Computer-implemented method for preventing infeasible loading states in aircraft
By using computer simulation to randomly select empty loads and generate load distribution, the problem of lateral moment imbalance caused by improper loads in aircraft is solved, ensuring the feasibility and safety of the loading process.
Patent Information
- Application Number
- CN202510943961.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2024-07-22
- Filing Date
- 2025-07-09
- Publication Date
- 2026-01-23
AI Technical Summary
Existing technologies cannot effectively prevent lateral moment imbalance caused by improper load distribution in the aircraft cargo hold, especially when the empty load is unknown, and cannot ensure the feasibility of the loading process.
By simulating multiple load distributions using computer simulations, randomly selecting empty rows and generating random load distributions, calculating lateral moments, and determining whether the loading state is feasible, loading is prevented under infeasible conditions.
It effectively prevents aircraft from being in an infeasible loading state due to load imbalance, ensures flight safety, and reduces loading risks caused by unknown empty loads.
Smart Images
Figure CN121389401A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present invention relates to a computer-implemented method for preventing infeasible loading states in an aircraft before the aircraft is loaded. Given a layout of a load space and a set of load units, the method estimates the loading state and prevents an infeasible loading once the aircraft is loaded. BACKGROUND
[0002] One of the most serious flight safety issues in an aircraft is the lack of balance due to improper distribution of loads in the cargo compartment of the aircraft.
[0003] The loads on an aircraft are placed in pre-established spaces so that the loads can be distributed as evenly as possible. However, each load has a different value according to its weight and its distance from the center axis of the aircraft (an axis parallel to the roll axis) defines a lateral moment equal to the value of the weight multiplied by the distance to the axis. In an ideal situation, the lateral moment of one load must be canceled by the lateral moment of another load.
[0004] The cargo compartment of an aircraft is usually distributed in rows. In each row there are multiple cargo spaces and all the cargo spaces can be divided into two groups, the spaces on one side of the symmetry axis or center axis and the spaces on the other side. Depending on the way the orientation is chosen, for example according to the plan view, one side will be on the right and the other side will be on the left.
[0005] In some cases, a portion of these rows has spaces that are disabled corresponding to half a row. This creates a problem because each of the load units generates a lateral moment that is not canceled when the available spaces on the other side of the same row are loaded. The row in this case will be called empty row.
[0006] The empty row can be at least partially canceled by another empty row on the opposite side with empty spaces. However, it is especially worth noting the cases where there is no such cancellation.
[0007] One might think that knowing the layout of the aircraft, the empty rows and their positioning, and the loads to be installed in the cargo compartment, it is possible to pre-assign the positioning of each cargo unit so as to minimize the lateral moment of the entire load. However, this is not possible because it is not known in advance which rows are empty and what weight each individual load has.
[0008] At most, it is usually estimated which loads are heavy and which loads are not heavy at the time of loading, and then the person responsible for assigning the loads can take advantage of this arrangement when carrying the loads on either side of the center axis.
[0009] However, no control is established to prevent the start of the loading process of the aircraft, since without this information, it establishes the conditions of feasibility or infeasibility of the load. The total load lateral moment is considered to produce a feasible load when it does not exceed the maximum value of the lateral moment determined for each aircraft. The present invention overcomes this problem by performing a plurality of load simulations and, according to the results of the simulations, stabilizing the feasible or infeasible state, preventing the loading process when the state is infeasible. SUMMARY
[0010] The present invention is a computer-implemented method for preventing infeasible loading states in an aircraft.
[0011] The method provides information which is subsequently processed to check whether the aircraft can be loaded according to the state. That is, if the state is "feasible", the aircraft is loaded, but if the state is "infeasible", the aircraft is not loaded. The state "feasible" or "infeasible" can be represented by a binary variable or by a more complex structure with additional information, such as the estimated load balance.
[0012] The loads to be loaded in the aircraft comprise a plurality of load units.
[0013] The method according to the first aspect of the invention comprises the following steps:
[0014] in any order:
[0015] a) receiving data of the layout of the load space of the aircraft, the layout comprising:
[0016] a set of N rows, each row comprising a set of M positions, the M positions having a subset of left positions and a subset of right positions;
[0017] for each position, the distance of the position to the axis of symmetry, the distance being used to measure the lateral moment of the load, the axis of symmetry being parallel to the roll axis of the aircraft;
[0018] b) receiving a maximum load imbalance lateral moment value;
[0019] c) receiving a probability function or probability distribution of the weights of the load units;
[0020] d) pre-determining a maximum number of empty rows R to be checked, an empty row being a row in which one side, either the right or the left, is locked so that the positions of the selected row cannot be loaded, while the opposite side is not locked to allow being loaded;
[0021] The layout of the load space of the aircraft identifies the positions where the load units can be positioned. The load space is distributed in rows, each row having one or more positions at the right of a central symmetry axis parallel to the roll axis of the aircraft. Any load placed at a distance from this symmetry axis generates a lateral moment equal to the weight of the load multiplied by the distance from the symmetry axis.
[0022] Each row has one or more positions at the right and one or more positions at the left, where right and left are chosen as reference for this description as right and left according to the plan view.
[0023] The method further comprises receiving information about the maximum load imbalance lateral moment allowed for the particular aircraft associated with the layout. This maximum value will be used as a reference value to check if the estimated value of the load imbalance lateral moment is admissible.
[0024] As previously mentioned, the empty rows will identify rows whose side is locked and cannot be loaded. This is the case when the fixture is broken or there are certain specific reasons that cause that side of the row to be unavailable for storing load units.
[0025] In the first aspect of the invention, the relevant empty rows are those empty rows at the same side, because the locked side cancels the empty rows at the opposite side. That is, the number of empty rows that induce an imbalance lateral moment is the number of empty rows at the same side.
[0026] The method estimates the lateral moment of the imbalance load for the case when the layout has no empty rows, when there is one empty row, when there are two empty rows, etc., up to the maximum number of empty rows R.
[0027] The method according to the first aspect of the invention further comprises the steps of:
[0028] For i = 0, 1,..., R, a number of simulations of the loading of the load space are implemented according to the received layout, where for each simulation:
[0029] 1) i rows are randomly selected to be empty, such empty rows being empty at the same side;
[0030] 2) the weight of each unlocked position is determined as a random value in response to a probability function or probability distribution of the weight, generating a random load distribution;
[0031] These steps randomly select empty rows (where the locked loading positions are at one side, and all selected rows with locked loading positions are at the same side) and randomly fill the load units according to a predetermined probability function. It has been pointed out that the weight of each unlocked position is in response to a probability function or probability distribution, because a probability function is defined by its probability distribution, and a probability distribution is defined by its probability function.
[0032] Likewise, it is considered equivalent to use other ways to express the value of the unit load, for example expressed as a percentage of weight with respect to the maximum weight to be loaded.
[0033] As a result of these steps, for each number of empty rows, a plurality of statistically estimated weight distributions over the entire layout is obtained. That is, for each number of empty rows, there are a plurality of statistically distributed loads that induce different lateral moments.
[0034] The method according to the first aspect of the application further comprises the steps of:
[0035] for each i = 0, 1,..., R,
[0036] i. generating a random load distribution by accumulating the random load distributions of a plurality of simulations in the case of i empty rows;
[0037] ii. determining the lateral moment of the accumulated load distribution with respect to the axis of symmetry in the case of i empty rows;
[0038] iii. determining that the loading condition in the aircraft with i empty rows is feasible if the imbalance lateral moment measured in the accumulated random load distribution in the previous step ii) is lower than the maximum load imbalance lateral moment value, otherwise determining that it is not feasible;
[0039] providing the data to be processed when loading the aircraft, identifying as load distributions to be prevented the load distributions that respond to the number of empty rows as a non-feasible condition.
[0040] In this set of steps, first and for each number of empty rows, a load distribution is generated as a result of accumulating all the distributions randomly obtained in the previous steps. That is, a single distribution is obtained, not with a plurality of random experiments. It is this distribution that enables the calculation of the lateral moment with respect to the axis of symmetry and this calculation is repeated for each number of empty rows.
[0041] For each number of empty rows, the lateral moment it generates is calculated and compared with the maximum value. Thus, there are as many comparisons as the number of simulated empty rows. The result for each number of empty rows is independent of the result for a different number of empty rows.
[0042] These results are provided by the method so that information is sent to the device or processor responsible for establishing the safety of the aircraft when loading.
[0043] At loading, it is known how many rows are empty rows. From the information provided by the method according to the first aspect of the application, the state calculated for this number of empty rows is verified, and if the calculated state is infeasible, the aircraft is not loaded because it is estimated that the loading will result in a lateral moment about the roll axis greater than the allowed. On the other hand, if the value of the state is "feasible" for this number of empty rows, the aircraft is allowed to be loaded and the loading process continues. That is, the next step uses this information to establish whether the aircraft is loaded in such a way that ensures a safe flight.
[0044] According to an embodiment of the previously disclosed method, step 2) is performed multiple times for the i rows selected in step 1), generating multiple random load distributions, which are then accumulated into a single random load distribution.
[0045] According to another embodiment of the previously disclosed embodiment, steps 1) and 2) are performed multiple times, with a different set of empty rows being randomly selected each time.
[0046] According to this embodiment, the same number of empty rows can have different positions, and in this embodiment, multiple combinations of positions for the empty rows are explored, providing a rich distribution, which is then accumulated. This enables to identify distributions in which the position of the empty rows can provide different results. This is the case, for example, in which the spatial distribution of the loading positions of the rows is different, and even for the same weight, selecting different rows as empty rows will result in different lateral moments.
[0047] According to another embodiment of any of the previously disclosed embodiments, R = N.
[0048] In this particular embodiment, all cases in which even the entire aircraft has empty rows are explored. In this case, the method provides information for any possibility of the layout.
[0049] According to another embodiment of any of the previously disclosed embodiments, the weight of each unlocked position is further determined as a random value from a probability function or probability distribution responsive to the weight of the load cell is according to the following steps:
[0050] - generating a list of weights for the total number of unlocked positions according to the probability function or probability distribution;
[0051] - ordering the generated list;
[0052] - for each row, assigning the load to the unlocked positions from the list according to the order of the ordering, minimizing the unbalanced lateral moment for each row.
[0053] In either case, whenever it is stated that the weight value of a unit load is assigned in response to a probability density function, it should be interpreted as taking a random value according to the probability density function or probability distribution.
[0054] In some practical cases, the operator in charge of loading the aircraft determines to arrange the loads by weight and uses the ordered weight to assign the rows, for example, alternating the assignment on one side and on the opposite side, in opposite positioning and at the same distance, to implement a loading that reduces the lateral moment of loads with very different weights. Since the ordering process groups unit loads with close weights, if the weights of two unit loads are very different, such two loads will be in different rows and will be at least partially counterbalanced by the weight of other load units with close weights.
[0055] This action reduces the lateral moment generated by the whole set of load units and is introduced into the simulation process, but since the loads are unknown, an ordering process is implemented on the whole set of weights, which are randomly determined by sampling a probability density function. In this case, the number of cases that are expected to result in infeasible states is less.
[0056] A second aspect of the present application is a data processing system comprising a processor configured to perform the steps of the method according to the first aspect of the present application or according to any one of the embodiments of the first aspect of the present application.
[0057] A third aspect of the present application is a computer program product comprising instructions which, when the program is executed by a computer, cause the computer to carry out the steps of the method according to the first aspect of the present application or according to any one of the embodiments of the first aspect of the present application. BRIEF DESCRIPTION OF DRAWINGS
[0058] These and other features and advantages of the present application will become more apparent from the following detailed description of preferred embodiments, provided by way of illustration and by way of non-restricting example only, with reference to the appended drawings.
[0059] Figure 1 This figure shows an embodiment of the layout processed by the processor to estimate the lateral moment or torque generated due to the lack of load balance with respect to the roll axis of the aircraft when there are two empty rows in the load space.
[0060] Figure 2 This figure schematically shows the loading process of an aircraft in which the method provides a safety system that prevents a loading that is estimated to be infeasible. DETAILED DESCRIPTION
[0061] As will be appreciated by one skilled in the art, aspects of the present application can be embodied as a system, method, or computer program product.
[0062] According to an embodiment of the method, there is a first step of receiving data, in this case, by means of a data line, a request for the loading feasibility state of the aircraft. As Figure 1 As this information shows, the layout of the load space of the aircraft shows those positions (L) in which a load unit (W) can be placed and fixed. The layout schematically shows the positions (L) as squares and if a load unit (W) is located in the center of a position (L), the load unit (W) causes a lateral moment of force with respect to the axis of symmetry (X-X'), which is parallel to the roll axis of the aircraft. The sum of the lateral moments of force of all unit loads (W) must be compensated by the wings and, therefore, the maximum lateral moment of force of the entire load is stable according to the aircraft to ensure the safety of the aircraft.
[0063] At this stage, only the number of positions and the total load to be loaded are known and, therefore, each load unit (W) is defined to statistically present a Gaussian distribution whose mean is equal to the total load divided by the number of available positions and with a predetermined variance.
[0064] Figure 1 It is also shown that two load units (W) have already been installed and the lateral moment of force of one of the load units (W) is calculated as the weight of the load unit (W) estimated by random sampling of the Gaussian probability function multiplied by the distance (d) from the center of mass to the axis of symmetry.
[0065] The number of maximum lateral moments of force and the number of maximum empty rows R are also received as data.
[0066] The method generates a plurality of simulations for each i = 0, 1,..., R by means of the following steps:
[0067] - randomly selecting i rows as empty rows, such empty rows being empty at the same side;
[0068] - determining the weight of each unlocked position as a random value in response to a probability function or probability distribution of the weight, generating a random load distribution;
[0069] In one of these steps, when i = 2, two empty rows are selected: the empty rows 4 and 6, counting the rows starting from the top of the figure, wherein the two selected empty rows are not allowed to be loaded at the right side. The locked positions (L) are identified by the dashed squares.
[0070] Once the simulation has sampled the weight of each unlocked position (L), such simulation is repeated a plurality of times, thus enabling to obtain an aggregated or cumulative statistical distribution. This resulting cumulative statistical distribution is used to calculate the identified unbalanced lateral moment of force for i = 2.
[0071] If the unbalanced lateral moment is greater than the maximum lateral moment allowed for the aircraft, the condition for i = 2 is determined to be infeasible.
[0072] The same procedure is repeated for other values of i.
[0073] According to another embodiment, since the two selected rows are randomly selected several times, information is provided, for example, of several cases of selected rows having different conditions, so the cumulative distribution is enriched. The first row or the two rows positioned and at the ends (where the number of positions (L) at each side is less and closer to the symmetry axis) are cases of this.
[0074] Figure 2 The input lines (1) are shown and the output lines (3), the input lines providing initial data to the system (2) which comprises a processor (2.1) adapted to implement the method according to the first aspect of the application, the output lines being connected to a checking system (4) in which the operator assigned to control the loading of the aircraft indicates which rows are empty rows and verifies the status of the number of empty rows according to the information provided by the system (2).
[0075] When the status is infeasible, an alarm (4.1) is triggered and the aircraft is prevented from being loaded in these cases, preventing it from flying in unsafe conditions.
Claims
1. A computer-implemented method for preventing an infeasible loading state in an aircraft, a load to be loaded in the aircraft comprising a plurality of load units (W), the method comprising: in any order: a) receiving data of a layout of a load space of the aircraft, the layout comprising: a set of N rows, each row comprising a set of M positions (L), the M positions (L) having a subset of left positions (L) and a subset of right positions (L); for each position (L) the distance of the position (L) to a symmetry axis (X-X’), the distance being used to measure a lateral moment of a load, the symmetry axis (X-X’) being parallel to a roll axis of the aircraft; b) receiving a maximum load unbalance lateral moment value; c) receiving a probability function or a probability distribution of weights of load units (W); d) pre-determining a maximum number R of empty rows to be checked, an empty row being a row in which one side, either the right or the left side, is locked so that the positions (L) of the selected row cannot be loaded, while the opposite side is not locked to allow being loaded; for i = 0, 1,..., R, implementing a plurality of simulations of loading the load space according to the received layout, wherein for each simulation: 1) randomly selecting i rows as empty rows, such empty rows being empty on the same side; 2) determining a weight for each unlocked position (L) as a random value responsive to the probability function or the probability distribution of weights, generating a random load distribution; for each i = 0, 1,..., R, i. generating a random load distribution by accumulating the random load distributions of the plurality of simulations in the case of i empty rows; ii. determining the lateral moment of the accumulated load distribution with respect to the symmetry axis (X-X’) in the case of i empty rows; iii. determining that the loading state in the aircraft with i empty rows is feasible if the unbalance lateral moment measured on the accumulated random load distribution in the previous step ii) is lower than the maximum load unbalance lateral moment value, otherwise determining that it is infeasible; providing data to be processed in loading the aircraft, identifying as load distributions to be prevented in infeasible states the load distributions responsive to the number of empty rows.
2. The method of claim 1, wherein, performing step 2) a plurality of times for the i rows selected in step 1), generating a plurality of random load distributions which are then accumulated into a single random load distribution.
3. The method of claim 1 or 2, wherein, performing steps 1) and 2) a plurality of times with a different set of empty rows randomly selected.
4. The method according to any of the preceding claims, wherein, R = N.
5. The method according to any of the preceding claims, wherein, determining a weight for each unlocked position as a random value responsive to the probability function or the probability distribution of weights of load units is according to the following steps: - generating a list of weights for the total number of unlocked positions according to the probability function or the probability distribution; - sorting the generated list; - for each row, assigning loads to unlocked positions from the list according to the order of sorting, minimizing the unbalance lateral moment for each row.
6. A data processing system comprising a processor configured to perform the steps of the method according to any one of claims 1 to 5.
7. A computer program product comprising instructions which, when the program is executed by a computer, cause the computer to carry out the steps of the method according to any one of claims 1 to 5.