A center of gravity balancing system.

Abstract

The invention relates to a center-of-gravity balancing system for an auxiliary fuel tank center-of-gravity improvement, developed to balance the center of gravity in an externally used auxiliary fuel tank to ensure safe jettison in aircraft.

Description

1 TARIFF A CENTER OF GRAVITY BALANCING SYSTEM The technical field to which the invention relates: The invention relates to changes in the center of gravity of tanks carrying liquids. a center of gravity balancing system that allows for the balancing of changes 5 It is related to. The invention is an external device, particularly designed to ensure safe separation in aircraft. Developed to balance the center of gravity of auxiliary fuel tanks used as such, It relates to an automatically operating center of gravity balancing system. State of the art: 10 The auxiliary fuel tank on aircraft consists of front, middle, and rear sections. Fuel The aircraft has pumps that transfer fuel between the compartments of its tank. The fuel usage is determined by considering the center of gravity of the aircraft and the auxiliary fuel tank. For a safe jettison situation to be achieved, the geometric center of gravity must be aligned. The storage area must be divided into sections so that it does not extend beyond the center. Appendix 15 fuel tank fuel transfer, safe separation of center of gravity (jettison) To ensure proper placement, it needs to be adjusted so that the position of the object is first at the front and then in the middle. To achieve this, fuel is first drawn from the rear compartment, then from the front compartment, and finally... It is also absorbed from the middle compartment. This situation means that the center of gravity is not affected in any way. This ensures that it does not fall behind the geometric center. 20 The auxiliary fuel tank has a fixed capacity. Due to the decreasing fuel level during use... as the amount of fuel in the tank decreases, it experiences agitation depending on the forces it is subjected to. This occurs in a fuel tank designed to be long and narrow for aerodynamic reasons. Fuel churning along the longitudinal axis (longitudinal axis) on the aircraft Unexpected forces are causing it to act. Emergency and critical 25 During maneuvers, this situation can lead to loss of control of the aircraft or impairment of its control capability. This can lead to limitations. Deviation of the center of gravity from the ideal position. Even during navigation, it at least causes an increase in fuel consumption. 2 In the known state of the art, additional fuel tanks are used for center of gravity balancing systems. Although various suggestions and practices have been developed, these improvements are still insufficient. Some examples of invention applications developed for this purpose are given below. Patent number “JPH0840394” of Japanese origin, which is in the known state of the art, 5 The file has been examined. The invention in question involves rapidly transporting fuel. effectively controls the aircraft's center of gravity and moment of inertia, and the fuel tank. A system that takes emergency action when damaged is described. The fuel described in the invention. transport device, multiple devices communicating with each other through communication holes a fuel tank formed by divided small chambers, with 10 in each small chamber expandable and compressible airbags and the interior of the airbags It includes a pressurization device for pressurizing. As mentioned above More than one of the units has been provided, and the fuel tanks of the units are connected to each other. It is connected. The pipe is partly to supply nitrogen gas through the body of the machine. A section inside the body to supply high-pressure gas from the engine, nitrogen gas 15 and includes a section for relieving high-pressure gas. Gas inlet / outlet. The port has a nitrogen gas inlet valve. A high-pressure gas inlet valve, a nitrogen gas exhaust valve and a high-pressure gas exhaust valve are provided and these The valves are controlled independently by a flight computer on the aircraft. Additional The fuel tank's fuel level is 20 at the interface where the auxiliary fuel tank is connected to the aircraft. Measurement is done with load cells placed on the connection interfaces and measurement sensors, etc. Features are not included. The Chinese patent numbered “CN102367063A” exists in the known state of the art. The file has been examined. The invention in question involves a bellows-type device consisting of a body. The fuel tank's feature is that one end of the body is fixed with an end cap, and the other end of the body is 25... It is equipped with a movable end cap. Fixed end cap vs. movable end cap. a flexible bellows and a movable end, sealed and securely connected between them. The cover is arranged. On the fixed end cap, there is a fuel inlet pipe and a fuel outlet. A pipe and an exhaust vent are arranged. The position of the center of gravity Improvements in areas such as readability and load cell usage are not explained. 30 United States registration number “US5850757A” in the known state of the art. The patent application originating from the state has been examined. The invention that is the subject of the application has a 3 a device mounted inside the vehicle that measures the amount of liquid in the tank It is explained that the device mechanically attaches to the tank to prevent translational movement of the tank. It includes a tank bay that is attached to and surrounds the tank. The tank bay is the base of the tank. It has numerous rotating parts that allow only rotational movement. The parts, 5, each of the numerous fixed parts attached to the vehicle is defined by a hole in it. It rotates around a common axis. In tank assembly, numerous pivot elements On the opposite side, it has an extended end that protrudes outwards from the tank. The device also to provide a signal proportional to the load applied to the load cell by the extended end It also includes a load cell in contact with the extended end. Accordion type. 10 for bellows air bags and the number of fuel pumps in each fuel compartment. No improvements are included. In conclusion, due to the negative aspects described above and the current solutions, the subject matter... Due to its shortcomings, an improvement is needed in the relevant technical field. It has been made. The purpose of the invention: The main purpose of the invention is to create accordion-type bellows valves in tanks carrying liquids (fuel). This involves balancing the center of gravity by inflating the airbags with compressed air. Another aim of the invention is to reduce the weight and capacity of fuel tanks in aircraft. By enabling the reading of the center of gravity position, additional fuel is automatically added. the center of gravity of the tank due to the forces it is subjected to as a result of the aircraft's movement It means preserving it ideally without spoiling. Another purpose of the invention is to improve the current situation thanks to the accordion-type bellows air bag. The goal is to reduce the number of fuel pumps used in each fuel compartment. Another aim of the invention is to restrict the turbulent motion of fuel carried in tanks. 25 thanks to this, separation time in aircraft is shortened and safe separation is achieved. The goal is to increase its reliability. Another purpose of the invention is to enable the air in which an additional fuel tank is fitted under different limit conditions. By actively controlling the center of gravity of the aircraft, the weight of the aircraft can be reduced. The control of the center is carried out. 30 4 Another purpose of the invention is to inflate the accordion-type bellows air bag with air pressure. Thanks to this feature, there is no air gap in the center of the tank, thus keeping the fuel inside the tank. The goal is to eliminate the shaking problem. The structural and characteristic features and all the advantages of the invention are given in the figures below. And thanks to the detailed explanation written by referring to these figures, it becomes clearer. 5 This will be understood as such. Therefore, the evaluation should also include these forms and detailed explanations. This should be done taking that into consideration. Explanation of the figures: FIGURE -1; Side view of the center of gravity balancing system in the liquid tanks subject to the invention. It is a drawing that shows a cross-sectional view. 10 Reference numbers: 1. Center of gravity balancing system 2. Body 3. Liquid tank 4. Air bag 15 5. Interface 6. Load cell 7. Fuel pump Description of the invention: 20 The invention relates to changes in the center of gravity of tanks carrying liquids. It relates to a center of gravity balancing system that compensates for changes. The invention Specifically, externally to ensure safe separation status on aircraft. to automatically balance the center of gravity in the additional fuel tanks used It is an improved center of gravity balancing system (1). 25 Center of gravity balancing system (1) in liquid tanks (3) containing liquid By reading the current weight and the position of the center of gravity of the fuselage (2) accordion-type bellows structure placed inside the liquid tank (3) by placing the air bag (4) and supplying compressed air to the air bags (4) inside Adjustment of liquid and air gaps in the volume and control by pressure sensor 5 This is ensured by the bellows structure of the air bags (4) with air pressure. In cases where the body (2) to which the liquid tank (3) is attached is limited as a result of its movement Active control of the center of gravity of the body (2) is provided. In one application of the invention, an additional component is included on aircraft and used externally. The position of the center of gravity for the liquid tank (3), which is the fuel tank, is read. Aircraft 10 inside the body (2) liquid tank (3) used for transporting fuel The center of gravity of the liquid tank (3) with the air bags (4) placed in the aircraft is not affected in any way. It can remain geometrically centered without creating a problem. In aircraft, the center of gravity can vary beyond the center of gravity distribution determined during manufacturing. It does not change. In different limit situations, this external fuel tank, the liquid tank (3) 15 Active control of the center of gravity of the aircraft to which it is attached, the weight of the aircraft It provides an advantage as it will control the center. The fuel of the liquid tank (3) The amount of liquid is measured by sensors placed on the interface (5) where the liquid tank (3) is connected to the aircraft. It is measured with load cells (6). 20 placed on the connection interface (5) which provides the connection between the liquid tank (3) and the body (2). Load cells (6) with measurement sensors are currently in each fuel compartment The need to use fuel metering sensors is eliminated. The use of accordion-type bellows-structured air bags (4) enables fuel transfer and each The number of fuel pumps (7) used in a fuel section is three in total, liquid tank (3) reduces it to one, with the center being (3). Also, with the air bag (4) 25 the fuel must remain in such a way that there is no air gap in the center of the liquid tank (3) Since this will be ensured, the shaking problem is eliminated. The air bag (4) is controlled by air pressure thanks to its accordion-type bellows structure. By doing this, the agitation motion of the liquid is prevented and the liquid is removed from the tank (3) By shortening the liquid disposal time, the reliability of the liquid disposal process is increased. 30 6 Preventing fuel churning in the aircraft, separation in the aircraft. By shortening the time, it increases the reliability of safe separation. Liquid tank (3) In cases where the body (2) in which it is located is movable, the center of gravity This ensures that it does not change. In this way, the aircraft can perform various maneuvers. The center of gravity is also kept constant for the liquid tank (3), which is the fuel tank. 5 15

Claims

7 REQUESTS 1. Center of gravity balancing in tanks carrying liquids. The system (1) has the feature of having at least one fuselage (2), located inside the fuselage (2), At least one air bag (4) used for liquid transport. one liquid tank (3); accordion-type bellows located inside the liquid tank (3) 5 It has a foldable structure and there will be no air gap in the center of the liquid tank (3). which keeps it in this state and agitates the liquid inside the liquid tank (3) This prevents the bellows structure's volume from changing due to the compressed air pumped into it. change in volume of liquid tank (3) liquid and air space in the internal volume liquid 10 that balances the center of gravity by arranging its parts accordion structure in cases where the hull (2) to which the tank (3) is attached is limited thanks to which at least one of the centers of gravity of the body (2) provides active control. 4 air bags; interface connecting the liquid tank (3) to the body (2) (5); with measuring sensors placed on the interface (5) in each fuel compartment 15 measuring the amount of fuel in the liquid tank (3) through sensors and sensors placed on the interface (5) that provide active center of gravity control at least one load cell (6); located in the centre of the liquid tank (3), fuel by using an accordion-type bellows-structured air bag (4) that facilitates its transfer It includes a fuel pump (7) whose number has been reduced to one. 20 2. The center of gravity balancing system (1) in accordance with claim 1, its feature is; accordion The agitation of the liquid is controlled by air pressure in a bellows-type structure. shorten the time of liquid discharge from the liquid tank (3) by preventing its movement It contains an air bag (4) which increases the reliability of the liquid removal process.

3. The center of gravity balancing system (1) in accordance with claim 1, its feature is; it contains 25 In cases where the body (2) in which it is located is mobile, the center of gravity It contains a liquid tank (3) in which it is kept in balance.

Images