: Slowly increase the collective distance until the torque reaches Q1+10%. Record the current collective distance value as Clp2 and the torque value as Q2 (Q2=Q1+10%). Step 1-3: Continue to slowly increase the collective distance until the torque reaches Q2 + 10%. Record the current collective distance value as Clp3 and the torque value as Q3 (Q3 = Q2 + 10%). Steps 1-4: Increase in sequence until the maximum engine torque Q is reached max , and record the total distance value at maximum torque as Clp max ; Among them, the maximum torque Q max is the torque limit of the engine or helicopter, whichever occurs first; Step 1-5: Based on the torque values ​​Q1, Q2, Q3 ... the maximum engine torque Q max , and helicopter total distance values ​​Clp1, Clp2, Clp3…Clp max , obtain the first engine torque value and helicopter collective pitch table; Step 1-6: With collective and thrust pitch at low, start the engines to flight idle. Step 1-7: Slowly increase the total distance until the torque reaches 30%, and record the current total distance value as clp x ; Step 1-8: Continue to slowly increase the total distance until the torque reaches 50%, and record the current total distance value as clp y ; Step 1-9: According to clp x and clp y , get the second engine torque value and helicopter collective pitch table.

3. The method according to claim 2, characterized in that Step 2 includes: Step 2-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 2-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula a=(Clp max -Clp1) / 30s, calculate the rate a, and increase the helicopter's collective pitch at rate a until the engine torque is Q max ; Step 2-3: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds; Step 2-4: Reduce the helicopter's collective pitch at a rate a until the engine torque is Q1; where a = (Clp max -Clp1) / 30s; Step 2-5: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

4. The method according to claim 2, characterized in that Step 3 includes: Step 3-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 3-2: Based on the data in the first engine torque value and helicopter collective pitch table and the second engine torque value and helicopter collective pitch table, use the formula b = (Clp2 - Clp1) / 5s to calculate the rate b, and increase the helicopter collective pitch at the rate b until the engine torque reaches Q2; Step 3-3: Maintain the helicopter collective pitch at Clp2 and allow the engine to maintain a torque of Q2 for 30 seconds. Step 3-4: Repeat steps 3-2 and 3-3, increasing the engine torque by 10% each time until the engine torque is Q max ; Step 3-5: Maintain the helicopter's collective pitch at Clp max , so that the engine maintains the torque Q max Stable operation for 30 seconds; Step 3-5: Reverse the steps 3-2 and 3-3, reducing the engine torque by 10% each time until the engine torque reaches Q1; Step 3-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

5. The method according to claim 2, characterized in that Step 4 includes: Step 4-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 4-2: Slowly increase the collective pitch to clp x , so that the engine can work stably at 30% torque; Step 4-3: According to the formula e1=(clp y -clp x ) / 5s, calculate the rate e1, and increase the helicopter collective pitch at the rate e1 until the engine torque reaches 50%; Step 4-4: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Step 4-5: Reduce the helicopter collective pitch at rate e1 until the engine torque is 30%; Step 4-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds; Step 4-7: According to the formula e2=(clp y -clp x ) / 2s calculation rate e 2， Increase the helicopter collective pitch at rate e2 until the engine torque reaches 50%; Step 4-8: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Step 4-9: Reduce the helicopter collective pitch at rate e2 until the engine torque is 30%; Step 4-10: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds; Step 4-11: According to the formula e3=(clp y -clp x ) / 1s, calculate the rate e3, and increase the helicopter collective pitch at the rate e3 until the engine torque reaches 50%; Step 4-12: Maintain helicopter collective pitch clp y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Step 4-13: Decrease the helicopter collective pitch at a rate of e3 until the engine torque is 30%; Step 4-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

6. The method according to claim 1, characterized in that Step 5 includes: Step 5-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and record the current thrust pitch value as Cla1 and the torque value as Q1. Step 5-2: Slowly increase the thrust pitch until the torque reaches Q1+10%. Record the current thrust pitch value as Cla2 and the torque value as Q2 (Q2=Q1+10%). Step 5-3: Continue to slowly increase the thrust pitch until the torque reaches Q2 + 10%. Record the current thrust pitch value as Cla3 and the torque value as Q3 (Q3 = Q2 + 10%). Step 5-4: Increase gradually until the maximum engine torque Q is reached max , and record the thrust pitch value at maximum torque as Cla max ; Among them, the maximum torque Q max is the torque limit of the engine or helicopter, whichever occurs first; Step 5-5: According to the torque values ​​Q1, Q2, Q3...Q max , helicopter thrust pitch Cla1, Cla2, Cla3, Cla max , obtaining a first engine torque value and a helicopter thrust pitch table; Steps 5-6: With collective and thrust pitch at low, start the engines to flight idle. Step 5-7: Slowly increase the thrust pitch until the torque reaches 30%, and record the current thrust pitch value as cla x ; Step 5-8: Continue to slowly increase the thrust pitch until the torque reaches 50%, and record the current thrust pitch value as cla y ; Step 5-9: According to Cla x and Cla y , obtain the second engine torque value and helicopter thrust pitch table.

7. The method according to claim 6, characterized in that Step 6 includes: Step 6-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 6-2: Based on the data in the first engine torque value and helicopter thrust pitch table and the second engine torque value and helicopter thrust pitch table, use the formula c=(Cla max -Cla1) / 30s calculate the rate c, and increase the helicopter thrust pitch at rate c until the engine torque is Q max ; Step 6-3: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds; Step 6-4: Reduce the helicopter thrust pitch at a rate c until the engine torque is Q1; Step 6-5: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

8. The method according to claim 6, characterized in that Step 7 includes: Step 7-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 7-2: Calculate the rate d using the formula d = (Cla2 - Cla1) / 5s, and increase the helicopter thrust pitch at the rate d until the engine torque reaches Q2; Step 7-3: Maintain the helicopter thrust pitch at Cla2 and the engine torque at Q2 for 30 seconds. Step 7-4: Repeat steps 7-2 and 7-3, increasing the engine torque by 10% each time until the engine torque reaches Qmax; Step 7-5: Maintain the helicopter thrust pitch at Cla max , so that the engine maintains the torque Q max Stable operation for 30 seconds; Step 7-6: Reverse the steps 7-2 and 7-3, reducing the engine torque by 10% each time until the engine torque reaches Q1; Step 7-6: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

9. The method according to claim 6, characterized in that Step 8 includes: Step 8-1: With the collective pitch and thrust pitch at low, start the engine to flight idle and maintain stable engine operation. Step 8-2: Slowly raise the collective distance to cla x , so that the engine can work stably at 30% torque; Step 8-3: Use the formula f1=(cla y -cla x ) / 5s, calculate the rate f1, and increase the helicopter collective pitch at the rate f1 until the engine torque reaches 50%; Step 8-4: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Step 8-5: Reduce the helicopter collective pitch at a rate of f1 until the engine torque reaches 30%; Step 8-6: Maintain helicopter collective pitch clp x , so that the engine maintains a torque of 30% and works stably for 15 seconds; Step 4-7: Use the formula f2 = (cla y -cla x ) / 2s, calculate the rate f2, and increase the helicopter collective pitch at the rate f2 until the engine torque reaches 50%; Step 8-8: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Steps 8-9: Decrease the helicopter collective pitch at rate f2 until the engine torque is 30%; Steps 8-10: Maintain helicopter collective distance cla x , so that the engine maintains a torque of 30% and works stably for 15 seconds; Step 8-11: Use the formula f3 = (cla y -cla x ) / 1s, calculate the rate f3, and increase the helicopter collective pitch at the rate f3 until the engine torque reaches 50%; Steps 8-12: Maintain helicopter collective distance cla y , so that the engine maintains a torque of 50% and works stably for 15 seconds; Step 8-13: Decrease the helicopter collective pitch at rate f3 until the engine torque is 30%; Step 8-14: The collective pitch and thrust pitch are in the low pitch state to maintain stable engine operation.

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