Fuel-powered unmanned aerial vehicle endurance index test flight verification method

Abstract

The invention discloses a flight time index test flight verification method for a fuel-powered unmanned aerial vehicle, and relates to the field of unmanned aerial vehicle design. Comprising the following steps: establishing a mathematical model for flight time calculation, analyzing the mathematical model for flight time calculation, performing maximum-weight takeoff test flight, minimum-weight landing test flight, solving actual flight comprehensive hour fuel consumption, solving the maximum flight time of the fuel-powered unmanned aerial vehicle flight time index test flight verification method, and judging whether the flight time index of the unmanned aerial vehicle is met or not. According to the method, two sorties of maximum-weight takeoff and minimum-weight landing are planned, the average hourly oil consumption of the two sorties is obtained respectively, and the flight duration is shortened. The maximum-weight takeoff capability and climbing capability of the unmanned aerial vehicle are examined, the large-weight cruising capability and the small-weight cruising capability of the unmanned aerial vehicle are verified, a calculation formula of the maximum endurance is finally given, segmented data processing is carried out on the full-endurance fuel quantity, and the obtained maximum endurance data are accurate and available.

Description

Technical Field

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

[0002] The flight time of a fuel-powered unmanned aerial vehicle is closely related to the weight and aerodynamic characteristics of the unmanned aerial vehicle, the fuel loading, the engine power and fuel consumption, and the propeller efficiency. During the flight test stage or performance verification stage of the unmanned aerial vehicle, the technical state of the unmanned aerial vehicle is relatively fixed, and the above factors affecting the flight time are relatively convergent. Therefore, it is crucial to adopt a flight time flight test method.

[0003] Undoubtedly, if a fuel-powered unmanned aerial vehicle conducts a full flight time flight profile, that is, takes off at the maximum weight, lands at the minimum weight, and the actual flight duration is greater than or equal to the requirement of the flight time index, then it can directly prove that the flight time of the unmanned aerial vehicle meets the standard. However, on the one hand, due to the relatively long flight time of most unmanned aerial vehicles, often twenty or thirty hours; on the other hand, the flight airspace is controlled by relevant agencies such as civil aviation, and the flight airspace is small, and the flight test time is limited. Therefore, the unmanned aerial vehicle often cannot fly the entire flight time.

[0004] Since the fuel consumption per unit time of a fuel-powered unmanned aerial vehicle is relatively fixed during cruising, the flight test department can use the intermediate weight during the flight test of the unmanned aerial vehicle, and the corresponding average hourly fuel consumption represents the average hourly fuel consumption of the full flight time. The method of conducting a flight test with the intermediate weight is used to obtain the maximum flight time. However, this method also has deficiencies. First, the takeoff weight of the intermediate weight flight test method does not reach the maximum weight, and it cannot prove that the unmanned aerial vehicle has the takeoff ability and climbing ability at the maximum weight. Second, the weight range of the intermediate weight flight test method is small, and it cannot prove that the unmanned aerial vehicle has the cruising ability in the full weight range. Summary of the Invention

[0005] In view of this, the present invention provides a method for flight time index flight test verification of a fuel-powered unmanned aerial vehicle. For the objective conditions of limited flight test airspace and limited flight endurance time of the fuel-powered unmanned aerial vehicle, how to truly and objectively reflect the flight profile of the fuel-powered unmanned aerial vehicle flying the full flight time, ensure the accuracy and availability of the flight test data, and utilize the limited flight test airspace and flight endurance time. Through scientific and reasonable flight test planning, the problem of obtaining accurate maximum flight time data during the flight test of the fuel-powered unmanned aerial vehicle is solved. The present invention provides a method for flight time index flight test verification of a fuel-powered unmanned aerial vehicle, which plans two flight sorties of taking off at the maximum weight and landing at the minimum weight, respectively obtains the average hourly fuel consumption of the two flight sorties, and shortens the flight verification time of the fuel-powered unmanned aerial vehicle. It not only examines the takeoff ability and climbing ability of the fuel-powered unmanned aerial vehicle at the maximum weight, but also verifies the cruising ability of the fuel-powered unmanned aerial vehicle at a large weight and a small weight. Finally, a calculation formula for the maximum flight time is given, and the full flight time fuel quantity is processed in segments to obtain accurate and available maximum flight time data.

[0006] The technical solution of the present invention is as follows: A method for flight time index flight test verification of a fuel-powered unmanned aerial vehicle includes the following parts: Step S1: Establish a mathematical model for flight time calculation; Step S2: Analyze the mathematical model for flight time calculation; Step S3: First flight plan: Take off at maximum weight; Step S4: Second flight plan: Land at minimum weight; Step S5: Obtain the actual flight comprehensive hourly fuel consumption; Step S6: Obtain the maximum flight time of the flight test plan based on weight segmentation; Step S7: Determine whether the range index of the unmanned aerial vehicle is satisfied.

[0007] Further, according to the parameters of the unmanned aerial vehicle, including: Flight time index of the unmanned aerial vehicle Empty operating weight of the unmanned aerial vehicle Maximum fuel capacity of the unmanned aerial vehicle Backup fuel of the unmanned aerial vehicle Flight time of the flight test plan Actual flight time of the first flight Actual flight time of the second flight .

[0008] Further, the said step S1 includes: Establish a mathematical model for flight time calculation. The mathematical model is as follows: ; Wherein: is the endurance time, unit: hour; is the cruise lift, unit: Newton; is the cruise drag, unit: Newton; is the specific fuel consumption per unit of thrust, unit: kg / (Newton×hour); is the acceleration due to gravity, unit: m / s²; is the ratio of the starting weight to the ending weight; is the natural logarithmic function of the ratio of the starting weight to the ending weight.

[0009] Further, the said step S2 includes: According to the empty operating weight of the unmanned aerial vehicle and the maximum fuel capacity , Backup fuel And the endurance index of the UAV, analyze the data model for endurance calculation.

[0010] Furthermore, the endurance index of the UAV The corresponding starting weight Is the empty operating weight Plus the maximum fuel filling amount , The ending weight Is the empty operating weight Plus the backup fuel , That is: ; Wherein: Is the empty operating weight of the UAV, unit: kilogram; Is the maximum fuel filling amount of the UAV, unit: kilogram; Is the backup fuel of the UAV, unit: kilogram; Is the starting weight of the UAV, that is, the weight at the start of flight, unit: kilogram; Is the ending weight of the UAV, that is, the weight at the end of flight: unit: kilogram; Is the endurance index of the UAV, unit: hour; Is the cruise lift, unit: Newton; Is the cruise drag, unit: Newton; Is the fuel consumption per unit of thrust, unit: kilogram / (Newton×hour); Is the acceleration due to gravity, unit: meter / second²; Is the natural logarithmic function of the ratio of the starting weight to the ending weight; Is the endurance per unit weight, unit: hour / kilogram.

[0011] Furthermore, the said step S3 includes: Step S31: Fill up the fuel before the first flight; Step S32: Obtain the endurance data during the actual flight of the first flight ; Step S33: Obtain the landing weight by weighing after the first flight lands , and obtain the remaining fuel ; Step S34: Obtain the actual average fuel consumption per hour for the first flight .

[0012] Furthermore, the step S31 includes: The refueling amount is full fuel , and the takeoff weight in the full fuel state is: ; where: is the takeoff weight of the UAV for the first flight, unit: kilogram; is the empty weight of the UAV in use, unit: kilogram; is the maximum refueling amount of the UAV, unit: kilogram.

[0013] Furthermore, the step S32 includes: From the moment of takeoff and leaving the ground to the moment of landing and touching the ground ending, the actual flight time of the first flight is equal to the moment of landing and touching the ground minus the moment of takeoff and leaving the ground .

[0014] It is required that the actual flight time of the first flight is close to but not greater than the planned flight time of the test flight.

[0015] Furthermore, the actual flight time of the first flight is calculated by the following formula: ; where: is the actual flight time of the first flight, unit: hour; is the moment of landing and touching the ground of the first flight, unit: hour, minute, second; is the moment of takeoff and leaving the ground of the first flight, unit: hour, minute, second.

[0016] Furthermore, the step S33 includes: ; where: is the remaining fuel of the first flight, unit: kilogram; is the landing weight of the first flight, unit: kilogram; It is the empty weight of the drone for use, unit: kilogram.

[0017] Further, the step S34 includes: ; Wherein: Is the average hourly fuel consumption of the first flight, unit: kilogram per hour; Is the take-off weight of the first flight, unit: kilogram; Is the landing weight of the first flight, unit: kilogram; Is the actual flight time of the first flight, unit: hour.

[0018] Further, the step S4 includes: Step S41: Refuel before the second flight; Step S42: Obtain the flight time data during the actual flight of the second flight ; Step S43: Obtain the landing weight by weighing after the second flight , and obtain the remaining fuel ; Step S44: Obtain the average hourly fuel consumption of the second flight .

[0019] Further, the step S41 includes: The principle of the take-off weight Should ensure that the drone lands with a weight close to After the flight duration . According to the mathematical model for calculating the flight time, the take-off weight Is: ; Further, the refueling amount Is: .

[0020] Wherein: Is the empty weight of the drone for use, unit: kilogram; Is the backup fuel of the drone, in accordance with relevant airworthiness or other standard regulations, unit: kilogram; Is the flight time planned for the test flight, unit: hour; Is the flight time per unit weight, unit: hour per kilogram; is the base of the natural logarithm function, approximately equal to 2.71828; is the fuel filling amount for the second flight of the UAV, unit: kilogram; is the takeoff weight for the second flight of the UAV, unit: kilogram;

[0021] Further, the step S42 includes: From the moment of takeoff and leaving the ground starting, to the moment of landing and touching the ground ending, the actual flight time of the second flight is equal to the moment of landing and touching the ground minus the moment of takeoff and leaving the ground .

[0022] It is required that the actual flight time of the second flight is close to but not greater than the planned flight time of the test flight.

[0023] Further, the actual flight time of the second flight is calculated by the following formula: ; where: is the actual flight time of the second flight, unit: hour; is the moment of landing and touching the ground of the second flight, unit: hour:minute:second; is the moment of takeoff and leaving the ground of the second flight, unit: hour:minute:second.

[0024] Further, the step S43 includes: ; where: is the remaining fuel of the second flight, unit: kilogram; is the landing weight of the second flight, unit: kilogram; is the empty weight of the UAV in use, unit: kilogram.

[0025] Further, the step S44 includes: ; where: is the actual average hourly fuel consumption of the second flight, unit: kilogram / hour; is the takeoff weight of the second flight, unit: kilogram; is the touchdown moment of the second flight, unit: hour:minute:second; is the actual flight time of the second flight, unit: hour.

[0026] Furthermore, the step S5 includes: Actual flight comprehensive hourly fuel consumption is equal to the average value of the actual flight average hourly fuel consumption of the first flight and the second flight: ; Wherein: is the actual flight comprehensive hourly fuel consumption, unit: kg / h; is the actual flight average hourly fuel consumption of the first flight, unit: kg / h; is the actual flight average hourly fuel consumption of the second flight, unit: kg / h.

[0027] Furthermore, the step S6 includes: The maximum flight time of the fuel-powered UAV obtained by the flight time index flight test verification method for fuel-powered UAVs : ; Wherein: is the maximum flight time of the fuel-powered UAV, unit: hour; is the maximum fuel filling amount of the UAV, unit: kg; is the remaining fuel of the second flight, unit: kg; is the actual flight comprehensive hourly fuel consumption, unit: kg / h; is the backup fuel of the UAV, in accordance with relevant airworthiness or other standard regulations, unit: kg; is the actual flight average hourly fuel consumption of the second flight, unit: kg / h.

[0028] Furthermore, the step S7 includes: If the maximum flight time of the fuel-powered UAV obtained by the flight time index flight test verification method for fuel-powered UAVs this UAV flight time index, then the UAV flight time index can be achieved; otherwise, the UAV does not meet the flight time index.

[0029] Compared with the existing technology, the beneficial effects of the present invention are: 1. Based on actual flight verification, the present invention takes into account takeoff at maximum weight and landing at minimum weight. While effectively verifying the flight time index, it assesses flight performances such as the takeoff ability at maximum weight and the climbing ability, and also verifies the cruise ability at large weight and small weight. The assessment is more comprehensive and closer to the flight profile of actual flight for the entire flight time.

[0030] 2. The present invention establishes a mathematical model for calculating flight time, clarifies the takeoff fuel quantity, plans the flight test process, which is scientific, reasonable, and complete. It effectively shortens the flight time of actual flight verification and proposes conditions for whether the flight time index of the unmanned aerial vehicle (UAV) is met, with clear conditions and feasible criteria.

[0031] 3. The present invention is applicable to fuel-powered UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments recorded in the embodiments of the present invention, and those of ordinary skill in the art can also obtain other drawings based on these drawings.

[0033] Figure 1 It is a flowchart of the flight test verification method for the flight time index of a fuel-powered UAV. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0034] The present invention will be further described in conjunction with the drawings and embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art shall fall within the scope of protection of the embodiments of the present invention.

[0035] See Figure 1 , a flight test verification method for the flight time index of a fuel-powered UAV, specifically including the following steps: Step S1: Establish a mathematical model for calculating flight time; Step S2: Analyze the mathematical model for calculating flight time; Step S3: Flight test plan for the first sortie: Takeoff at maximum weight; Step S4: Flight test plan for the second sortie: Landing at minimum weight; Step S5: Obtain the actual flight comprehensive fuel consumption per hour; Step S6: Obtain the maximum flight time of the flight test plan method based on weight segmentation; Step S7: Determine whether the UAV range index is met.

[0036] In this embodiment, specifically, according to the UAV parameters, including: UAV flight time index , unit: hour; Empty weight of the unmanned aerial vehicle , unit: kilogram; Maximum fuel capacity of the unmanned aerial vehicle , unit: kilogram; Backup fuel of the unmanned aerial vehicle , unit: kilogram; Flight duration planned for the test flight , unit: hour.

[0037] Actual flight duration of the first flight , unit: hour; Actual flight duration of the second flight , unit: hour.

[0038] In this embodiment, specifically, the step S1 includes: Establish a mathematical model for calculating the flight duration. The mathematical model is as follows: ;

[0039] Where: is the endurance time, unit: hour; is the cruise lift, unit: Newton; is the cruise drag, unit: Newton; is the fuel consumption per unit of thrust, unit: kilogram / (Newton×hour); is the acceleration due to gravity, unit: meter per square second; is the ratio of the starting weight to the ending weight; is the natural logarithm function of the ratio of the starting weight to the ending weight.

[0040] In this embodiment, specifically, the step S2 includes: According to the empty weight of the unmanned aerial vehicle , the maximum fuel filling amount of the unmanned aerial vehicle , the backup fuel of the unmanned aerial vehicle and the flight duration index of the unmanned aerial vehicle, analyze the data model for calculating the flight duration.

[0041] Flight duration index of the unmanned aerial vehicle The corresponding starting weight is the empty weight of the unmanned aerial vehicle plus the maximum fuel capacity , and the ending weight is the empty weight of the unmanned aerial vehicle plus the backup fuel , that is:

[0042] Wherein: is the empty weight of the unmanned aerial vehicle, unit: kilogram; is the maximum fuel filling amount of the unmanned aerial vehicle, unit: kilogram; is the backup fuel of the unmanned aerial vehicle, unit: kilogram; is the starting weight of the unmanned aerial vehicle, that is, the weight at the start of flight, unit: kilogram; is the ending weight of the unmanned aerial vehicle, that is, the weight at the end of flight: unit: kilogram; is the flight time index of the unmanned aerial vehicle, unit: hour; is the cruise lift, unit: Newton; is the cruise drag, unit: Newton; is the fuel consumption per unit thrust, unit: kilogram / (Newton×hour); is the acceleration of gravity, unit: meter per square second; is the natural logarithmic function of the ratio of the starting weight to the ending weight; is the flight time per unit weight, unit: hour / kilogram.

[0043] During the cruise,[[]] and are relatively fixed,[[]] is a constant, thus the value is relatively fixed and is a constant.

[0044] In this embodiment, specifically, the step S3 includes: Step S31: Fill up the fuel before the first flight; Step S32: Obtain the flight time data during the actual first flight ; Step S33: Obtain the landing weight by weighing after the first flight and obtain the remaining fuel ; Step S34: Obtain the average hourly fuel consumption during the actual first flight .

[0045] In this embodiment, specifically, step S31 includes: .

[0046] Wherein: is the take-off weight of the UAV with full fuel, unit: kilogram; is the empty weight of the UAV in use, unit: kilogram; is the maximum fuel filling amount of the UAV, unit: kilogram.

[0047] In this embodiment, specifically, step S32 includes: From the moment when the UAV takes off and leaves the ground to the moment when it lands and touches the ground ends, the actual flight time of the first flight is equal to the moment when it lands and touches the ground minus the moment when it takes off and leaves the ground .

[0048] It should be noted that during the cruise phase, the altitude is selected as the endurance altitude (favorable flight time altitude), and the speed during the cruise phase is selected as the endurance speed (favorable flight time speed).

[0049] It is required that the actual flight time is less than or equal to the flight time planned for the test flight , preferably, it is required that the actual flight time is close to but not greater than the flight time planned for the test flight. For example: take a value between 0.95 and 1 times of the flight time planned for the test flight, that is, it is required that .

[0050] In this embodiment, specifically, the actual flight time of the first flight is calculated by the following formula: Wherein: is the actual flight time of the first flight, unit: hour; is the moment when the first flight lands and touches the ground, unit: hour:minute:second; is the moment when the first flight takes off and leaves the ground, unit: hour:minute:second.

[0051] In this embodiment, specifically, step S33 includes: ; Wherein: is the remaining fuel of the first flight, unit: kilogram; is the landing weight of the first flight, unit: kilogram; is the empty weight of the UAV in use, unit: kilogram.

[0052] In this embodiment, specifically, the step S34 includes: ; wherein: is the average hourly fuel consumption of the first flight, unit: kilogram / hour; is the takeoff weight of the first flight, unit: kilogram; is the landing weight of the first flight, unit: kilogram; is the actual flight time of the first flight, unit: hour.

[0053] In this embodiment, specifically, the step S4 includes: Step S41: Refuel before the second flight; Step S42: Obtain the flight time data during the actual flight of the second flight ; Step S43: Obtain the landing weight by weighing after the second flight , and obtain the remaining fuel ; Step S44: Obtain the average hourly fuel consumption of the second flight .

[0054] In this embodiment, specifically, the step S41 includes: The takeoff weight should ensure that the UAV lands with a weight close to after a flight duration of . According to the mathematical model for calculating flight time, the takeoff weight is: ; Furthermore, the refueling amount is: .

[0055] wherein: is the empty weight of the UAV in use, unit: kilogram; is the backup fuel of the UAV, in accordance with relevant airworthiness or other standards, unit: kilogram; is the flight time planned for the test flight, unit: hour; The flight time per unit weight, unit: hour / kg; The base of the natural logarithm function, approximately equal to 2.71828; The fuel filling amount for the second flight of the UAV, unit: kg; The takeoff weight for the second flight of the UAV, unit: kg;

[0056] In this embodiment, specifically, the step S42 includes: From the moment of taking off and leaving the ground Start, to the moment of landing and touching the ground End, the actual flight time of the second flight Is equal to the moment of landing and touching the ground Subtract the moment of taking off and leaving the ground Moment.

[0057] It should be noted that the altitude in the cruise phase is selected as the endurance altitude (favorable flight time altitude), and the speed in the cruise phase is selected as the endurance speed (favorable flight time speed).

[0058] The required actual flight time Is less than or equal to the flight time planned for the test flight , Preferably, it is required that the actual flight time is close to but not greater than the flight time planned for the test flight. For example: take between 0.95 and 1 times of the flight time planned for the test flight, that is, it is required that .

[0059] In this embodiment, specifically, the actual flight time of the second flight Is calculated by the following formula: ; Where: Is the actual flight time of the second flight, unit: hour; Is the moment of landing and touching the ground of the second flight, unit: hour:minute:second; Is the moment of taking off and leaving the ground of the second flight, unit: hour:minute:second.

[0060] In this embodiment, specifically, the step S43 includes: Where: Is the remaining fuel of the second flight, unit: kg; Is the landing weight of the second flight, unit: kg; It is the empty aircraft weight for the unmanned aircraft.

[0061] In this embodiment, specifically, the step S44 includes: ; Wherein: is the average hourly fuel consumption of the second flight, unit: kg / hour; is the takeoff weight of the second flight, unit: kg; is the landing weight of the second flight, unit: kg; is the actual flight time of the second flight, unit: hour.

[0062] In this embodiment, specifically, the step S5 includes: ;

[0063] Wherein: is the actual flight comprehensive hourly fuel consumption, unit: kg / hour; is the average hourly fuel consumption of the first flight, unit: kg / hour; is the average hourly fuel consumption of the second flight, unit: kg / hour.

[0064] In this embodiment, specifically, the step S6 includes: ; Wherein: is the maximum flight time of the fuel-powered unmanned aircraft, unit: hour; is the maximum fuel filling amount of the unmanned aircraft, unit: kg; is the remaining fuel of the second flight, unit: kg; is the actual flight comprehensive hourly fuel consumption, unit: kg / hour; is the backup fuel of the unmanned aircraft, unit: kg; The average hourly fuel consumption of the second flight, unit: kg / hour.

[0065] It should be noted that the calculation formula for the above maximum flight time has strong generality and is applicable to the remaining fuel of the second flight greater than The same applies to the remaining fuel of the second flight Less than or equal to case.

[0066] In this embodiment, specifically, the step S7 includes: If the maximum flight time of the flight time index test and verification method for fuel-powered UAVs flight time index, then the flight time index of the fuel-powered UAV can be achieved; otherwise, the UAV does not meet the flight time index.

[0067] 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 them. Although the present invention has been described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: it is still possible to modify the specific implementation manners of the present invention or make equivalent replacements, and any modification or equivalent replacement that does not depart from the spirit and scope of the present invention shall be covered by the protection scope of the claims of the present invention.

Claims

1. A flight time index test flight verification method for a fuel-powered UAV, 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 of the first test flight: take-off at maximum weight; Step S4: planning of the second flight test: landing at minimum weight; Step S5: Calculate the actual flight comprehensive hourly fuel consumption; Step S6: Calculate the maximum flight time of the flight test planning method based on weight segmentation; Step S7, determining whether the drone range index is met.

2. The method for verifying the flight time index 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 as follows: ； in: Is the battery life, unit: hours; is the cruise lift, unit: Newton; is the cruise resistance, unit: Newton; The fuel consumption per unit pulling force, unit: kg / (Newton × hour); is the acceleration due to gravity, unit: meter / square second; is the ratio of the starting weight to the ending weight of the drone; It is the natural logarithmic 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 comprises: According to the empty weight of the drone , Maximum refueling capacity , backup fuel And the UAV flight time indicators, analyze the data model of flight time calculation, namely: ； ； ; in: Use the empty weight for the drone in kilograms; The maximum refueling capacity of the drone, in kilograms; Backup fuel for the drone, unit: kilograms; The starting weight of the drone, i.e. the weight at the start of the flight, in kilograms; The ending weight of the drone, i.e. the weight at the end of the flight: unit: kilograms; It is the flight time index of the UAV, unit: hour; is the cruise lift, unit: Newton; is the cruise resistance, unit: Newton; The fuel consumption per unit pulling force, unit: kg / (Newton × hour); is the acceleration due to gravity, unit: meter / square second; is the natural logarithmic function of the ratio of the starting weight to the ending weight; It is the flight time per unit weight, unit: hour / kilogram.

4. The method for verifying the flight time index of 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: Obtaining flight time data for the first actual flight Step S33: After the first flight lands, the landing weight is obtained by weighing , and calculate the remaining fuel ; Step S34: Calculate the average hourly fuel consumption of the first flight .

5. The method for verifying the flight time index of a fuel-powered UAV according to claim 4 is characterized in that: include: The step S31 comprises: Add full oil , take-off weight for: ； in: The take-off weight of the first UAV, in kilograms; Use the empty weight for the drone in kilograms; The maximum refueling capacity of the drone, in kilograms; The step S32 comprises: From take-off time Start to touchdown End, the first flight time Equal to the landing touchdown time Minus takeoff time ; The actual flight time of the first flight 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 flight Calculated by the following formula: ； in: The actual flight time of the first flight, unit: hour; The first landing time, in hours, minutes and seconds; The first take-off time, in hours, minutes and seconds; The step S33 comprises: ； The remaining fuel for the first flight, in kilograms; The first landing weight, unit: kilograms; The empty weight of the drone, in kilograms; The step S34 comprises: ； in: The average hourly fuel consumption of the first flight, unit: kg / hour; The take-off weight of the first sortie, unit: kilogram; The first landing weight, unit: kilograms; It is the actual flight time of the first flight, unit: hour.

6. The method for verifying the flight time index of 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; Step S42: Obtaining flight time data for the second actual flight ; Step S43: After the second flight lands, the landing weight is obtained by weighing , and calculate the remaining fuel ; Step S44: Calculate the actual flight average hourly fuel consumption of the second flight .

7. A method for verifying the flight time index of a fuel-powered UAV according to claim 6, characterized in that: include: The step S41 comprises: Takeoff weight The principle should ensure that the drone has a long flight time. After that, the landing weight is close to ; Based on the mathematical model of flight time calculation, take-off weight for: ； Fuel filling amount for: ； in: Use the empty weight for the drone in kilograms; Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilograms; The flight duration planned for the test flight, in hours; It is the flight time per unit weight, unit: hour / kilogram; is the base of the natural logarithm function, approximately equal to 2.71828; The amount of fuel added for the second flight of the drone, unit: kilograms; The second take-off weight of the UAV, in kilograms; The step S42 comprises: From take-off time Start to touchdown End, the second flight time Equal to the landing touchdown time Minus takeoff time ; 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 flight Calculated by the following formula: ； in: The actual flight time of the second flight, unit: hour; The second landing time, in hours, minutes and seconds; The time when the second flight takes off from the ground, in hours, minutes and seconds; The step S43 comprises: ； in: The remaining fuel for the second flight, in kilograms; The landing weight of the second sortie, unit: kilograms; Use the empty weight for the drone in kilograms; The step S44 comprises: ； in: The average hourly fuel consumption of the second flight, unit: kg / hour; The take-off weight of the second sortie, unit: kilograms; The landing weight of the second sortie, unit: kilograms; It is the actual flight time of the second flight, unit: hour.

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

9. The method for verifying the flight time index of a fuel-powered UAV according to claim 1 is characterized in that: The step S6 comprises: The maximum flight time of a fuel-powered UAV calculated based on the flight time indicator test verification method of a fuel-powered UAV : ； in: The maximum flight time of fuel-powered UAV, unit: hours; The maximum refueling capacity of the drone, in kilograms; The remaining fuel for the second flight, in kilograms; It is the comprehensive hourly fuel consumption of actual flight, unit: kg / hour; Backup fuel for the drone, in accordance with relevant airworthiness or other standards, unit: kilograms; It is the average hourly fuel consumption of the second flight, unit: kg / hour.

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

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