Aircraft flight test counterweight control device

Abstract

A counterweight control device for aircraft flight testing enables water to flow regardless of aircraft attitude, offering high computational reliability, convenient operation, and high versatility. It includes a mounting bracket, multiple water tanks, and multiple weighbridges. The water tanks are installed and fixed to the mounting bracket in a predetermined frame arrangement. Each water tank has a sealed cover and can store water. The weighbridges are used to weigh the total weight and center of gravity of the water in the multiple tanks. During normal operation, based on the set target values ​​for the weight and center of gravity of the test aircraft, the target weight of the water in each tank arranged in that frame is calculated. After water is injected, the weighbridges are used to weigh and verify whether the measured values ​​of the total weight and center of gravity of the water in the multiple tanks meet the target values. The weight of the water in the multiple tanks is fine-tuned until the verification is passed. Then, for each tank, the position of the sealed cover within the corresponding tank is adjusted to fix and maintain the state of the water sealed within that tank.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to an automated aircraft flight test counterweight control device. Background Technology

[0002] Currently, civil aircraft are undergoing performance flight tests and subjective evaluation tests.

[0003] To obtain the expected test data, different aircraft weighting schemes must be implemented according to the different test flight missions to meet the test requirements. Aircraft weighting schemes are highly diverse, and current technologies involve manually moving standard weight sandbags, water, counterweight plates, and weights at calibrated distances to change the aircraft's center of gravity. Calculating the aircraft's center of gravity manually for balancing is inefficient, inaccurate, and poses safety hazards.

[0004] For example, Patent Document 1 (CN113581490A) discloses a water counterweight system test platform and test system, which determines the weight of the aircraft by the number of water tanks, then adjusts the support bracket to determine the center of gravity, and calculates the center of gravity and weight by linking the weighing structure at the bottom. By repeatedly adjusting and confirming in this way, the target counterweight of the aircraft is finally obtained.

[0005] For example, Patent Document 2 (CN207759078U) discloses a liquid storage device for aircraft test flights. The liquid storage device is a cylindrical tank, and the support adopts a non-standard saddle support. A set of handrails and flanges are welded on the upper arc surface. Liquid replaces the traditional solid counterweight, which is easier to adjust and monitor.

[0006] For example, Patent Document 3 (CN109305388A) discloses an automatic longitudinal center of gravity adjustment system for aircraft based on water ballast. Eight water tanks are arranged in a rectangular shape and connected by pipes. The center of gravity is adjusted by controlling the valves in the connecting pipes.

[0007] In addition, for example, Patent Document 4 (CN109278988A) discloses an aircraft center of gravity adjustment device, which uses a computer connected to a water pump with a pre-set control algorithm to control and adjust the working state of the water pump and the two-way solenoid valve to adjust the volume of counterweight water in their respective water tanks and adjust the overall center of gravity of the aircraft.

[0008] However, the existing ballast method is difficult to meet the stability requirements of aircraft during high-speed flight and high-G maneuvers. With the large increase in aircraft test missions, frequent changes to the aircraft ballast are required, resulting in a waste of manpower and seriously affecting the test progress and milestones of flight tests.

[0009] For example, in Patent Document 1, the entire configuration process is too mobile, requiring repeated adjustments to the water tank positions to achieve the target weight and center of gravity, resulting in excessive adjustments. In Patent Document 2, the liquid is easily affected by the aircraft's attitude and cannot maintain a single shape, potentially affecting the aircraft's center of gravity during flight. In Patent Document 3, only the center of gravity can be adjusted; furthermore, the limited number of eight water tanks significantly restricts the adjustable space, making it difficult to adjust many center of gravity positions accurately, and manual adjustment is time-consuming. Increasing the number of water tanks further complicates the adjustment process. While Patent Document 4 adds automation, making it easier to configure different centers of gravity, it only allows adjustment of the center of gravity, not the weight itself. It also suffers from limited space for center of gravity adjustment, and the ballast water in the tanks flows due to the aircraft's attitude during flight, potentially restarting the automatic ballast function and affecting the experiment.

[0010] Therefore, how to design a counterweight control device for aircraft flight tests that allows the counterweight liquid (such as water) to flow without being affected by the aircraft's attitude, has high computational reliability, is easy to operate, and has high versatility has become an urgent technical problem to be solved. Summary of the Invention

[0011] This invention is made to solve the above-mentioned technical problems. Its purpose is to provide an aircraft flight test counterweight control device that enables the counterweight liquid (water) to flow without being affected by the aircraft attitude, has high calculation reliability, is easy to operate and has high versatility.

[0012] To achieve the aforementioned objective, this invention provides an aircraft flight test counterweight control device for adjusting and controlling the counterweight state of an aircraft during flight tests under different counterweight conditions. The device comprises: a mounting bracket installed in the passenger cabin of the aircraft for fixing counterweight containers and weighing devices; multiple counterweight containers arranged in a predetermined frame and fixed to the mounting bracket, each container having a sealing cover capable of vertical movement relative to the container, and capable of storing counterweight liquid within the container covered by the sealing cover; and multiple weighing devices for weighing the total weight and center of gravity of the counterweight liquid in the multiple counterweight containers containing the stored counterweight liquid. When the aircraft flight test counterweight control device is operating normally, based on a set flight test... To determine the target values ​​for the weight and center of gravity of the test aircraft required for the test, the target amount of the counterweight liquid in each of the multiple counterweight containers is calculated by importing the frame arrangement of the multiple counterweight containers. After injecting the counterweight liquid, the total weight and total center of gravity of the counterweight liquid in the multiple counterweight containers containing the counterweight liquid are weighed by the weighing device. The measured values ​​of the total weight and total center of gravity of the counterweight liquid in the multiple counterweight containers are verified to meet the target values ​​for the weight and center of gravity of the test aircraft required for the test flight. Before the verification is passed, the weight of the counterweight liquid in the multiple counterweight containers is finely adjusted. After the verification is passed, for each counterweight container, the position of the sealing cover in the corresponding counterweight container is adjusted to fix and maintain the shape of the counterweight liquid sealed in the corresponding counterweight container by the sealing cover.

[0013] Preferably, the mounting bracket has an upper counterweight mounting part and a lower weighing fixing part, the counterweight mounting part and the weighing fixing part are connected by a column, a plurality of counterweight containers are mounted on the upper counterweight mounting part of the mounting bracket through the mounting fixing part thereon, and a plurality of weighing devices are connected to the lower weighing fixing part of the mounting bracket through sensors.

[0014] Furthermore, multiple counterweight containers are installed and fixed on the counterweight mounting portion of the mounting bracket in a matrix arrangement.

[0015] Alternatively, it may have a plurality of sensors respectively disposed on the corners of the counterweight mounting portion on the lower layer of the mounting bracket.

[0016] Preferably, a positioning screw is provided inside the counterweight container, and the positioning screw is fixed to the counterweight container as a whole.

[0017] Based on this, the positioning screw can be designed to pass through the sealing cover and be inserted into the bottom of the counterweight container and remain fixed in place.

[0018] In addition, the positioning nut is located above the sealing cover and is screwed into the positioning screw.

[0019] In addition, a displacement sensor is provided on the upper surface of the sealing cover plate to detect the position of the positioning nut relative to the positioning screw.

[0020] In addition, a liquid level sensor is provided on the lower surface of the sealing cover to detect the water level in the counterweight container.

[0021] In addition, an exhaust hole is provided on the upper surface of the sealing cover to discharge the gas inside the counterweight container, and it can be sealed.

[0022] In addition, a water inlet is provided on the lower side of the counterweight container, and a water outlet is provided on the bottom surface of the counterweight container.

[0023] The core idea of ​​this invention is to calculate the target weight and center of gravity of the test aircraft required for the flight test using a pre-programmed algorithm. The target weight of all the counterweight containers arranged in a matrix is ​​then converted into the liquid level in the counterweight containers. A pump is used to pump the counterweight liquid in the counterweight containers to reach the corresponding liquid level. The total weight and center of gravity of the current counterweight liquid (e.g., water) are verified by a weighing device at the bottom to ensure that they meet the target weight and center of gravity of the test aircraft required for the flight test. After verification, the positioning nut is tightened to fix the counterweight liquid in the counterweight container with a sealing cover, so that the counterweight liquid maintains a certain shape and is not affected by the aircraft's attitude.

[0024] This invention improves upon existing aircraft ballast devices in some aircraft. Compared to the current manual ballast method used in flight testing, which is now automated through algorithm control, the aircraft flight test ballast control device of this invention performs refined ballast by arranging the weights in a defined grid (e.g., matrix arrangement). That is, according to the requirements of the flight test, the ballast space is rationally divided into grids to ensure accurate configuration of all the weights and center of gravity required for the flight test, and the target values ​​are verified by a weighing device.

[0025] Furthermore, the aircraft flight test counterweight control device of the present invention adds a positioning screw and a positioning nut to all counterweight containers. After calculating and determining the liquid level in the counterweight container, the position of the sealing cover plate in the counterweight container is determined by the displacement sensor and the liquid level sensor, and the rotation of the positioning nut is controlled to fix the positioning screw and the positioning nut. This allows the sealing cover plate to press the water in the counterweight container, thereby ensuring that the water in the counterweight container remains in a certain state and does not change during flight.

[0026] Furthermore, the aircraft flight test counterweight control device of the present invention utilizes an automated algorithm.

[0027] Based on the target values ​​of the test aircraft's weight and center of gravity, the weight and center of gravity of each counterweight container are calculated in advance. Unlike traditional devices that can only counterweight the center of gravity, this invention can counterweight both the weight and the center of gravity, achieving the counterweight effect in one step. It can form different aircraft configurations, has a high degree of automation, reduces or even eliminates human error, greatly shortens the counterweighting time, and saves manpower and resources.

[0028] Furthermore, the aircraft flight test counterweight control device of the present invention has a stable structure and a high degree of automation. It is also easy to test, reducing the likelihood of errors. In addition, the device requires no parts replacement during use, minimizing material waste and reducing maintenance material and time costs. Moreover, it simulates the aircraft's motion during flight to a certain extent, thus overcoming the limitations of manual counterweight techniques in existing technologies. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the aircraft flight test counterweight control device of the present invention under normal conditions.

[0030] Figure 2 This is a schematic diagram of the aircraft flight test counterweight control device of the present invention under normal conditions from another perspective.

[0031] Figure 3 This is a schematic diagram of the external structure of the counterweight container of the aircraft flight test counterweight control device of the present invention.

[0032] Figure 4 yes Figure 3 The diagram shows the internal structure of the counterweight container.

[0033] Figure 5 This is a flowchart of the working process (operation steps) of the aircraft flight test counterweight control device of the present invention under normal conditions.

[0034] (Symbol Explanation)

[0035] 100 aircraft test flight test counterweight control device;

[0036] 110 mounting bracket;

[0037] 111 Counterweight Installation Unit;

[0038] 112 Weighing fixing part;

[0039] 113 columns;

[0040] 120 counterweight container;

[0041] 121 Mounting and fixing parts;

[0042] 122 positioning screw;

[0043] 123 Sealing cover plate;

[0044] 124 locating nut;

[0045] 125 displacement sensor;

[0046] 126 liquid level sensor;

[0047] 127 exhaust port;

[0048] 128 water inlet;

[0049] 129 water outlet;

[0050] 130 Weighing device;

[0051] 140 sensors. Detailed Implementation

[0052] See below. Figures 1 to 4 First, the structure of the aircraft flight test counterweight control device 100 of the present invention will be described in detail.

[0053] Figure 1 This is a schematic diagram of the aircraft flight test counterweight control device 100 of the present invention under normal conditions, viewed from one perspective. Figure 2 This is a schematic diagram of the aircraft flight test counterweight control device 100 of the present invention under normal conditions from another perspective.

[0054] like Figure 1 and Figure 2 As shown, the aircraft flight test counterweight control device 100 of the present invention...

[0055] The system is used to adjust and control the weight distribution of an aircraft (hereinafter referred to as "test aircraft") under different weight conditions during flight tests before it is put into formal operation. It includes a mounting bracket 110, multiple weight containers 120 (e.g., multiple water tanks), and multiple weighing devices 130.

[0056] (For example, multiple weighbridges).

[0057] The mounting bracket 110 is installed in the cabin of the test aircraft and is mainly used to fix a counterweight container 120, such as a water tank, and a weighing device 130, such as a weighbridge.

[0058] like Figure 1 and Figure 2 As shown, the mounting bracket 110 can be divided into two layers, for example, an upper counterweight mounting section 111 and a lower weighing fixing section 112. The counterweight mounting section 111 and the weighing fixing section 112 are connected by multiple columns 113, thus forming a columnar shape. Figure 1 and Figure 2 In the example shown, both the counterweight mounting part 111 and the weighing fixing part 112 have quadrilateral cross-sections, but they are not limited to this; their cross-sections can also be any other common shape such as a circle, triangle, or pentagon. Furthermore, considering the compatibility and structural simplicity of the connection between the counterweight mounting part 111 and the weighing fixing part 112, it is preferable that the counterweight mounting part 111 and the weighing fixing part 112 have the same cross-sectional shape, for example... Figure 1 and Figure 2 The cross-sections shown are all quadrilaterals, but the invention is not limited to this; different cross-sections are also possible. For example, the cross-section of the counterweight mounting part 111 is circular, while the cross-section of the weighing fixing part 112 is a quadrilateral such as a square. Furthermore, the cross-sections of the counterweight mounting part 111 and the weighing fixing part 112 can be as follows: Figure 1 and Figure 2 The sizes shown are different, but they can also be the same.

[0059] like Figure 1 and Figure 2 As shown, multiple counterweight containers 120 are mounted on the counterweight mounting portion 111 on the upper layer of the mounting bracket 110 via mounting and fixing portions 121 thereon. As an example, for instance, 24 water tanks (counterweight containers 120) are mounted and fixed on the counterweight mounting portion 111 of the mounting bracket 110 in a matrix arrangement of 3 rows × 8 columns.

[0060] In addition, such as Figure 2As shown more clearly, the weighing device 130 is connected to the weighing fixing part 112 on the lower layer of the mounting bracket 110 via, for example, a sensor 140, for weighing multiple counterweight containers 120 mounted and fixed on the counterweight mounting part 111 on the upper layer of the mounting bracket 110, and thereby calculating the total weight, center of gravity, etc. of the counterweight liquid in the multiple counterweight containers 120. As an example, for example, five weighbridges (the weighing device 130) use five sensors 140 located at the four corners and the center of the quadrilateral-shaped counterweight mounting part 111 on the lower layer of the mounting bracket 110 to weigh 24 water tanks (counterweight containers 120) mounted and fixed on the counterweight mounting part 111 on the upper layer of the mounting bracket 110 in a matrix arrangement, and thereby calculate the total weight, center of gravity, etc. of the 24 water tanks (counterweight containers 120).

[0061] Figure 3 This is a schematic diagram of the external structure of the counterweight container 120 of the aircraft flight test counterweight control device 100 of the present invention. Figure 4 yes Figure 3 A schematic diagram of the internal structure of the counterweight container 120 shown.

[0062] like Figure 3 and Figure 4 As shown, a positioning screw 122 is provided inside the counterweight container 120 (water tank). In addition, a sealing cover plate 123 is provided inside the counterweight container 120 (water tank).

[0063] The positioning screw 122 and the counterweight container 120 are fixed as a whole, for example,

[0064] The positioning screw 122 passes through the sealing cover plate 123 and is inserted into the bottom of the counterweight container 120 (water tank) and is fixed in place. The positioning nut 124 is located above the sealing cover plate 123 and is screwed onto the positioning screw 122. By turning the positioning nut 124, the sealing cover plate 123 can rotate relative to the counterweight container 120 (or the positioning screw 122) and move up and down.

[0065] A displacement sensor 125 is provided on the upper surface of the sealing cover 123 for detecting the position of the positioning nut 124 relative to the counterweight container 120 (or the positioning screw 122). As an example, ... Figure 4 As shown, three displacement sensors 125 are provided on the upper surface of the sealing cover plate 123.

[0066] In addition, a liquid level sensor 126 is provided on the lower surface of the sealing cover 123 for detecting the water level in the counterweight container 120 (water tank). Furthermore, a vent 127 can be provided on the upper surface of the sealing cover 123 to release gas from inside the counterweight container 120 (water tank) when the sealing cover 123 moves up and down relative to the counterweight container 120 (or the positioning screw 122), and to ensure sealing.

[0067] A water inlet 128 is provided on the lower side of the counterweight container 120 (water tank) to allow counterweight liquid (e.g., water) to enter the interior of the counterweight container 120 (water tank) covered by the sealing cover plate 123. Additionally, in the counterweight container 120...

[0068] The bottom surface of the (water tank) is provided with an outlet 129 for allowing the counterweight liquid (e.g., water) inside the counterweight container 120 (water tank) to flow out through the outlet 129.

[0069] Below, refer to Figure 5 The working process of the aircraft flight test counterweight control device 100 under normal conditions of the present invention will be described.

[0070] Figure 5 This is a flowchart of the working process (operation steps) of the aircraft flight test counterweight control device 100 under normal conditions according to the present invention.

[0071] According to the laws of conservation of gravity and conservation of gravitational moment, the following equations (1) and (2) are known.

[0072] Equation (1) is: A1×A2 + B1×B2 + C1×C2 = D1×D2

[0073] Equation (2) is: A1 + B1 + C1 = D1

[0074] in:

[0075] A1 is the empty weight of the machine;

[0076] A2 is the empty aircraft's center of gravity;

[0077] B1 represents the weight of the fuel;

[0078] B2 is the center of gravity of the fuel system;

[0079] C1 is the target weight of the counterweight liquid (e.g., water);

[0080] C2 is the target center of gravity of the counterweight liquid (e.g., water);

[0081] D1 is the set value for the total weight of the test aircraft required for flight testing;

[0082] D2 is the set value of the total center of gravity of the test aircraft required for flight testing.

[0083] Next, the target weight and center of gravity of the counterweight liquid (e.g., water) in all counterweight containers 120 under the specified (e.g., matrix arrangement) frame arrangement are calculated using the above equations (1) and (2), namely equations (3) and (4).

[0084] Equation (3) is: C1 = D1 - A1 - B1

[0085] C2 = (D1×D2 - B1×B2 - A1×A2) / C1 Equation (4)

[0086] When the aircraft flight test counterweight control device 100 is working normally, such as Figure 5 As shown, firstly, the target values ​​of the weight and center of gravity of the test aircraft required for the test flight are set (step S110). Then, by importing the prescribed (e.g., matrix arrangement) frame layout of all the counterweight containers 120 (step S120), the target amount of the weight of the counterweight liquid in each of the multiple counterweight containers 120 arranged in this frame layout is calculated (step S130), and then converted into the target amount of liquid level in each counterweight container 120 and imported into the motor controller (step S140). After receiving the indication of the target amount of liquid level in each counterweight container 120, the motor controller pumps or drains water through the water inlet 128 on the lower side of the counterweight container 120 and the water outlet 129 at the bottom of the counterweight container 120 (step S150). Then, the total weight and center of gravity of the counterweight liquid (e.g., water) in the multiple counterweight containers 120 containing counterweight liquid (e.g., water) are weighed by the weighing device 130 connected to the weighing fixing part 112 on the lower layer of the mounting bracket 110, and the total weight and center of gravity of the counterweight liquid in the multiple counterweight containers 120 are verified (judged) to see if the measured values ​​of the total weight and center of gravity of the counterweight liquid in the multiple counterweight containers 120 meet the target values ​​of the weight and center of gravity of the test aircraft required for the test flight test (step S160).

[0087] Before the verification is passed, i.e., the judgment in step S160 is "no", return to step S130, recalculate (or fine-tune) the target amount of weight of the counterweight liquid in each of the multiple counterweight containers 120, and then perform the same steps S140 and S150 as above until the verification is passed in step S160.

[0088] After verification is passed, i.e., step S160 is judged as "yes", for each counterweight container 120, the positioning nut 124 above the sealing cover 123 is tightened (step S170) until the displacement sensor 125 that detects the position of the positioning nut 124 and the liquid level sensor 126 that detects the liquid level in each counterweight container 120 are consistent, and step S180 is judged as "yes", to ensure that the counterweight liquid sealed in the counterweight container 120 by the sealing cover 123 is completely fixed and maintains a certain shape without change. If they are inconsistent, i.e., step S180 is judged as "no", then return to step S170 and continue tightening the positioning nut 124.

[0089] Finally, fix and seal the positioning screw 122 and the positioning nut 124, and close the vent hole 127 on the sealing cover plate 123 (step S190).

[0090] The following aspects should be noted when using this invention:

[0091] (1) The length and size of the mounting bracket 110, the counterweight container 120 and the weighing device 130 should be designed reasonably and correctly so that the counterweight container 120 can be installed and fixed on the upper counterweight mounting part 111 of the mounting bracket 110 in a specific arrangement (e.g., matrix arrangement), and the weighing device 130 can be installed on the lower weighing fixing part 112 of the mounting bracket 110, so that the weight of each counterweight container 120 can be accurately measured under normal conditions.

[0092] (2) In the counterweight container 120, the design layout of the positioning screw 122, positioning nut 124, vent 127, displacement sensor 125, sealing cover 123, liquid level sensor 126, water inlet 128 and water outlet 129 should be reasonable. They are used to fix and seal the liquid in the counterweight container 120 after the accurate measurement of each counterweight container 120 containing liquid is completed, so as to prevent the counterweight liquid (water) from flowing due to the change of aircraft attitude, which would cause the total weight and center of gravity of the test aircraft required for the test flight to change.

[0093] Furthermore, the aircraft flight test counterweight control device 100 of the present invention has high computational reliability and is easy to operate, reducing a large amount of manual operation. Normal operation can be restored simply by manually resetting the program. In addition, the aircraft flight test counterweight control device 100 of the present invention has high versatility, requires no parts replacement, is easy to maintain, and can be applied to the testing of aircraft counterweight management for various aircraft models.

[0094] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

[0095] For example, in the present invention Figure 1 and Figure 2 The illustration shows 24 water tanks (counterweight containers 120), 5 weighbridges (the weighing device 130) and 3 displacement sensors 125, but the present invention is not limited to the aforementioned number and can be adjusted according to the installation dimensions or other requirements.

[0096] Furthermore, in the present invention Figure 1 and Figure 2 In the illustration, 24 water tanks (counterweight containers 120) are installed and fixed on the counterweight mounting part 111 of the mounting bracket 110 in a matrix arrangement of 3 rows × 8 columns. However, as long as the frame arrangement of the water tanks (counterweight containers 120) is preset and the target amount of counterweight liquid in each counterweight container 120 of the multiple counterweight containers 120 arranged in this frame arrangement can be calculated, the present invention is not limited to the matrix arrangement and can be any arrangement.

Claims

1. An aircraft test flight weight control device (100) for adjusting and controlling the weight state of a test aircraft when the test aircraft is tested in different weight states, characterized in that, The aircraft flight test weight control device (100) comprises: a mounting bracket (110) mounted in the cabin of the flight test aircraft for fixing the weight container (120) and the weighing device (130); a plurality of weight containers (120) arranged and fixed on the mounting bracket (110) at specified frame positions, a sealing cover plate (123) capable of moving up and down relative to the weight container (120) is arranged in the weight container (120), and the weight container (120) is capable of storing weight liquid inside the weight container (120) covered by the sealing cover plate (123); and a plurality of weighing devices (130) for weighing the total weight and total center of gravity of the weight liquid stored in the plurality of weight containers (120), When the aircraft flight test weight control device (100) is working normally, based on the target values of the weight and center of gravity of the flight test aircraft required by the flight test, the target amount of the weight of the weight liquid in each of the plurality of weight containers (120) arranged at the frame positions is calculated by introducing the frame position arrangement of the plurality of weight containers (120), after the weight liquid is injected, the total weight and total center of gravity of the weight liquid stored in the plurality of weight containers (120) are weighed by the weighing device (130), and it is verified whether the measured values of the total weight and total center of gravity of the weight liquid in the plurality of weight containers (120) meet the target values of the weight and center of gravity of the flight test aircraft required by the flight test, before the verification is passed, the weight of the weight liquid in the plurality of weight containers (120) is fine-tuned, and after the verification is passed, for each weight container (120), the position of the sealing cover plate (123) in the corresponding weight container (120) is adjusted to fix and maintain the form of the weight liquid sealed in the corresponding weight container (120) by the sealing cover plate (123).

2. The aircraft flight test weight control device (100) of claim 1, wherein: the mounting bracket (110) has an upper weight mounting portion (111) and a lower weighing fixing portion (112), the weight mounting portion (111) and the weighing fixing portion (112) are connected by a vertical column (113), the plurality of weight containers (120) are mounted on the weight mounting portion (111) of the upper layer of the mounting bracket (110) through the mounting fixing portion (121) thereon, the plurality of weighing devices (130) are connected to the weighing fixing portion (112) of the lower layer of the mounting bracket (110) through the sensor (140).

3. The aircraft flight test weight control device (100) of claim 2, wherein: A plurality of the weight containers (120) are installed and fixed in a matrix arrangement on the weight installation portions (111) of the installation support (110).

4. The aircraft test flight test weight control device (100) according to claim 2, wherein A plurality of the sensors (140) are provided on the corners and the center of the weight installation portions (111) of the lower layer of the installation support (110), respectively.

5. The aircraft test flight test weight control device (100) according to claim 2, wherein A positioning screw (122) is provided in the weight container (120), The positioning screw (122) is fixed as one body with the weight container (120).

6. The aircraft test flight test weight control device (100) according to claim 5, wherein The positioning screw (122) is inserted into the bottom of the weight container (120) through the sealing cover plate (123) and is fixed.

7. The aircraft test flight test weight control device (100) according to claim 5, wherein A positioning nut (124) is provided above the sealing cover plate (123) and is screwed with the positioning screw (122).

8. The aircraft test flight test weight control device (100) according to claim 7, wherein A displacement sensor (125) is provided on the upper surface of the sealing cover plate (123) to detect the position of the positioning nut (124) relative to the positioning screw (122).

9. The aircraft test flight test weight control device (100) according to any one of claims 1 to 8, wherein A liquid level sensor (126) is provided on the lower surface of the sealing cover plate (123) to detect the water level in the weight container (120).

10. The aircraft test flight test weight control device (100) according to any one of claims 1 to 8, wherein An exhaust hole (127) is provided on the upper surface of the sealing cover plate (123) to exhaust the gas inside the weight container (120) and can be closed.

11. The aircraft test flight test weight control device (100) according to any one of claims 1 to 8, wherein A water inlet (128) is provided on the lower side of the weight container (120), A water outlet (129) is provided on the bottom surface of the weight container (120).

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