CN117227974B - Cargo aircraft with center of gravity adjusting device and center of gravity adjusting method - Google Patents
Cargo aircraft with center of gravity adjusting device and center of gravity adjusting method Download PDFInfo
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Abstract
The invention discloses a freight aircraft with a gravity center adjusting device and a gravity center adjusting method, and relates to the technical field of gravity center adjustment of freight aircraft. The freight aircraft adopts a mounting type cargo carrying mode, can realize automatic air drop control, is provided with the gravity center adjusting device, the flight control system can realize monitoring calculation of the gravity center of the freight aircraft in a static state or in a flight state, after the air drop, the gravity center of the freight aircraft is recalculated based on the air drop cargo through the flight control system, the displacement required to be adjusted by the residual cargo is calculated, the automatic adjustment of the gravity center of the aircraft is realized through the action of the gravity center adjusting device actuator, the gravity center of the freight aircraft returns to the position when in no-load, and the safety, the flight quality and the performance of the aircraft in the subsequent flight process are ensured.
Description
Technical Field
The invention relates to the technical field of gravity center adjustment of freight aircrafts, in particular to a freight aircrafts with a gravity center adjusting device and a gravity center adjusting method.
Background
The center of gravity of a cargo aircraft is the point of action of its gravity and is closely related to the aerodynamic focus of the aircraft in the cargo aircraft design. Whether it is a static or unstable aircraft, the matching relationship between the center of gravity and the focus directly influences the safety, the flight quality, the performance and economy of the aircraft and the selection of the geometrical parameters of the aircraft.
The invention patent application with the publication number of CN115848672A discloses an open type hollow structure cargo aircraft with the capacity of container air drop, which comprises a cargo hold cabin body, a front fuselage, a tail, a landing gear assembly, a pneumatic structure, a collection loading tool, a power assembly and a control system, wherein the side surface and the bottom of the cargo hold cabin body are of an open type structure, and a group-following hanging point matrix is arranged at the top of the inner wall of the cargo hold cabin body. The cargo hold body of the open type hollow structure adopts a bottomless plate design, so that the hanging and the air drop of materials are facilitated; the top of the cargo hold body adopts a hanging point matrix, and a hanging beam of a hanging hook is additionally arranged as required, so that the cargo hold is widely suitable for carriers with different specifications; the device can be used for carrying common parachute containers and modularized air-drop collection loading tools for direct air-drop, and simultaneously has the capacities of parachute landing materials and rapid air-drop of goods without using parachutes.
The cargo is loaded by adopting the loading mode of the cargo collecting and loading device, and the cargo collecting and loading device and the cargo are thrown by adopting the air-drop mode, and because the relative mass of the loaded cargo is large, when the cargo aircraft drops out a certain hanging type air-drop cargo collecting and loading device, the influence of instantaneous air-drop on the gravity center movement change is large, and if the active gravity center adjustment is not carried out, the safety, the flight quality and the performance of the aircraft are directly influenced.
Therefore, there is a need to design a gravity center adjusting device and a gravity center adjusting method for automatically adjusting the position of the residual load after the load is released, so that the gravity center of the cargo aircraft returns to the initial position.
Disclosure of Invention
In order to solve the technical problem of gravity center adjustment before and after air drop of a cargo aircraft, the invention provides the cargo aircraft with the gravity center adjusting device and a gravity center adjusting method. The following technical scheme is adopted:
the utility model provides a freight aircraft with focus adjusting device, includes fuselage cargo hold structure, power device, load mount device, a plurality of collection loading tool subassembly and flight control system, power device installs in fuselage cargo hold structure's front end or both sides, load mount device includes mount device and focus adjustment control device, mount device includes two bearing linear electric slide rail and a plurality of planer-type mount subassembly, the linear rail of two bearing linear electric slide rail is parallel-mounted respectively in fuselage cargo hold structure's inner wall top surface department, two bearing linear electric slide rail are equipped with a plurality of sliders respectively, a plurality of sliders are along the linear rail removal respectively, the top of a plurality of planer-type mount subassembly is installed on a plurality of sliders respectively, and follow the slider and follow the linear rail removal, a plurality of collection loading tool subassemblies are hung respectively in a plurality of planer-type mount subassembly departments, and follow planer-type mount subassembly and follow the linear rail removal, focus adjustment control device and the executor communication connection of mount device's two bearing linear electric slide rail and a plurality of planer-type mount subassembly, flight control system is connected with power device and load mount device communication respectively.
By adopting the technical scheme, for a single-engine cargo aircraft, the power device is arranged at the front end of the fuselage cargo hold structure, and for a double-engine cargo aircraft, the power device 2 is arranged at two sides of the wing structure of the fuselage cargo hold structure 1;
the load mounting device can provide a plurality of mounting positions, the plurality of mounting positions can move along the sliding blocks of the two bearing linear electric sliding rails, the plurality of load collecting and carrying tool components and cargoes in the load collecting and carrying tool components can be mounted on the plurality of mounting positions, and after the loading of cargoes is completed, the flight control system can adjust the positions of the plurality of load collecting and carrying tool components according to the weight of the loaded cargoes, so that the gravity center returns to the position when the cargoes are unloaded again, and the safety, the flight quality and the performance of the cargo aircraft after taking off are ensured;
when the aircraft arrives at the air drop position, the flight control system can control the action of the gantry type mounting assembly to realize the air drop of the appointed collection carrier assembly, the gravity center of the freight aircraft changes after the air drop, the flight control system calculates the gravity center change quantity according to the current condition of the freight aircraft again, and respectively controls the action of the sliding blocks of the two bearing linear electric sliding rails, and controls the rest of the collection carrier assemblies to respectively move for a certain displacement, so that the gravity center of the freight aircraft returns to the position when no load, and the safety, the flight quality and the performance of the aircraft in the subsequent flight process are ensured.
Optionally, the flight control system calculates the position of the center of gravity of the aircraft according to the data of the power device and the load mounting device, generates an aircraft center of gravity adjustment instruction according to the calculation result, and transmits the aircraft center of gravity adjustment instruction to the center of gravity adjustment control device, and the center of gravity adjustment control device respectively controls the execution actions of the two bearing linear electric sliding rails and the plurality of gantry mounting assembly actuators and realizes the adjustment of the center of gravity of the aircraft through the control of the execution actions.
Through adopting above-mentioned technical scheme, power device and load mounting device's data include the fuel quantity of aircraft, load mounting device's position, data such as weight, can carry out real-time barycenter calculation to calculate the displacement volume of remaining collection loader subassembly after the air drop according to barycenter calculation, thereby generate aircraft barycenter adjustment instruction, barycenter adjustment controlling means controls the execution action of two bearing linear electric sliding rail and a plurality of planer-type mounting subassembly executors respectively, and realizes the adjustment of aircraft barycenter through the control of execution action, thereby realize automatic barycenter adjustment solution.
Optionally, the cargo hold structure further comprises a tail fuselage structure, wherein the tail fuselage structure is arranged at the tail of the fuselage cargo hold structure.
Optionally, a landing gear structure is also included, the landing gear structure being mounted at the bottom of the fuselage cargo hold structure.
Optionally, planer-type mounting subassembly includes slider connecting plate, gantry frame and a plurality of aviation couple, the top surface demountable installation of slider connecting plate is in the slider bottom surface of two bearing linear electric sliding rails, the top surface demountable installation of gantry frame is in the bottom surface of slider connecting plate, and a plurality of aviation couple are installed respectively on gantry frame inner wall top surface for install and load container carrier subassembly.
Through adopting above-mentioned technical scheme, the mount of mount collection dress carrier subassembly mainly is based on aviation couple, still can realize controllable automatic air drop control, and aviation couple adopts ripe aviation bomb weapon stores pylon technique, and piston connection one set utilizes pulse cartridge case as the throwing mechanism of power. The pulse cartridge is positioned in the beam body, after the input instruction is issued, an electric signal can trigger one pulse cartridge in the hanger, and the charge in the cartridge is combusted to generate a large amount of fuel gas, so that the connecting mechanism is driven by extremely high pressure to release the hook. Controllable telescopic limiting mechanisms can be arranged at the side and bottom of the gantry frame, so that the mounting stability of the loader assembly is further ensured.
Optionally, a folding split bottom cabin door is arranged at the bottom of the cargo hold structure of the fuselage and is used for the air-drop loading assembly, and the flight control system controls the folding split bottom cabin door to open and close.
A freight aircraft gravity center adjusting method adopts a freight aircraft with a gravity center adjusting device to carry out air drop control on a loading set carrier assembly, and adjusts the gravity center of the freight aircraft after the air drop, comprising the following steps:
step 1, air drop control, namely numbering a plurality of collection loader components respectively when a freight aircraft loads the i collection loader components, wherein the numbers are 1, 2, … … and i respectively, and the weights are recorded as respectively、/>、……、/>The method comprises the steps that the kth assembly loading device component is required to be subjected to air drop, a flight control system controls a folding type split bottom cabin door to be opened, and controls an aviation hook of a gantry type mounting component corresponding to the kth assembly loading device component to start unhooking, and the kth assembly loading device component falls from the folding type split bottom cabin door;
step 2, calculating the center of gravity, wherein before air drop, the freight aircraft is loaded with i cargoes, and the flight control system calculates the integral center of gravity position of the freight aircraft:
；
where W represents the empty weight of the cargo aircraft,indicating the current fuel weight, ++>Representing the position of the center of gravity of the ith collective loading fixture assembly loaded by the cargo aircraft, when the kth collective loading fixture assembly is dropped from the cargo aircraft, the new center of gravity of the aircraft as a whole:
；
gravity center offset of whole cargo aircraft of flight control system；
The rest of the collection loader components in the cargo cabin need to move, and the displacement of the ith cargo is recorded asThen->And->The relationship is as follows:
。
by adopting the technical scheme, a space rectangular coordinate system is adopted when the center of gravity of the freight aircraft is calculated. The X axis is generally parallel to the horizontal line of the fuselage structure, the forward direction of the X axis is from the nose to the tail, the y axis is perpendicular to the plane of symmetry of the airplane, the forward direction of the X axis is from the plane of symmetry of the airplane to the right wing, the Z axis is in the plane of symmetry of the airplane, the Z axis is perpendicular to the X axis, and the forward direction of the Z axis is from bottom to top. The origin of coordinates can be taken in the plane of symmetry of the aircraft, can be arranged at a certain distance in front of the aircraft nose or the aircraft nose, or can be arranged at a station with a frame marked obviously on the aircraft body, when the cargo is not loaded in the cargo compartment, the weight and the gravity center position of the cargo aircraft can be regarded as being related to the fuel quantity only, when the cargo is loaded, the gravity center change of the cargo aircraft is mainly based on the position and the weight of the loaded cargo, and the current fuel quantity weight, the position and the weight of the empty cargo are considered in the calculation of the gravity center change of the cargo aircraft after the air drop in the flight process.
Optionally, the method further comprises a step 3, wherein the flight control system generates an aircraft gravity center adjustment instruction according to the calculated result of the displacement of the ith cargo and transmits the aircraft gravity center adjustment instruction to the gravity center adjustment control device, and the gravity center adjustment control device respectively controls the execution actions of the two bearing linear electric sliding rails and realizes the adjustment of the aircraft gravity center through the control of the execution actions.
Alternatively, the flight control system controls displacement of the ith set of loader assemblies when the kth set of loader assemblies are thrown awayAnd restoring the center of gravity of the cargo aircraft to the initial position.
Optionally, the flight control system reads the current fuel amount in real time, and calculates the current fuel weight according to the current fuel amount.
In summary, the present invention includes at least one of the following beneficial technical effects:
the invention provides a freight aircraft with a gravity center adjusting device and a gravity center adjusting method, wherein the freight aircraft adopts a loading type cargo carrying mode, and can realize automatic air drop control, a gravity center adjusting device is arranged, a flight control system can realize monitoring calculation of the gravity center of the freight aircraft in a static state or a flight state, after the air drop, the gravity center of the freight aircraft is recalculated based on the air drop cargo through the flight control system, the displacement amount required to be adjusted by the residual cargo is calculated, and the automatic adjustment of the gravity center of the aircraft is realized through the action of an actuator of the gravity center adjusting device, so that the gravity center of the freight aircraft returns to the position when in no-load, and the safety, the flight quality and the performance of the aircraft in the subsequent flight process are ensured.
Drawings
FIG. 1 is a schematic view of the internal structure of a cargo aircraft with a center of gravity adjustment device according to the present invention;
FIG. 2 is a schematic view of the structure of a folding side-by-side bottom door of a cargo aircraft with a center of gravity adjustment device according to the present invention;
FIG. 3 is a schematic illustration of a cargo aircraft collection carrier assembly and mounting device having a center of gravity adjustment device in accordance with the present invention;
FIG. 4 is a schematic illustration of the electrical device connection principle of a cargo aircraft with a center of gravity adjustment device according to the present invention;
fig. 5 is a schematic diagram of a barycentric coordinate system of a cargo aircraft barycentric adjustment method of the present invention.
Reference numerals illustrate: 1. a fuselage cargo hold structure; 11. folding split bottom cabin door; 2. a power device; 311. a bearing linear electric sliding rail; 312. a gantry type mounting assembly; 3121. a slide block connecting plate; 3122. a gantry frame; 3123. aviation hook; 313. a slide block; 32. a center of gravity adjustment control device; 4. a cluster loader assembly; 5. a flight control system; 6. a tail fuselage structure; 7. landing gear structure.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The embodiment of the invention discloses a freight aircraft with a gravity center adjusting device and a gravity center adjusting method.
Referring to fig. 1-5, embodiment 1, a cargo aircraft with a gravity center adjusting device, which comprises a cargo hold structure 1, a power device 2, a load mounting device, a plurality of loading assembly 4 and a flight control system 5, wherein the power device 2 is installed at the front end or both sides of the cargo hold structure 1, the load mounting device comprises a mounting device and a gravity center adjusting control device 32, the mounting device comprises two load bearing linear electric sliding rails 311 and a plurality of gantry mounting assemblies 312, the linear rails of the two load bearing linear electric sliding rails 311 are respectively installed at the top surface of the inner wall of the cargo hold structure 1 in parallel, the two load bearing linear electric sliding rails 311 are respectively provided with a plurality of sliding blocks 313, the plurality of sliding blocks 313 respectively move along the linear rails, the tops of the plurality of gantry mounting assemblies 312 are respectively installed on the plurality of sliding blocks 313 and move along the linear rails along the sliding blocks, the plurality of loading assembly 4 are respectively installed at the plurality of gantry mounting assemblies 312 and move along the linear rails along the gantry mounting assemblies 312, the gravity center adjusting control device 32 is respectively connected with the two linear electric sliding rails 311 of the mounting device and the gantry type electric sliding rails and the flight control system 2 of the loading assembly.
For a single-engine cargo aircraft, the power device 2 is arranged at the front end of the fuselage cargo hold structure 1, and for a double-engine cargo aircraft, the power device 2 is arranged at two sides of the wing structure of the fuselage cargo hold structure 1; providing power for the cargo aircraft;
the load mounting device can provide a plurality of mounting positions, the plurality of mounting positions can move along the sliding blocks 313 of the two bearing linear electric sliding rails 311, the plurality of load collecting and carrying tool assemblies 4 and cargoes therein can be mounted on the plurality of mounting positions, after the loading of cargoes is completed, the flight control system 5 can adjust the positions of the plurality of load collecting and carrying tool assemblies 4 according to the weight of the loaded cargoes, the gravity center adjusting control device 32 is mainly realized on the basis of a control chip, the control chip can realize automatic control of a plurality of actuators, so that the gravity center returns to the position when in no-load, and the safety, the flight quality and the performance of a cargo aircraft after taking off are ensured;
when the air drop position is reached, the flight control system 5 can control the action of the gantry type mounting assembly 312 to realize the air drop of the designated collection carrier assembly 4, the gravity center of the freight aircraft changes after the air drop, the flight control system 5 calculates the gravity center change amount again according to the current situation of the freight aircraft, and respectively controls the actions of the sliding blocks 313 of the two bearing linear electric sliding rails 311, and controls the rest of the container carrier assemblies 4 to respectively move for a certain displacement, so that the gravity center of the freight aircraft returns to the position when no load, and the safety, the flight quality and the performance of the aircraft in the subsequent flight process are ensured.
The flight control system 5 calculates the position of the center of gravity of the aircraft according to the data of the power device 2 and the load mounting device, generates an aircraft center of gravity adjustment command according to the calculation result, and transmits the aircraft center of gravity adjustment command to the center of gravity adjustment control device 32, wherein the center of gravity adjustment control device 32 respectively controls the execution actions of the two bearing linear electric sliding rails 311 and the actuators of the plurality of gantry mounting assemblies 312, and realizes the adjustment of the center of gravity of the aircraft through the control of the execution actions.
The data of the power device 2 and the load mounting device comprise data such as fuel quantity of the aircraft, position and weight of the load mounting device, and the like, real-time gravity center calculation can be performed, and the displacement of the remaining set of the loader assembly 4 after the air drop is calculated according to the gravity center calculation, so that an aircraft gravity center adjustment command is generated, the gravity center adjustment control device 32 respectively controls the execution actions of the two bearing linear electric sliding rails 311 and the plurality of gantry type mounting assembly 312 executors, and the adjustment of the aircraft gravity center is realized through the control of the execution actions, so that an automatic gravity center adjustment solution scheme is realized.
Embodiment 2 further comprises a tail fuselage structure 6, the tail fuselage structure 6 being mounted aft of the fuselage cargo hold structure 1.
Embodiment 3 further comprises a landing gear structure 7, the landing gear structure 7 being mounted at the bottom of the fuselage cargo hold structure 1.
In embodiment 4, the gantry mounting assembly 312 includes a sliding block connecting plate 3121, a gantry frame 3122 and a plurality of aviation hooks 3123, wherein the top surface of the sliding block connecting plate 3121 is detachably mounted on the bottom surface of the sliding block 313 of the two bearing linear electric sliding rails 311, the top surface of the gantry frame 3122 is detachably mounted on the bottom surface of the sliding block connecting plate 3121, and the plurality of aviation hooks 3123 are respectively mounted on the top surface of the inner wall of the gantry frame 3122 for mounting the container carrier assembly 4.
The mounting of the mounting set loader assembly 4 is mainly based on the aviation hook 3123, and can also realize controllable automatic air drop control, the aviation hook 3123 adopts the mature aviation bomb weapon hanging frame technology, and a set of throwing mechanism using a pulse cartridge as power is connected with a piston. The pulse cartridge is positioned in the beam body, after the input instruction is issued, an electric signal can trigger one pulse cartridge in the hanger, and the charge in the cartridge is combusted to generate a large amount of fuel gas, so that the connecting mechanism is driven by extremely high pressure to release the hook. Controllable telescopic limit mechanisms can be arranged at the side and bottom of the gantry frame 3122, so that the mounting stability of the loader assembly 4 is further ensured.
In embodiment 5, the bottom of the cargo hold structure 1 is provided with a folding split bottom hatch 11 for air-drop loading the carrier assembly 4, and the flight control system 5 controls the folding split bottom hatch 11 to open and close.
Embodiment 6, a method for adjusting the center of gravity of a cargo aircraft, which uses a cargo aircraft with a center of gravity adjusting device to control an airdrop of a cargo set carrier assembly, and adjusts the center of gravity of the cargo aircraft after the airdrop, includes the following steps:
step 1, performing air drop control, namely numbering a plurality of collection loader assemblies 4 when a freight aircraft loads the i collection loader assemblies 4, wherein the numbers are 1, 2, … … and i, and the weights are respectively recorded as、/>、……、/>The kth set of loading tool assemblies 4 is required to be subjected to air drop, the flight control system 5 controls the folding type split bottom cabin door 11 to be opened, and controls the aviation hook 3123 of the gantry type mounting assembly 312 corresponding to the kth set of loading tool assemblies 4 to start unhooking, and the kth set of loading tool assemblies 4 to start unhookingThe collection carrier assembly 4 falls from the folding split bottom bay door 11;
step 2, calculating the center of gravity, wherein before air drop, the freight aircraft is loaded with i goods, and the flight control system 5 calculates the integral center of gravity position of the freight aircraft:
；
where W represents the empty weight of the cargo aircraft,indicating the current fuel weight, ++>Representing the position of the center of gravity of the ith collection of loader assemblies 4 loaded by the cargo aircraft, when the kth collection of loader assemblies 4 is dropped from the cargo aircraft, the new center of gravity of the aircraft as a whole:
；
flight control system 5 center of gravity offset of the cargo aircraft as a whole；
The rest of the pallet assembly 4 in the cargo hold needs to be moved to record the displacement of the ith cargo asThen->And->The relationship is as follows:
。
referring to fig. 3, a space rectangular coordinate system is used in calculating the center of gravity of a cargo aircraft. The X axis is generally parallel to the horizontal line of the fuselage structure, the forward direction of the X axis is from the nose to the tail, the y axis is perpendicular to the plane of symmetry of the airplane, the forward direction of the X axis is from the plane of symmetry of the airplane to the right wing, the Z axis is in the plane of symmetry of the airplane, the Z axis is perpendicular to the X axis, and the forward direction of the Z axis is from bottom to top. The origin of coordinates can be taken in the plane of symmetry of the aircraft, can be arranged at a certain distance in front of the aircraft nose or the aircraft nose, or can be arranged at a station with a frame marked obviously on the aircraft body, when the cargo is not loaded in the cargo compartment, the weight and the gravity center position of the cargo aircraft can be regarded as being related to the fuel quantity only, when the cargo is loaded, the gravity center change of the cargo aircraft is mainly based on the position and the weight of the loaded cargo, and the current fuel quantity weight, the position and the weight of the empty cargo are considered in the calculation of the gravity center change of the cargo aircraft after the air drop in the flight process.
Embodiment 7 further includes step 3, where the flight control system 5 generates an aircraft center of gravity adjustment command according to the calculation result of the displacement amount of the ith cargo, and transmits the aircraft center of gravity adjustment command to the center of gravity adjustment control device 32, where the center of gravity adjustment control device 32 controls the execution actions of the two bearing linear electric sliding rails 311, respectively, and realizes the adjustment of the aircraft center of gravity through the control of the execution actions.
When the kth set carrier assembly 4 is thrown away, the flight control system 5 controls the displacement of the kth set carrier assembly 4And restoring the center of gravity of the cargo aircraft to the initial position.
The flight control system 5 reads the current fuel amount in real time and calculates the current fuel weight according to the current fuel amount.
Example 8, a modular airdrop cargo plane of a certain type is taken as a specific example. Empty load of cargo aircraftFuel weight->The three pallet assemblies 4 comprise a cargo weight of +.>，/>，/>The method comprises the steps of carrying out a first treatment on the surface of the Three set carrier assemblies 4 are +.>，，/>And three cargo loads fill the cargo holds when full, see fig. 4;
the positions of the gravity centers of the cargoes in initial full loading are respectively，/>，/>The method comprises the steps of carrying out a first treatment on the surface of the The total central position after full load is +.>Then, the following 5 conditions are provided for the gravity center adjustment after the air drop:
air drop when three cargoes are mountedGoods are selected;
center of gravity shift positionThe following relationship is obtained:and then the geometric conditions are satisfied:，/>，/>the coordinate position of the adjusted goods can be obtained through calculation of the flight control system
Air drop when three cargoes are mountedGoods are selected;
center of gravity shift positionThe following relationship is obtained:and then the geometric conditions are satisfied:the coordinate position of the adjusted goods can be obtained through calculation of the flight control system;
air drop when three cargoes are mountedGoods are selected;
center of gravity shift positionThe following relationship is obtained:and then the geometric conditions are satisfied:the coordinate position of the adjusted goods can be obtained through calculation of the flight control system;
when three cargoes are mounted, two cargoes in the air drop are carried out;
because only one cargo remains, the remaining cargo is only required to be transferred to the center of gravity which is the same as that of the aircraft;
one of the two goods is air-dropped when the other two goods are left;
in this case, as the derivation after the end of the first case, only one cargo is left on the aircraft, and therefore, only the remaining cargo gravity center position is required to be moved to the aircraft gravity center position.
And then, using a certain model of airplane as data inspection, using the nose as a geometric coordinate origin, and assuming that the length of the airplane body of the model of airplane is 12m, the length of a cargo hold is 9m, and the left boundary is positioned at the right side of the nose and 1m and is full of oil, the weight of the oil is 2000 kg, and the effective load is 1600 kg. The three modularized weights respectively weigh 400 kg, 600 kg and 600 kg, have the same length of 3 m, and are sequentially loaded in the cargo hold, wherein the centers of gravity of the three modularized weights are positioned at the geometric centers of the three modularized weights; the centre of gravity of the full-oil aircraft is located at a distance of 4m from the nose.
Then it can be calculated according to the formulaWhen the first goods are dropped out by air +.>，Substituting case 1: />It can be derived that: />The third cargo may be left without moving while the second cargo is left 1.318m if the geometric conditions are met.
The above embodiments are not intended to limit the scope of the present invention, and therefore: all equivalent changes in structure, shape and principle of the invention should be covered in the scope of protection of the invention.
Claims (4)
1. A method for adjusting the center of gravity of a cargo aircraft is characterized by comprising the following steps of: the method for controlling the air drop of the cargo set carrier assembly by adopting the cargo aircraft with the gravity center adjusting device and adjusting the gravity center of the cargo aircraft after the air drop comprises the following steps:
step 1, performing air drop control, namely numbering a plurality of collection loader assemblies (4) respectively when the freight aircraft loads the i collection loader assemblies (4), wherein the numbers are respectively 1, 2, … … and i, and the weights are respectively recorded as、/>、……、/>The method comprises the steps that the kth collection loader assembly (4) is required to be subjected to air drop, a flight control system (5) controls a folding split bottom cabin door (11) to be opened, and controls an aviation hook (3123) of a gantry type mounting assembly (312) corresponding to the kth collection loader assembly (4) to start unhooking, and the kth collection loader assembly (4) falls from the folding split bottom cabin door (11);
step 2, calculating the center of gravity, wherein before air drop, the freight aircraft is loaded with i goods, and a flight control system (5) calculates the integral center of gravity position of the freight aircraft:
；
where W represents the empty weight of the cargo aircraft,indicating the current fuel weight, ++>Representing the position of the center of gravity of the ith collection of loader assemblies (4) loaded by the cargo aircraft, when the kth collection of loader assemblies (4) are dropped from the cargo aircraft, the new center of gravity of the aircraft as a whole:
；
gravity center offset of whole cargo aircraft of flight control system (5)；
The rest of the collection loader assembly (4) in the cargo compartment needs to move to record the displacement of the ith cargo asThen->And (3) withThe relationship is as follows:
；
the cargo aircraft with the gravity center adjusting device comprises a cargo hold structure (1) of the aircraft body, a power device (2), a load mounting device, a plurality of collection loader components (4) and a flight control system (5), wherein the power device (2) is arranged at the front end or two sides of the cargo hold structure (1) of the aircraft body, the load mounting device comprises a mounting device and a gravity center adjusting control device (32), the mounting device comprises two load-bearing linear electric sliding rails (311) and a plurality of gantry mounting components (312), linear rails of the two load-bearing linear electric sliding rails (311) are respectively arranged at the top surface of the inner wall of the cargo hold structure (1) in parallel, the two load-bearing linear electric sliding rails (311) are respectively provided with a plurality of sliding blocks (313), the sliding blocks (313) respectively move along the linear rails, the tops of the gantry mounting components (312) are respectively arranged on the sliding blocks (313) and move along the linear rails, the plurality of collection loader components (4) are respectively mounted at the gantry mounting components (312) and are respectively connected with the two gantry mounting components (312) along the linear rails, and the two load-bearing linear adjusting devices (312) are respectively communicated with the flight control system (2);
the flight control system (5) calculates the gravity center position of the airplane according to the data of the power device (2) and the load mounting device, generates an airplane gravity center adjusting instruction according to the calculation result and transmits the instruction to the gravity center adjusting device (32), and the gravity center adjusting device (32) respectively controls the execution actions of the two bearing linear electric sliding rails (311) and the actuators of the plurality of gantry mounting assemblies (312) and realizes the adjustment of the center of gravity of the airplane through the control of the execution actions;
the cargo hold structure also comprises a tail body structure (6), wherein the tail body structure (6) is arranged at the tail part of the cargo hold structure (1);
-a landing gear structure (7), said landing gear structure (7) being mounted at the bottom of the fuselage cargo hold structure (1);
the gantry type mounting assembly (312) comprises a sliding block connecting plate (3121), a gantry frame (3122) and a plurality of aviation hooks (3123), wherein the top surface of the sliding block connecting plate (3121) is detachably arranged on the bottom surfaces of sliding blocks (313) of two bearing linear electric sliding rails (311), the top surface of the gantry frame (3122) is detachably arranged on the bottom surface of the sliding block connecting plate (3121), and the aviation hooks (3123) are respectively arranged on the top surfaces of the inner walls of the gantry frame (3122) and are used for mounting a collection loader assembly (4);
the bottom of the fuselage cargo hold structure (1) is provided with a folding split bottom cabin door (11) for the air-drop loading assembly (4), and the flight control system (5) controls the folding split bottom cabin door (11) to open and close.
2. The method for adjusting the center of gravity of a cargo aircraft according to claim 1, wherein: and 3, generating an airplane gravity center adjusting instruction according to the calculated result of the displacement of the ith cargo by the flight control system (5), transmitting the airplane gravity center adjusting instruction to the gravity center adjusting device (32), respectively controlling the execution actions of the two bearing linear electric sliding rails (311) by the gravity center adjusting device (32), and realizing the adjustment of the airplane gravity center through the control of the execution actions.
3. A method of adjusting the center of gravity of a cargo aircraft according to claim 2, wherein: when the kth part collection loader assembly (4) is thrown down, the flight control system (5) controls the displacement of the ith part collection loader assembly (4)And restoring the center of gravity of the cargo aircraft to the initial position.
4. The method for adjusting the center of gravity of a cargo aircraft according to claim 1, wherein: the flight control system (5) reads the current fuel quantity in real time and calculates the current fuel weight according to the current fuel quantity.
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