A flight test verification method for endurance index of a fuel-powered unmanned aerial vehicle

Abstract

The application discloses a kind of fuel-powered unmanned aerial vehicle endurance index test flight verification methods, it is related to unmanned aerial vehicle design field, including: establishing the mathematical model of endurance calculation, analytical endurance calculation mathematical model, maximum weight take-off is completed test flight according to planned endurance, minimum weight landing is completed test flight according to planned endurance, obtain actual flight comprehensive hourly fuel consumption, obtain the maximum endurance of fuel-powered unmanned aerial vehicle endurance index test flight verification method, judge whether to meet unmanned aerial vehicle endurance index.The application plans two flights of maximum weight take-off and minimum weight landing, obtains the average hourly fuel consumption of two flights respectively, shortens the flight length.Both assess the maximum weight take-off capacity of unmanned aerial vehicle, climbing capacity, and verify the large weight cruise and small weight cruise capacity of unmanned aerial vehicle, finally give the calculation formula of maximum endurance, carry out segmented data processing to total endurance fuel quantity, and the obtained maximum endurance data is accurate and available.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a flight test verification method for a fuel-powered UAV's flight time index. Background Art

[0002] The flight time of a fuel-powered UAV is closely related to its weight and aerodynamic characteristics, fuel load, engine power and fuel consumption, and propeller efficiency. During the UAV flight test or performance verification phase, the UAV's technical status is relatively solid, and the above factors affecting flight time are relatively convergent. Therefore, the flight time test method used is crucial.

[0003] Undoubtedly, if a fuel-powered drone conducts a full-flight profile—taking off at maximum weight and landing at minimum weight—and the actual flight duration is greater than or equal to the flight duration requirement, then it can be directly proven to have met the flight duration requirement. However, because most drones have long flight times, sometimes 20 to 30 hours, and because flight airspace is controlled by relevant agencies such as the Civil Aviation Administration of China, the flight space is relatively small, and test flight time is limited, drones are often unable to fly the full flight duration.

[0004] Since fuel-powered drones have a relatively fixed unit fuel consumption during cruising, flight test departments can use the principle that the average hourly fuel consumption at the intermediate weight during the drone test flight represents the average hourly fuel consumption for the entire flight time, and use the intermediate weight test flight method to determine the maximum flight time. However, this method also has shortcomings. First, the takeoff weight of the intermediate weight test flight method does not reach the maximum weight, and it cannot prove that the drone has the ability to take off and climb at the maximum weight. Second, the weight range of the intermediate weight test flight method is relatively small, and it cannot prove that the drone has the ability to cruise within the full weight range. Summary of the Invention

[0005] In view of this, the present invention provides a flight test verification method for fuel-powered UAV flight time indicators. This method addresses the problem of how to truly and objectively reflect the flight profile of a fuel-powered UAV during its actual flight time under the objective conditions of limited flight test airspace and flight time, ensuring that the flight test data is accurate and available, while also utilizing the limited flight test airspace and time to obtain accurate maximum flight time data for the fuel-powered UAV during the flight test through scientific and reasonable flight test planning. The present invention provides a flight test verification method for fuel-powered UAV flight time indicators, plans two sorties, namely, maximum weight takeoff and minimum weight landing, and obtains the average hourly fuel consumption of the two sorties, thereby shortening the flight verification time of the fuel-powered UAV. It not only assesses the maximum weight takeoff capability and climb capability of the fuel-powered UAV, but also verifies the high-weight cruise and low-weight cruise capabilities of the fuel-powered UAV. Ultimately, a calculation formula for the maximum flight time is provided, and segmented data processing is performed on the full flight time fuel quantity, so that the obtained maximum flight time data is accurate and available.

[0006] The technical solutions of the present invention are as follows:

[0007] A flight test verification method for a fuel-powered UAV flight time indicator includes the following parts:

[0008] Step S1: Establishing a mathematical model for flight time calculation;

[0009] Step S2: Analyze the mathematical model of flight time calculation;

[0010] Step S3: planning the first flight test: taking off at maximum weight and completing the flight test according to the planned flight time, and calculating the average hourly fuel consumption q1 of the first flight;

[0011] Step S4: planning the second flight test: completing the flight test with minimum landing weight and within the planned flight time, and calculating the average hourly fuel consumption q2 of the second flight, where the takeoff weight is calculated based on the mathematical model for flight time calculation;

[0012] Step S5: Calculate the actual flight comprehensive hourly fuel consumption;

[0013] Step S6: Calculating the maximum flight time of the weight-segment-based flight test planning method;

[0014] Step S7: Determine whether the drone flight time index is met.

[0015] Furthermore, according to the drone parameters, including:

[0016] UAV flight time index T 指标 、UAV empty weight M 空机 、UAV maximum refueling capacity M 满油 、UAV backup fuel M 备份 , flight duration of flight test plan 规划 , the first actual flight time t 实飞1 , the second flight time 实飞2 .

[0017] Furthermore, the step S1 includes:

[0018] A mathematical model for flight time calculation is established. The mathematical model is as follows:

[0019]

[0020] in:

[0021] t CR Is the endurance time, unit: hours;

[0022] L is the cruise lift, unit: Newton;

[0023] D is the cruise resistance, unit: Newton;

[0024] C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour);

[0025] g is the acceleration due to gravity, unit: meter / second squared;

[0026] M fCR is the ratio of the starting weight to the ending weight;

[0027] ln(M fCR ) is the natural logarithmic function of the ratio of the starting weight to the ending weight.

[0028] Furthermore, the step S2 includes:

[0029] According to the UAV's empty weight M 空机 、Maximum refueling volume M 满油 , backup fuel M 备份 and UAV flight time indicators, parsing the data model for flight time calculation.

[0030] Furthermore, the UAV flight time index T 指标 The corresponding starting weight M 起始 Use empty weight M 空机 Plus the maximum refueling volume M 满油 , end weight M 结束 Use empty weight M 空机 Plus reserve fuel M 备份 ,Right now:

[0031] M 起始 =M 空机 +M 满油

[0032] M 结束 =M 空机 +M 备份

[0033]

[0034] in:

[0035] M 空机 Use the empty weight of the drone in kilograms;

[0036] M 满油 The maximum refueling capacity of the drone, in kilograms;

[0037] M 备份 Backup fuel for the drone, unit: kilogram;

[0038] M 起始 The starting weight of the drone, i.e. the weight at the start of flight, in kilograms;

[0039] M 结束 The ending weight of the drone, i.e. the weight at the end of the flight: unit: kilograms;

[0040] T 指标 It is the flight time index of the UAV, unit: hour;

[0041] L is the cruise lift, unit: Newton;

[0042] D is the cruise resistance, unit: Newton;

[0043] C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour);

[0044] g is the acceleration due to gravity, unit: meter / second squared;

[0045] is the natural logarithmic function of the ratio of the starting weight to the ending weight;

[0046] The flight time that can be maintained per unit logarithmic weight ratio, unit: hours.

[0047] Furthermore, the step S3 includes:

[0048] Step S31: The first flight completes full fueling before takeoff according to the planned flight time;

[0049] Step S32: Obtain flight time data t for the first actual flight 实飞1 ;

[0050] Step S33: After the first landing, the landing weight M is obtained by weighing 着陆1 , and calculate the remaining fuel M 余油1 ;

[0051] Step S34: Calculate the actual flight average hourly fuel consumption q1 of the first flight.

[0052] Furthermore, the step S31 includes:

[0053] The refueling amount is full M 满油 , takeoff weight with full fuel M 起飞1 for:

[0054] M 起飞1 =M 空机 +M 满油 ;

[0055] in:

[0056] M 起飞1 The take-off weight of the UAV for the first time, in kilograms;

[0057] M空机 Use the empty weight of the drone in kilograms;

[0058] M 满油 The maximum refueling capacity of the drone, in kilograms.

[0059] Furthermore, the step S32 includes:

[0060] From takeoff time t 起飞1 Start, to landing touchdown time t 着陆1 End, the first actual flight time t 实飞1 Equal to the landing touchdown time t 着陆1 Subtract the takeoff time t 起飞1 .

[0061] It is required that the actual flight time of the first flight be close to but not greater than the flight time planned for the test flight.

[0062] Furthermore, the actual flight time of the first sortie is t 起飞1 Calculated by the following formula:

[0063] t 实飞1 =t 着陆1 -t 起飞1 ;

[0064] in:

[0065] t 实飞1 The actual flight time of the first flight, unit: hour;

[0066] t 着陆1 The first landing time, in hours, minutes and seconds;

[0067] t 起飞1 The first take-off time, in hours, minutes and seconds.

[0068] Furthermore, the step S33 includes:

[0069] M 余油1 =M 着陆1 -M 空机 ;

[0070] in:

[0071] M 余油1 The remaining fuel for the first flight, in kilograms;

[0072] M 着陆1 The first landing weight, unit: kilogram;

[0073] M 空机 Use the empty weight for the drone in kilograms.

[0074] Furthermore, the step S34 includes:

[0075]

[0076] in:

[0077] q1 is the average hourly fuel consumption of the first flight, unit: kg / hour;

[0078] M 起飞1 The take-off weight of the first sortie, unit: kilogram;

[0079] M 着陆1 The first landing weight, unit: kilogram;

[0080] t 实飞1 It is the actual flight time of the first flight, unit: hour.

[0081] Furthermore, the step S4 includes:

[0082] Step S41: refueling before the second flight takes off, and the take-off weight is calculated based on the mathematical model of flight time calculation;

[0083] Step S42: The second flight is completed according to the planned flight time to obtain the flight time data t 实飞2 ;

[0084] Step S43: After the second landing, obtain the landing weight M by weighing 着陆2 , and calculate the remaining fuel M 余油2 ;

[0085] Step S44: Calculate the actual flight average hourly fuel consumption q2 of the second flight.

[0086] Furthermore, the step S41 includes:

[0087] Takeoff weight M 起飞2 The principle should ensure that the UAV has a flight time of t 规划 After that, the landing weight is close to M 空机 +M 备份 According to the mathematical model of flight time calculation, take-off weight M 起飞2 for:

[0088]

[0089] Furthermore, the refueling amount M 加油量2 for:

[0090] M 加油量2 =M 起飞2 -M 空机 .

[0091] in:

[0092] M 空机 Use the empty weight of the drone in kilograms;

[0093] M 备份 Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilogram;

[0094] t 规划 The flight duration planned for the test flight, in hours;

[0095] K is the flight time that can be maintained per unit logarithmic weight ratio, unit: hour;

[0096] e is the base of the natural logarithm function, which is approximately equal to 2.71828;

[0097] M 加油量2 The amount of fuel added for the second flight of the UAV, unit: kilograms;

[0098] M 起飞2 The take-off weight of the second UAV, in kilograms;

[0099] Furthermore, the step S42 includes:

[0100] From takeoff time t 起飞2 Start, to landing touchdown time t 着陆2 End, the second flight time t 实飞2 Equal to the landing touchdown time t 着陆2 Subtract the takeoff time t 起飞2 .

[0101] The actual flight time of the second sortie is required to be close to but not greater than the flight time planned for the test flight.

[0102] Furthermore, the actual flight time of the second sortie is t 实飞2 Calculated by the following formula:

[0103] t 实飞2 =t 着陆2 -t 起飞2 ;

[0104] in:

[0105] t 实飞2 The actual flight time of the second flight, unit: hour;

[0106] t 着陆2 The second landing time, in hours, minutes and seconds;

[0107] t 起飞2 The take-off time of the second flight, in hours, minutes and seconds.

[0108] Furthermore, the step S43 includes:

[0109] M 余油2 =M 着陆2 -M 空机 ;

[0110] in:

[0111] M 余油2 The remaining fuel for the second flight, in kilograms;

[0112] M 着陆2 The landing weight of the second sortie, unit: kilogram;

[0113] M 空机 Use the empty weight for the drone in kilograms.

[0114] Furthermore, the step S44 includes:

[0115]

[0116] in:

[0117] q2 is the average hourly fuel consumption of the second flight, in kg / hour;

[0118] M 起飞2 The take-off weight of the second sortie, unit: kilogram;

[0119] t 着陆2 The second landing time, in hours, minutes and seconds;

[0120] t 实飞2 The actual flight time of the second flight, unit: hour.

[0121] Furthermore, the step S5 includes:

[0122] Actual flight comprehensive hourly fuel consumption q 综合 Equal to the average of the actual flight average hourly fuel consumption of the first and second sorties:

[0123]

[0124] in:

[0125] q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour;

[0126] q1 is the average hourly fuel consumption of the first flight, unit: kg / hour;

[0127] q2 is the average hourly fuel consumption of the second flight, unit: kg / hour.

[0128] Furthermore, the step S6 includes:

[0129] The maximum flight time T of fuel-powered UAV obtained by flight test verification method of fuel-powered UAV flight time index 试飞 :

[0130]

[0131] in:

[0132] T 试飞 The maximum flight time of fuel-powered UAV, unit: hours;

[0133] M 满油 The maximum refueling capacity of the drone, in kilograms;

[0134] M 余油 The remaining fuel for the second flight, in kilograms;

[0135] q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour;

[0136] M 备份 Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilogram;

[0137] q2 is the average hourly fuel consumption of the second flight, unit: kg / hour.

[0138] Furthermore, the step S7 includes:

[0139] If the maximum flight time of a fuel-powered unmanned aerial vehicle obtained by the flight time index test flight verification method of a fuel-powered unmanned aerial vehicle is ≥ the flight time index of the unmanned aerial vehicle, then the flight time index of the unmanned aerial vehicle can be achieved; otherwise, the unmanned aerial vehicle does not meet the flight time index.

[0140] Compared with the existing technology, the beneficial effects of the present invention are:

[0141] 1. The present invention is based on actual flight verification, taking into account both maximum weight takeoff and minimum weight landing. While effectively verifying the flight time indicators, it also assesses flight performance such as maximum weight takeoff capability and climb capability, and verifies the heavy weight cruise capability and light weight cruise capability. The assessment is more comprehensive and closer to the flight profile of the actual full flight time.

[0142] 2. The present invention establishes a mathematical model for flight time calculation, clarifies the takeoff refueling amount, and plans the test flight process. It is scientific and reasonable, the process is complete, and it effectively shortens the flight time of actual flight verification. It also proposes conditions for whether the UAV flight time indicators meet the standards. The conditions are clear and the judgment criteria are feasible.

[0143] 3. The present invention is applicable to fuel-powered UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0144] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments described in the embodiments of the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0145] Figure 1 This is a flow chart of the flight test verification method for fuel-powered UAV flight time indicators. DETAILED DESCRIPTION

[0146] The present invention will be further described with reference to the accompanying drawings and embodiments. Obviously, the embodiments described are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those skilled in the art should fall within the scope of protection of the embodiments of the present invention.

[0147] See also Figure 1 A flight test verification method for a fuel-powered UAV flight time indicator includes the following steps:

[0148] Step S1: Establishing a mathematical model for flight time calculation;

[0149] Step S2: Analyze the mathematical model of flight time calculation;

[0150] Step S3: planning the first flight test: taking off at maximum weight and completing the flight test according to the planned flight time, and calculating the average hourly fuel consumption q1 of the first flight;

[0151] Step S4: planning the second flight test: completing the flight test with minimum landing weight and within the planned flight time, and calculating the average hourly fuel consumption q2 of the second flight, where the takeoff weight is calculated based on the mathematical model for flight time calculation;

[0152] Step S5: Calculate the actual flight comprehensive hourly fuel consumption;

[0153] Step S6: Calculating the maximum flight time of the weight-segment-based flight test planning method;

[0154] Step S7: Determine whether the drone flight time index is met.

[0155] In this embodiment, specifically, according to the drone parameters, the following are included:

[0156] UAV flight time index T 指标 , unit: hour;

[0157] UAV empty weight M 空机 , unit: kilogram;

[0158] Maximum refueling capacity of drone M 满油, unit: kilogram;

[0159] UAV backup fuel M 备份 , unit: kilogram;

[0160] Flight duration of test flight planning 规划 , unit: hour.

[0161] The first actual flight time 实飞1 , unit: hour;

[0162] The second flight time 实飞2 , unit: hour.

[0163] In this embodiment, specifically, step S1 includes:

[0164] A mathematical model for flight time calculation is established. The mathematical model is as follows:

[0165]

[0166] in:

[0167] t CR Is the endurance time, unit: hours;

[0168] L is the cruise lift, unit: Newton;

[0169] D is the cruise resistance, unit: Newton;

[0170] C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour);

[0171] g is the acceleration due to gravity, unit: meter / second squared;

[0172] M fCR is the ratio of the starting weight to the ending weight;

[0173] ln(M fCR ) is the natural logarithmic function of the ratio of the starting weight to the ending weight.

[0174] In this embodiment, specifically, step S2 includes:

[0175] According to the empty weight M of the UAV 空机 、UAV maximum fuel capacity M 满油 、UAV backup fuel M 备份 and UAV flight time indicators, parsing the data model for flight time calculation.

[0176] UAV flight time index T 指标 The corresponding starting weight M 起始 Use empty weight M 空机Plus the maximum refueling volume M 满油 , end weight M 结束 Use empty weight M 空机 Plus reserve fuel M 备份 ,Right now:

[0177] M 起始 =M 空机 +M 满油

[0178] M 结束 =M 空机 +M 备份

[0179]

[0180] in:

[0181] M 空机 Use the empty weight of the drone in kilograms;

[0182] M 满油 The maximum refueling capacity of the drone, in kilograms;

[0183] M 备份 Backup fuel for the drone, unit: kilogram;

[0184] M 起始 The starting weight of the drone, i.e. the weight at the start of flight, in kilograms;

[0185] M 结束 The ending weight of the drone, i.e. the weight at the end of the flight: unit: kilograms;

[0186] T 指标 It is the flight time index of the UAV, unit: hour;

[0187] L is the cruise lift, unit: Newton;

[0188] D is the cruise resistance, unit: Newton;

[0189] C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour);

[0190] g is the acceleration due to gravity, unit: meter / second squared;

[0191] is the natural logarithmic function of the ratio of the starting weight to the ending weight;

[0192] The flight time that can be maintained per unit logarithmic weight ratio, unit: hours.

[0193] During cruising, L / D and C CRRelatively fixed, g is a constant, so the K value is relatively fixed and is a constant.

[0194] In this embodiment, specifically, step S3 includes:

[0195] Step S31: Fill up the fuel tank before the first flight takes off;

[0196] Step S32: The first flight is completed according to the planned flight time to obtain flight time data t 实飞1 ;

[0197] Step S33: After the first landing, the landing weight M is obtained by weighing 着陆1 , and calculate the remaining fuel M 余油1 ;

[0198] Step S34: Calculate the actual flight average hourly fuel consumption q1 of the first flight.

[0199] In this embodiment, specifically, step S31 includes:

[0200] M 起飞1 =M 空机 +M 满油 .

[0201] in:

[0202] M 起飞1 The takeoff weight of the UAV with full fuel, in kilograms;

[0203] M 空机 Use the empty weight of the drone in kilograms;

[0204] M 满油 The maximum refueling capacity of the drone, in kilograms.

[0205] In this embodiment, specifically, step S32 includes:

[0206] The drone takes off from the ground at t 起飞1 Start, to landing touchdown time t 着陆1 End, the first actual flight time t 实飞1 Equal to the landing touchdown time t 着陆1 Subtract the takeoff time t 起飞1 .

[0207] It should be noted that the altitude during the cruising phase is the long-term cruising altitude (favorable flight time altitude), and the speed during the cruising phase is the long-term cruising speed (favorable flight time speed).

[0208] Required actual flight time 实飞1 Less than or equal to the flight time t of the test flight plan 规划Preferably, the actual flight time is required to be close to but not greater than the flight time of the test flight plan, for example, it is required to be between 0.95 and 1 times of the flight time of the test flight plan, that is, 0.95×t 规划 ≤t 实飞1 ≤t 规划 .

[0209] In this embodiment, specifically, the actual flight time of the first sortie is t 实飞1 Calculated by the following formula:

[0210] t 实飞1 =t 着陆1 -t 起飞1

[0211] in:

[0212] t 实飞1 The actual flight time of the first flight, unit: hour;

[0213] t 着陆1 The first landing time, in hours, minutes and seconds;

[0214] t 起飞1 The first take-off time, in hours, minutes and seconds.

[0215] In this embodiment, specifically, step S33 includes:

[0216] M 余油1 =M 着陆1 -M 空机 ;

[0217] in:

[0218] M 余油1 The remaining fuel for the first flight, in kilograms;

[0219] M 着陆1 The first landing weight, unit: kilogram;

[0220] M 空机 Use the empty weight for the drone in kilograms.

[0221] In this embodiment, specifically, step S34 includes:

[0222]

[0223] in:

[0224] q1 Average hourly fuel consumption of the first flight, unit: kg / hour;

[0225] M 起飞1 The take-off weight of the first sortie, unit: kilogram;

[0226] M 着陆1 The first landing weight, unit: kilogram;

[0227] t 实飞1 It is the actual flight time of the first flight, unit: hour.

[0228] In this embodiment, specifically, step S4 includes:

[0229] Step S41: refueling before the second flight takes off, and the take-off weight is calculated based on the mathematical model of flight time calculation;

[0230] Step S42: The second flight is completed according to the planned flight time to obtain the flight time data t 实飞2 ;

[0231] Step S43: After the second landing, obtain the landing weight M by weighing 着陆2 , and calculate the remaining fuel M 余油2 ;

[0232] Step S44: Calculate the actual flight average hourly fuel consumption q2 of the second flight.

[0233] In this embodiment, specifically, step S41 includes:

[0234] Takeoff weight M 起飞2 The principle should ensure that the UAV has a flight time of t 规划 After that, the landing weight is close to M 空机 +M 备份 According to the mathematical model of flight time calculation, take-off weight M 起飞2 for:

[0235]

[0236] Furthermore, the refueling amount M 加油量2 for:

[0237] M 加油量2 =M 起飞2 -M 空机 .

[0238] in:

[0239] M 空机 Use the empty weight of the drone in kilograms;

[0240] M 备份 Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilogram;

[0241] t 规划 The flight duration planned for the test flight, in hours;

[0242] K is the flight time that can be maintained per unit logarithmic weight ratio, unit: hour;

[0243] e is the base of the natural logarithm function, which is approximately equal to 2.71828;

[0244] M 加油量2 The amount of fuel added for the second flight of the UAV, unit: kilograms;

[0245] M 起飞2 The take-off weight of the second UAV, in kilograms;

[0246] In this embodiment, specifically, step S42 includes:

[0247] From takeoff time t 起飞2 Start, to landing touchdown time t 着陆2 End, the second flight time t 实飞2 Equal to the landing touchdown time t 着陆2 Subtract the takeoff time t 起飞2 time.

[0248] It should be noted that the altitude during the cruising phase is the long-term cruising altitude (favorable flight time altitude), and the speed during the cruising phase is the long-term cruising speed (favorable flight time speed).

[0249] Required actual flight time 实飞2 Less than or equal to the flight time t of the test flight plan 规划 Preferably, the actual flight time is required to be close to but not greater than the flight time of the test flight plan, for example, it is required to be between 0.95 and 1 times of the flight time of the test flight plan, that is, 0.95×t 规划 ≤t 实飞2 ≤t 规划 .

[0250] In this embodiment, specifically, the actual flight time of the second sortie is t 实飞2 Calculated by the following formula:

[0251] t 实飞2 =t 着陆2 -t 起飞2 ;

[0252] in:

[0253] t 起飞2 The actual flight time of the second flight, unit: hour;

[0254] t 着陆2 The second landing time, in hours, minutes and seconds;

[0255] t 起飞2 The take-off time of the second flight, in hours, minutes and seconds.

[0256] In this embodiment, specifically, step S43 includes:

[0257] M 余油2 =M 着陆2 -M 空机

[0258] in:

[0259] M 余油2 The remaining fuel for the second flight, in kilograms;

[0260] M 着陆2 The landing weight of the second sortie, unit: kilogram;

[0261] M 空机 Use empty weight for the drone.

[0262] In this embodiment, specifically, step S44 includes:

[0263]

[0264] in:

[0265] q2 is the average hourly fuel consumption of the second flight, in kg / hour;

[0266] M 起飞2 The take-off weight of the second sortie, unit: kilogram;

[0267] M 着陆2 The landing weight of the second sortie, unit: kilogram;

[0268] t 实飞2 The actual flight time of the second flight, unit: hour.

[0269] In this embodiment, specifically, step S5 includes:

[0270]

[0271] in:

[0272] q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour;

[0273] q1 is the average hourly fuel consumption of the first flight, unit: kg / hour;

[0274] q2 is the average hourly fuel consumption of the second flight, unit: kg / hour.

[0275] In this embodiment, specifically, step S6 includes:

[0276]

[0277] in:

[0278] T 试飞 The maximum flight time of fuel-powered UAV, unit: hours;

[0279] M 满油 The maximum fuel volume of the drone, in kilograms;

[0280] M 余油2 The remaining fuel for the second flight, in kilograms;

[0281] q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour;

[0282] M 备份 Backup fuel for the drone, unit: kilogram;

[0283] q2 Average hourly fuel consumption of the second flight, unit: kg / hour.

[0284] It should be noted that the above formula for calculating the maximum flight time is more universal and is applicable to the remaining fuel M for the second flight. 余油2 Greater than M 备份 The same applies to the remaining fuel M for the second flight. 余油2 Less than or equal to M 备份 situation.

[0285] In this embodiment, specifically, step S7 includes:

[0286] If the maximum flight time of the fuel-powered UAV flight time index test flight verification method ≥ the flight time index, then the fuel-powered UAV flight time index can be achieved; otherwise, the UAV does not meet the flight time index.

[0287] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered by the scope of protection of the claims of the present invention.

Claims

1. A flight test verification method for fuel-powered UAV flight time indicators, characterized in that: include: Step S1: Establishing a mathematical model for flight time calculation; Step S2: Analyze the mathematical model of flight time calculation; Step S3: planning the first flight test: taking off at maximum weight and completing the flight test according to the planned flight time, and calculating the average hourly fuel consumption q1 of the first flight; Step S4: planning the second flight test: completing the flight test with minimum landing weight and within the planned flight time, and calculating the average hourly fuel consumption q2 of the second flight, where the takeoff weight is calculated based on the mathematical model for flight time calculation; Step S5: Calculate the actual flight comprehensive hourly fuel consumption; Step S6: Calculating the maximum flight time of the weight-segment-based flight test planning method; Step S7: Determine whether the drone flight time index is met; The step S6 comprises: The maximum flight time T of a fuel-powered UAV calculated based on the flight time index test verification method of a fuel-powered UAV 试飞 : in: T 试飞 The maximum flight time of fuel-powered UAV, unit: hours; M 满油 The maximum refueling capacity of the drone, in kilograms; M 余油2 The remaining fuel for the second flight, in kilograms; q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour; M 备份 Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilogram; q2 is the average hourly fuel consumption of the second flight, unit: kg / hour.

2. The flight time index test flight verification method of a fuel-powered UAV according to claim 1 is characterized in that: The step S1 comprises: The mathematical model for flight time calculation is established as follows: in: t CR Is the endurance time, unit: hours; L is the cruise lift, unit: Newton; D is the cruise resistance, unit: Newton; C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour); g is the acceleration due to gravity, unit: meter / second squared; M fCR is the ratio of the drone’s starting weight to its ending weight; ln(M fCR ) is the natural logarithm function of the ratio of the starting weight to the ending weight of the UAV.

3. The flight time index test flight verification method of a fuel-powered UAV according to claim 1 is characterized in that: The step S2 includes: According to the empty weight M of the UAV 空机 、Maximum refueling volume M 满油 , backup fuel M 备份 And the UAV flight time indicators, the data model for analyzing flight time calculation is: M 起始 =M 空机 +M 满油 ; M 结束 =M 空机 +M 备份 ; in: M 空机 Use the empty weight of the drone in kilograms; M 满油 The maximum refueling capacity of the drone, in kilograms; M 备份 Backup fuel for the drone, unit: kilogram; M 起始 The starting weight of the drone, i.e. the weight at the start of flight, in kilograms; M 结束 The ending weight of the drone, i.e. the weight at the end of the flight: unit: kilograms; T 指标 It is the flight time index of the UAV, unit: hour; L is the cruise lift, unit: Newton; D is the cruise resistance, unit: Newton; C CR Fuel consumption per unit pulling force, unit: kg / (Newton × hour); g is the acceleration due to gravity, unit: meter / second squared; is the natural logarithmic function of the ratio of the starting weight to the ending weight; The flight time that can be maintained per unit logarithmic weight ratio, unit: hours.

4. The flight time indicator test flight verification method for a fuel-powered UAV according to claim 1 is characterized in that: The step S3 comprises: Step S31: refueling before the first flight takes off; Step S32: The first flight is completed according to the planned flight time to obtain flight time data t 实飞1 ; Step S33: After the first landing, the landing weight M is obtained by weighing 着陆1 , and calculate the remaining fuel M 余油1 ; Step S34: Calculate the actual flight average hourly fuel consumption q1 of the first flight.

5. The flight time index test flight verification method of a fuel-powered UAV according to claim 4 is characterized in that: include: The step S31 includes: Adding amount is full oil M 满油 , takeoff weight M 起飞1 for: M 起飞1 =M 空机 +M 满油 ; in: M 起飞1 The take-off weight of the UAV for the first time, in kilograms; M 空机 Use the empty weight of the drone in kilograms; M 满油 The maximum refueling capacity of the drone, in kilograms; The step S32 includes: From takeoff time t 起飞1 Start, to landing touchdown time t 着陆1 End, the first actual flight time t 实飞1 Equal to the landing touchdown time t 着陆1 Subtract the takeoff time t 起飞1 ; The actual flight time of the first sortie is required to be close to but not greater than the flight time of the test flight plan; The actual flight time of the first sortie is t 实飞1 Calculated by the following formula: t 实飞1 =t 看陆1 -t 起飞1 ; in: t 实飞1 The actual flight time of the first flight, unit: hour; t 着陆1 The first landing time, in hours, minutes and seconds; t 起飞1 The first take-off time, in hours, minutes and seconds; The step S33 includes: M 余油1 =M 着陆1 -M 空机 ; M 余油1 The remaining fuel for the first flight, in kilograms; M 着陆1 The first landing weight, unit: kilogram; M 空机 Empty weight of the drone, in kilograms; The step S34 includes: in: q1 is the average hourly fuel consumption of the first flight, unit: kg / hour; M 起飞1 The take-off weight of the first sortie, unit: kilogram; M 着陆1 The first landing weight, unit: kilogram; t 实飞1 It is the actual flight time of the first flight, unit: hour.

6. The flight time indicator test flight verification method for a fuel-powered UAV according to claim 1 is characterized in that: The step S4 comprises: Step S41: refueling before the second flight takes off, and the take-off weight is calculated based on the mathematical model of flight time calculation; Step S42: The second flight is completed according to the planned flight time to obtain the flight time data t 实飞2 ; Step S43: After the second landing, obtain the landing weight M by weighing 着陆2 , and calculate the remaining fuel M 余油2 ; Step S44: Calculate the actual flight average hourly fuel consumption q2 of the second flight.

7. The flight time indicator test flight verification method for a fuel-powered UAV according to claim 6 is characterized in that: include: The step S41 includes: Takeoff weight M 起飞2 The principle should ensure that the UAV has a flight time of t 规划 After that, the landing weight is close to M 空机 +M 备份 ; According to the mathematical model of flight time calculation, take-off weight M 起飞2 for: Fuel quantity M 加油量2 for: M 加油量2 =M 起飞2 -M 空机 ; in: M 空机 Use the empty weight of the drone in kilograms; M 备份 Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilogram; t 规划 The flight duration planned for the test flight, in hours; K is the flight time that can be maintained by unit logarithmic weight ratio, unit: hour; e is the base of the natural logarithm function, which is approximately equal to 2.71828; M 加油量2 The amount of fuel added for the second flight of the UAV, unit: kilograms; M 起飞2 The take-off weight of the second UAV, in kilograms; The step S42 includes: From takeoff time t 起飞2 Start, to landing touchdown time t 着陆2 End, the second flight time t 实飞2 Equal to the landing touchdown time t 着陆2 Subtract the takeoff time t 起飞2 ; The actual flight time of the second sortie is required to be close to but not greater than the flight time of the test flight plan; The actual flight time of the second sortie is t 实飞2 Calculated by the following formula: t 实飞2 =t 着陆2 -t 起飞2 ; in: t 实飞2 The actual flight time of the second flight, unit: hour; t 着陆2 The second landing time, in hours, minutes and seconds; t 起飞2 The take-off time of the second flight, in hours, minutes and seconds; The step S43 includes: M 余油2 =M 着陆2 -M 空机 ; in: M 余油2 The remaining fuel for the second flight, in kilograms; M 着陆2 The landing weight of the second sortie, unit: kilogram; M 空机 Use the empty weight of the drone in kilograms; The step S44 includes: in: q2 is the average hourly fuel consumption of the second flight, in kg / hour; M 起飞2 The take-off weight of the second sortie, unit: kilogram; M 着陆2 The landing weight of the second sortie, unit: kilogram; t 实飞2 The actual flight time of the second flight, unit: hour.

8. The flight time index test and verification method of a fuel-powered UAV according to claim 1 is characterized in that: The step S5 comprises: Actual flight comprehensive hourly fuel consumption q 综合 Equal to the average of the actual flight average hourly fuel consumption of the first and second sorties: in: q 综合 It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour; q1 is the average hourly fuel consumption of the first flight, unit: kg / hour; q2 is the average hourly fuel consumption of the second flight, unit: kg / hour.

9. The flight time indicator test flight verification method for a fuel-powered UAV according to claim 1, characterized in that: The step S7 includes: If the maximum flight time of a fuel-powered UAV obtained by the flight time index test flight verification method of a fuel-powered UAV is ≥ the flight time index of the UAV, then the flight time index of the UAV can be achieved; otherwise, the UAV does not meet the flight time index.

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