A method for rapid analysis of the center of gravity of a multi-mount aircraft

Abstract

This invention belongs to the field of aircraft loadout design, specifically relating to a rapid method for analyzing the center of gravity (COP) of multi-loaded aircraft. Conventional analysis methods are cumbersome and slow, making it difficult to meet the needs of rapid iteration in hardpoint layout and external loadout schemes during the design phase. This invention addresses the challenges of complex COP analysis and iterative difficulties caused by the large number of hardpoints, external loadout types, and loadout schemes on multi-loaded aircraft. It proposes a variable-parameter design method that records the COP of all external loadouts in a table as a combination of fixed and variable parameters. The variable parameters based on hardpoint layout are used to quickly adjust the COP values ​​of all external loadouts. Modular formulas are then used to quickly construct the COP of the loadout scheme, which is then superimposed on the aircraft's COP to rapidly analyze the impact of the loadout scheme on the aircraft's COP, providing data support for optimizing hardpoint layout and external loadout schemes.

Description

Technical Field

[0001] This invention belongs to the field of aircraft payload design, specifically relating to a method for rapid analysis of the center of gravity of multi-mounted aircraft. Background Technology

[0002] For the overall design of new attack aircraft, diverse payloads are required to meet complex mission requirements, generally characterized by numerous hardpoints, various types of external stores, and numerous payload configurations. For example, one type of attack aircraft may have as many as 14 hardpoints and over 20 types of external stores, resulting in hundreds of potential payload configurations. Furthermore, given the aircraft's small tonnage, this dense payload configuration has a significant impact on the aircraft's center of gravity. To prevent payload configurations from exceeding the aircraft's center of gravity limitations and to determine appropriate hardpoint arrangements, iterative analysis of the impact of payload configurations on the aircraft's center of gravity is necessary during the design phase.

[0003] The conventional analysis method involves first constructing a table of fixed center-of-gravity positions of each external store in the aircraft's coordinate system based on the original layout of the hardpoints. Then, the center-of-gravity of the external stores is manually copied and combined to form the desired loadout scheme. Finally, the center of gravity of the aircraft itself is superimposed to analyze the center of gravity of different loadout schemes. This approach is inherently labor-intensive for multi-loadout aircraft, requiring a complete analysis of the center of gravity for all loadout schemes. Furthermore, any change in the hardpoint layout necessitates manually updating the table of fixed center-of-gravity positions for each external store and recalculating the entire process. This cumbersome operation and slow calculation speed make it difficult to meet the rapid iteration requirements for hardpoint layout and external storeout schemes during the design phase. Summary of the Invention

[0004] This invention addresses the challenges of complex center of gravity analysis and iterative difficulties caused by the numerous hardpoints, various external stores, and multiple mounting schemes on multi-mounted aircraft. It proposes a variable-parameter design method that records the center of gravity of all external stores in a table format, combining fixed and variable parameters. The method utilizes variable parameters based on hardpoint layout to quickly adjust the center of gravity values ​​of all external stores. Modular formulas are then used to rapidly construct the center of gravity of each mounting scheme, which is then superimposed with the aircraft's own center of gravity. This allows for rapid analysis of the impact of mounting schemes on the aircraft's center of gravity, providing data support for optimizing hardpoint layouts and external store configurations.

[0005] This invention proposes a rapid method for center of gravity analysis of multi-armed aircraft, which includes the following steps:

[0006] S1. Construct a fixed parameter table for external attachments and record the position parameters of the center of gravity of the attachment or weapon in its own coordinate system;

[0007] S2. Construct a variable parameter table for the attachment points and record the attachment point position parameters based on the aircraft coordinate system;

[0008] S3. Construct a center of gravity data table for external attachments, and record the position of the center of gravity of the external attachments in the aircraft coordinate system obtained through coordinate transformation;

[0009] S4. Determine the mounting scheme table;

[0010] S5. Calculate the center of gravity of the mounting scheme. By searching and referencing the center of gravity data table of external attachments, obtain the combination table of center of gravity data of various external attachments in the mounting scheme and calculate it.

[0011] S6. Calculate the center of gravity after the mounting scheme is combined with the aircraft body;

[0012] S7. Based on the aircraft's center of gravity usage restrictions, analyze whether the aircraft's center of gravity meets the requirements for each mounting scheme. If it does not meet the requirements or a better scheme needs to be sought, adjust the mounting point position or mounting scheme, and return to S2.

[0013] S8. Generate a summary table of the mounting scheme's center of gravity and compile a report.

[0014] Advantageously, in S1, the intersection of the center line of the mounting bracket or weapon lug and its own upper surface is used as the origin to determine its own coordinate system.

[0015] Advantageously, S3 filters out combination relationships based on the matching relationship between weapon type, rack capability and hardpoint.

[0016] Advantageously, the S4 determines the mounting scheme table based on operational requirements.

[0017] Advantageously, using the name of the add-on as a keyword for searching and referencing.

[0018] Advantageously, the aircraft's heading is taken as the X-axis, the aircraft's altitude as the Y-axis, and the aircraft's wingspan as the Z-axis.

[0019] Advantageously, the center of gravity of the mounting scheme and the center of gravity after mounting can be automatically calculated by compiling a calculation module.

[0020] Advantageously, the center of gravity data is updated in real time as the variable parameters are adjusted.

[0021] Beneficial effects: The rapid analysis method for the center of gravity of multi-mounted aircraft in this invention is mainly to solve the problems of cumbersome operation and slow calculation speed when iteratively analyzing the impact of a large number of mount schemes on the center of gravity of multi-mounted aircraft in the design stage. It proposes a variable parameter design method for rapid analysis and has high engineering application value. Attached Figure Description

[0022] Figure 1 This is a flowchart illustrating the implementation of the method of this invention;

[0023] Figure 2 This is an example of constructing fixed parameters for an add-on;

[0024] Figure 3 This is an example of constructing a variable parameter representation;

[0025] Figure 4 This is an example of a mounting scheme;

[0026] Figure 5 This is a schematic example of the center of gravity calculation for the mounting scheme. Detailed Implementation

[0027] The technical solution of the present invention will be further described below with reference to the accompanying drawings.

[0028] This application provides a rapid center of gravity analysis method for multi-mounted aircraft. In this embodiment, the aircraft heading is taken as the X-axis, the aircraft altitude direction as the Y-axis, and the aircraft wingspan direction as the Z-axis. The analysis process is as follows: Figure 1 As shown, the main steps include:

[0029] Step 1: Construct a fixed parameter table for the add-on.

[0030] See Figure 2 External attachments include various racks, auxiliary fuel tanks and weapons. Generally, the intersection of the center line of the rack or weapon's lifting lug and its own upper surface is used as the origin of the coordinate system to determine the position parameters of the rack or weapon's center of gravity in its own coordinate system, and these parameters are recorded in a fixed parameter table in combination with the weight parameters.

[0031] Step 2, construct the variable parameter table of the attachment point.

[0032] See Figure 3 Based on the aircraft coordinate system, establish the position parameters of several attachment points and record them in the variable parameter table;

[0033] Step 3, construct the external object center of gravity data table

[0034] Based on the matching relationship between weapon type, pylon capacity and hardpoint, the center of gravity position of the external stores in the aircraft coordinate system is obtained through coordinate transformation, and summarized into an external store center of gravity data table.

[0035] If a bomb 1 is mounted on a mounting point 2 via a mounting bracket 3, the external attachment data of bomb 1 is generated by adding the center of gravity position of bomb 1 in the fixed parameter table to the position parameter of mounting point 2 in the variable parameter table. Similarly, the center of gravity data table of all external attachments after mounting can be constructed.

[0036] The center of gravity data in this table is updated in real time as the variable parameters are adjusted, which facilitates rapid iterative analysis of the impact of the anchor point location on the center of gravity.

[0037] Step 4, determine the mounting scheme table

[0038] See Figure 4 The mounting scheme is determined according to operational requirements, resulting in different combinations of mounting schemes;

[0039] Step 5: Calculate the center of gravity of the mounting scheme.

[0040] See Figure 5 First, by searching and referencing (using the name of the add-on as a keyword) the add-on center of gravity data table, a combination table of center of gravity data for various add-ons in the mounting scheme is obtained. Second, based on the center of gravity data of the add-ons in the mounting scheme, the weights are directly added together, and the torque balance formula is applied to the center of gravity.

[0041] Let's calculate the total center of gravity of each mounting scheme separately.

[0042] Step 6: Analyze the impact of the mounting scheme on the aircraft's center of gravity. Combining the center of gravity data of the mounting scheme and the aircraft's center of gravity, and referring to the center of gravity formula in Step 5, calculate the impact of each mounting scheme on the aircraft's center of gravity.

[0043] Step 7: Based on the aircraft's center of gravity usage constraints, analyze whether the aircraft's center of gravity meets the requirements for each mounting scheme. If it does not meet the requirements or a better scheme is sought, the hardpoint positions or mounting schemes can be adjusted. The system will automatically refresh to obtain the center of gravity results of the aircraft with the adjusted mounting schemes, achieving a rapid iteration effect.

[0044] Step 8: Generate a summary table of the mounting scheme's center of gravity and compile a report.

Claims

1. A method for rapid analysis of the center of gravity of a multi-mount aircraft, comprising: The method includes the following steps: S1. Construct a fixed parameter table for external attachments and record the position parameters of the center of gravity of the attachment or weapon in its own coordinate system; S2. Construct a variable parameter table for the attachment points and record the attachment point position parameters based on the aircraft coordinate system; S3. Construct a center of gravity data table for external attachments, and record the position of the center of gravity of the external attachments in the aircraft coordinate system obtained through coordinate transformation; S4. Determine the mounting scheme table; S5. Calculate the center of gravity of the mounting scheme. By searching and referencing the center of gravity data table of external attachments, obtain the combination table of center of gravity data of various external attachments in the mounting scheme and calculate it. S6. Calculate the center of gravity after the mounting scheme is combined with the aircraft body; S7. Based on the aircraft's center of gravity usage restrictions, analyze whether the aircraft's center of gravity meets the requirements for each mounting scheme. If it does not meet the requirements or a better scheme needs to be sought, adjust the mounting point position or mounting scheme, and return to S2. S8. Generate a summary table of the mounting scheme's center of gravity and compile a report.

2. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: In S1, the origin of the coordinate system is determined by the intersection of the center line of the mounting bracket or weapon lug and the upper surface of the device itself.

3. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: In S3, combination relationships are filtered based on the matching relationship between weapon type, rack capability, and mounting point.

4. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: The S4 determines the mounting scheme table based on operational requirements.

5. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: Search and reference based on the name of the add-on item.

6. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: The aircraft's heading is taken as the X-axis, the aircraft's altitude as the Y-axis, and the aircraft's wingspan as the Z-axis.

7. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: The calculation module automatically calculates the center of gravity of the mounting scheme and the center of gravity after mounting.

8. The method for rapid center of gravity analysis of multi-mounted aircraft according to claim 1, characterized in that: The center of gravity data is updated in real time as the variable parameters are adjusted.

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