A method for water surface sliding water pumping flight test of amphibious fire-fighting aircraft

Abstract

The present application belongs to the field of aircraft flight test technology in the field of aircraft test and flight test technology, and relates to a kind of amphibious fire-fighting aircraft water surface sliding water pumping flight test method, including water pumping efficiency flight test, water pumping operation flow test, water pumping safety flight test.The technical problem of water surface high-speed sliding water pumping flight test verification of amphibious aircraft is solved, and the best water pumping speed, the best water pumping pitch angle, the best water pumping device lowering timing and water pumping fault handling procedure are obtained by the present application.The water surface sliding water pumping efficiency and safety of amphibious fire-fighting aircraft are effectively improved, and basic support is provided for emergency rescue system construction.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft flight test, and particularly relates to a water surface sliding water scooping flight test method for an amphibious fire-fighting aircraft. BACKGROUND

[0002] During the high-speed water surface sliding water scooping process of the amphibious fire-fighting aircraft, the wave disturbance, dynamic balance of water power lift and resistance need to be overcome, and the air-water dynamic integration layout, structural strength, avionics control and other fields are cooperated, the flight test verification needs to comprehensively consider multiple factors such as aircraft flight performance, water scooping speed, water scooping pitch angle, water scooping device lowering time and the like, which belongs to a typical multiple-input multiple-output research with great uncertainty.

[0003] The current water scooping efficiency and flight test method of the amphibious fire-fighting aircraft have certain reference value, but no standard process and basis are formed.

[0004] At present, how to overcome the multiple-input multiple-output technical difficulties of the fire-fighting aircraft water scooping effect flight test verification needs to be solved, a fire-fighting aircraft water scooping effect flight test method is designed, the best water scooping speed, the best water scooping pitch angle, the best water scooping device lowering time and the water scooping device fault disposal procedure with high credibility and high accuracy are obtained, so as to improve the water scooping efficiency and safety of the fire-fighting aircraft. SUMMARY

[0005] The purpose of the application is to solve the multiple-input multiple-output technical difficulties of the fire-fighting aircraft water scooping effect flight test verification, and propose a water surface sliding water scooping flight test method for an amphibious fire-fighting aircraft.

[0006] The technical scheme of the application is as follows:

[0007] A water surface sliding water scooping flight test method for an amphibious fire-fighting aircraft, comprising the following steps:

[0008] S1: selecting a target water scooping area test field;

[0009] S2: the fire-fighting aircraft adopts a water scooping mode of lowering the water scooping device in water, keeps the water scooping pitch angle unchanged, and adopts an equal step water scooping speed increment to fly over the test field in step S1 several times for water scooping at several speed points;

[0010] S3: measuring the time of each full water scooping in step S2, drawing a water scooping time and water scooping speed curve, and obtaining the best water scooping speed;

[0011] S4: the water scooping aircraft adopts the water scooping mode of putting down the water scooping device in water, maintains the optimal water scooping speed in step S3, and adopts the water scooping pitch angle increment of equidistant step length to perform water scooping several times at several angle points in the test field flight in step S1;

[0012] S5: the time of each water scooping in step S4 is measured, the water scooping time and water scooping pitch angle curve is drawn, and the optimal water scooping pitch angle is obtained;

[0013] S6: the water scooping aircraft maintains the optimal water scooping speed in step S3 and the optimal water scooping pitch angle in step S5, adopts the water scooping device put down angle increment of gradually decreasing to perform water scooping several times at several angle points until the water scooping device is completely put down;

[0014] S7: the in-flight aircraft attitude response data in step S6 is measured, the feasibility of putting down the water scooping device in air is determined, the water scooping time of putting down the water scooping device in air when the water scooping device is completely put down is measured, and the water scooping time when the water scooping device is put down in water is compared to obtain the optimal water scooping device put down timing;

[0015] S8: the water scooping aircraft maintains the optimal water scooping speed in step S3, the optimal water scooping pitch angle in step S5 and the optimal water scooping device put down timing in step S7, respectively realizes the fault state that the water scooping device cannot be retracted and the water scooping device cannot be put down, and performs water scooping several times in the test field flight in step S1.

[0016] S9: the breakaway distance and the in-flight aircraft attitude response data of the aircraft with faults in step S8 are measured, the water scooping device fault handling procedure is determined, and the test is ended.

[0017] Further, in step S1:

[0018] S1.1: the length and width dimensions of the water scooping area are not less than 3000m×200m;

[0019] S1.2: the water depth of the water scooping area is not less than 3m.

[0020] Further, in step S2:

[0021] S2.1: the initial value of the water scooping speed is 110km / h;

[0022] S2.2: the equidistant step length increment of the water scooping speed is +10km / h;

[0023] S2.3: the water scooping speed points are not less than 5.

[0024] Further, in step S3:

[0025] S3.1: the time of putting down the water scooping device in water is not more than 1.5s;

[0026] S3.2: The water pumping time is from the water pumping device being put down in place to the water being pumped up to the brim.

[0027] Further, in step S4:

[0028] S4.1: The initial angle of the water pumping pitch is 3°;

[0029] S4.2: The equal step increment of the water pumping pitch is +1°;

[0030] S4.3: The water pumping test pitch angle is not less than 4.

[0031] Further, in step S5:

[0032] S5.1: The time for the water pumping device to be put down in water is not more than 1.5s;

[0033] S5.2: The water pumping time is from the water pumping device being put down in place to the water being pumped up to the brim.

[0034] Further, in step S6:

[0035] S6.1: Before the water pumping device is put down, it is necessary to ensure that the water inlet pipe is unobstructed;

[0036] S6.2: The initial angle of the water pumping device being put down is 30°;

[0037] S6.3: The step increment of the water pumping device being put down is 30°, 20°, and 10° respectively.

[0038] Further, in step S7:

[0039] S7.1: The water pumping time is from the water pumping device being put down in place to the water being pumped up to the brim.

[0040] S7.2: The flight height when the water pumping device is put down in the air is not less than 100m.

[0041] Further, in step S8:

[0042] S8.1: The water pumping device failure that cannot be retracted includes: the single-sided water pumping device cannot be retracted and the double-sided water pumping device cannot be retracted;

[0043] S8.2: The water pumping device failure that cannot be put down includes: the single-sided water pumping device cannot be put down and the double-sided water pumping device cannot be put down;

[0044] S8.3: When the single-sided water pumping device cannot be put down, the flight mission should include the water pumping task after the failure is found is not completed, the water pumping device is retracted and taken off, and the water pumping device is retracted and taken off after the water is pumped up to the brim;

[0045] S8.4: When the water scooping device cannot be retracted, the flight mission should include taking off with the single-side water scooping device in the un-retracted state after discovering the fault in the full water state, taking off with the double-side water scooping device in the un-retracted state, taking off with the single-side water scooping device in the un-retracted state, and taking off with the double-side water scooping device in the un-retracted state.

[0046] S8.5: The fault interrupting take-off should be performed before the take-off is continued.

[0047] Further, in step S9, the interrupting take-off distance is not greater than the length of the test field.

[0048] The present application is a kind of amphibious fire-fighting aircraft water surface taxiing water scooping flight test method, solves the flight test verification technical problem of fire-fighting aircraft water scooping efficiency and flight safety, the best water scooping speed, the best water scooping pitch angle, the best water scooping device lowering time and water scooping device fault disposal measures obtained by the present application effectively improve the water scooping efficiency and safety of fire-fighting aircraft. DETAILED DESCRIPTION

[0049] The shape, structure, mutual position and connection relationship between parts, the role and working principle of each part, the manufacturing process and the operation and use method of the specific embodiments of the present application as involved will be further described below to help the skilled in the art to have a more complete, accurate and in-depth understanding of the concept and technical solution of the present application:

[0050] The present application provides a kind of amphibious fire-fighting aircraft water surface taxiing water scooping flight test method, for obtaining the best water scooping speed of fire-fighting aircraft, the best water scooping pitch angle, the best water scooping device lowering time and water scooping device fault disposal measures by flight test, which will be further described below in conjunction with embodiments.

[0051] In an embodiment of the present application, for a certain type of amphibious fire-fighting aircraft, a kind of amphibious fire-fighting aircraft water surface taxiing water scooping flight test method proposed by the present application is used to perform flight test verification on the water scooping efficiency and safety of the aircraft, and the steps are as follows:

[0052] S1: Select a water test site, requirements: 1) the length x width of the rectangular target water area is not less than 3000m x 200m; the water depth is not less than 3m.

[0053] S2: The fire-fighting aircraft adopts the water scooping mode of lowering the water scooping device in water, keeps the water scooping pitch angle fixed, and uses equal step water scooping speed increments to fly several times on the test field in step S1 to scoop water at several speed points; requirements: 1) the initial value of water scooping speed is 110km / h; 2) the equal step water scooping speed increment is +10km / h; 3) the water scooping speed points are not less than 5.

[0054] S3: Measure the time of each water filling in step S2, draw the curve of water filling time and water filling speed, and get the best water filling speed; requirements: 1) The time of putting down the water scooping device in water is not more than 1.5s; 2) The water filling time is from the water scooping device being put down to being filled with water.

[0055] S4: The water scooping mode of the water scooping device being put down in water is adopted by the fire-fighting aircraft, the best water filling speed in step S3 is maintained, and the water scooping pitch angle increment of equal step is adopted to fly several times of water scooping in the test field in step S1 at several angle points; requirements: 1) The initial angle of water scooping pitch angle is 3°; 2) The equal step increment of water scooping pitch angle is +1°; 3) The water scooping test pitch angle is not less than 4.

[0056] S5: Measure the time of each water filling in step S4, draw the curve of water filling time and water scooping pitch angle, and get the best water scooping pitch angle; requirements: 1) The time of putting down the water scooping device in water is not more than 1.5s; 2) The water filling time is from the water scooping device being put down to being filled with water.

[0057] S6: The best water filling speed in step S3 and the best water scooping pitch angle in step S5 are maintained by the fire-fighting aircraft, the water scooping device is gradually put down at several angle points by the way of hydraulic system modification, and several times of water scooping are performed until the water scooping device is completely put down; requirements: 1) The water inlet pipe should be ensured to be unobstructed before the water scooping device is put down; 2) The initial angle of the water scooping device being put down is 30°; 3) The step increment of the water scooping device being put down is 30°, 20°, and 10° respectively.

[0058] S7: Measure the attitude response data of the aircraft in the air in step S6, determine the feasibility of the water scooping device being put down in the air, measure the time of the water being filled when the water scooping device is completely put down in the air, compare the water filling time when the water scooping device is put down in water, and get the best time of the water scooping device being put down; requirements: 1) The water filling time is from the water scooping device being put down to being filled with water; 2) The flight height when the water scooping device is put down in the air is not less than 100m.

[0059] S8: the fire-fighting aircraft maintains the optimal water scooping speed in step S3, the optimal water scooping pitch in step S5 and the optimal water scooping device lowering time in step S7, and through hydraulic system modification, respectively realizes the failure states of the water scooping device being unable to be retracted and the water scooping device being unable to be lowered, and performs several water scooping tests in the test field in step S1; requirements: 1) the water scooping device being unable to be retracted includes the single-side water scooping device being unable to be retracted and the double-side water scooping device being unable to be retracted; 2) the water scooping device being unable to be lowered includes the single-side water scooping device being unable to be lowered and the double-side water scooping device being unable to be lowered; 3) when the single-side water scooping device is unable to be lowered, the flight task should include the flight after the water scooping task is not completed after the failure is found, the water scooping device is retracted and the aircraft takes off, and the flight after the water scooping device is retracted and the aircraft takes off after the water is scooped full; 4) when the water scooping device is unable to be retracted, the flight task should include the flight with the single-side water scooping device in the un-retracted state after the failure is found in the full water state, the flight with the double-side water scooping device in the un-retracted state, the interrupted flight with the single-side water scooping device in the un-retracted state and the interrupted flight with the double-side water scooping device in the un-retracted state; 5) the interrupted flight with the failure should be performed before the aircraft continues to take off.

[0060] S9: measures the interrupted take-off distance and the aircraft attitude response data of the aircraft taking off with the failure in step S8, determines the water scooping device failure disposal procedure, and ends the test; requirements: 1) the interrupted take-off distance is not greater than the length of the test field.

[0061] The above merely describes specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A test method for an amphibious firefighting aircraft to glide and scoop water on the water surface, characterized in that, Includes the following steps: S1: Select the target water intake area for the test site; S2: The firefighting aircraft adopts the water-collecting mode of lowering the water-collecting device underwater, keeping the water-collecting pitch angle constant, and at the same time, it uses equal-distance step water-collecting speed increments to fly the test range in step S1 several times at several speed points to collect water. S3: Measure the time it takes to fill the water each time in step S2, plot the water-drawing time versus water-drawing speed curve, and obtain the optimal water-drawing speed; S4: The firefighting aircraft adopts the water-drawing mode of lowering the water-drawing device underwater, maintains the optimal water-drawing speed in step S3, and at the same time uses equal-distance step water-drawing pitch angle increments to fly the test range in step S1 several times at several angle points to draw water. S5: Measure the time it takes to fill the water each time in step S4, plot the water filling time versus water filling pitch angle curve, and obtain the optimal water filling pitch angle; S6: The firefighting aircraft maintains the optimal water-drawing speed in step S3 and the optimal water-drawing pitch angle in step S5, and draws water several times at several angle points by gradually decreasing the water-drawing device lowering angle increment, until the water-drawing device is completely lowered. S7: Measure the aircraft attitude response data in the air in step S6 to determine the feasibility of releasing the water-collecting device in the air. Measure the time it takes for the water-collecting device to be fully submerged when it is released in the air. Compare the water-collecting time when the water-collecting device is released in the water to obtain the optimal timing for releasing the water-collecting device. S8: The firefighting aircraft maintains the optimal water-collecting speed in step S3, the optimal water-collecting pitch angle in step S5, and the optimal timing for lowering the water-collecting device in step S7, respectively achieving the fault states that the water-collecting device cannot be retracted and the water-collecting device cannot be lowered, and performs water-collecting several times during the test flight in step S1. Among them, the inability to retract the water intake device includes: the inability to retract the water intake device on one side and the inability to retract the water intake device on both sides; Faults that prevent the water intake device from being lowered include: a single water intake device cannot be lowered and a double water intake device cannot be lowered. When a single-sided water-collecting device cannot be lowered, the flight mission should include taking off after the water-collecting task is not completed upon discovery of the malfunction and the water-collecting task is retracted, and taking off after the normal side water-collecting device is filled with water and the water-collecting device is retracted. When the water intake device cannot be retracted, the flight mission should include taking off with one side of the water intake device not retracted after the fault is discovered in the full water state, taking off with both sides of the water intake device not retracted, aborting takeoff with one side of the water intake device not retracted, and aborting takeoff with both sides of the water intake device not retracted. Takeoff with a malfunction should be performed before proceeding with takeoff. S9: Measure the takeoff distance and attitude response data of the aircraft that took off with a malfunction after step S8 is interrupted, determine the malfunction handling procedure for the water intake device, and the test ends.

2. The method for testing the water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S1: S1.1: The length and width of the water intake area shall not be less than 3000m × 200m; S1.2: The water depth in the water intake area shall not be less than 3m.

3. The method for testing the water-board gliding and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S2: S2.1: The initial water-drawing speed is 110 km / h; S2.2: The water-drawing speed is increased by an equidistant step size of +10km / h; S2.3: The number of water intake points shall not be less than 5.

4. The method for testing the water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S3: S3.1: The time for lowering the water-drawing device into the water shall not exceed 1.5 seconds; S3.2: The water-drawing time is from when the water-drawing device is lowered into place until it is full of water.

5. The test method for a water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S4: S4.1: The initial angle of the water-drawing pitch is 3°; S4.2: The equidistant step increment of the water-drawing pitch angle is +1°; S4.3: The water-drawing test shall have no less than 4 pitch angles.

6. The method for testing the water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S5: S5.1: The time for lowering the water-drawing device into the water shall not exceed 1.5 seconds; S5.2: The water-drawing time is from when the water-drawing device is lowered into place until it is full of water.

7. The method for testing the water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S6: S6.1: Before lowering the water-drawing device, ensure that the water inlet pipe is unobstructed; S6.2: The initial angle at which the water-drawing device is lowered is 30°; S6.3: The water-drawing device is lowered in increments of 30°, 20°, and 10° respectively.

8. The method for testing the water-board gliding and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S7: S7.1: The water-drawing time is from when the water-drawing device is lowered into place until it is full of water; S7.2: When the water-collecting device is deployed in the air, the flight altitude shall not be less than 100m.

9. The test method for a water-board taxiing and water-lifting flight of an amphibious firefighting aircraft according to claim 1, characterized in that, In step S9, the distance of the interrupted takeoff is no greater than the length of the test range.