Method, system, device and medium for evaluating launch vehicle payload separation compatibility
By using CFD steady-state calculations and compatibility criteria, the problem of rapid and comprehensive assessment of payload separation safety in aircraft design was solved, enabling efficient and accurate support for delivery bay design and improving the overall layout optimization of the aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
- Filing Date
- 2026-05-18
- Publication Date
- 2026-06-12
AI Technical Summary
Existing technologies make it difficult to quickly and comprehensively assess the safety of payload separation in the initial design phase of an aircraft. Traditional methods are time-consuming and labor-intensive, and cannot meet the needs of comparing multiple options.
By employing CFD steady-state calculation methods and combining information on the mass and inertia of the deployed payload, an aerodynamic and aerodynamic moment model of the payload separation process is established. Separation compatibility criteria are constructed, structural parameters are simplified, and the focus is on length-to-depth ratio and key flight parameters to achieve rapid evaluation.
It significantly improves the efficiency and accuracy of separation compatibility assessment, adapts to the rapid assessment needs in the preliminary design stage, provides a systematic and standardized assessment process, reduces computational complexity, and improves the reliability of assessment results.
Smart Images
Figure CN122197747A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of computational fluid dynamics, and in particular to a method, system, device, and medium for evaluating the compatibility of payload separation during aircraft deployment. Background Technology
[0002] As aircraft design continues to evolve towards higher speeds, higher efficiency, and optimized aerodynamics, internal delivery capsules have become the mainstream design approach due to their ability to effectively reduce aircraft drag and optimize overall aerodynamic layout. They are widely used in the design of various aircraft carrying delivery payloads. However, the working environment of an internal delivery capsule exhibits significant aerodynamic differences. After the capsule is opened, the internal flow velocity is much lower than the external flow velocity. This velocity difference easily causes the airflow shear layer to shift inwards, forming a complex shock wave interference structure around the capsule door. This structure alters the stress state during payload separation, thus adversely affecting the normal separation of the payload.
[0003] The structural dimensions of the delivery capsule are a key factor affecting the internal and surrounding flow structure. Differences in the flow structure directly impact the delivery and separation process of the payload. If the payload experiences a large nose-up aerodynamic moment during separation, it can cause a significant attitude lift, easily leading to interference problems and affecting the safety of delivery and separation. With the development of computational fluid dynamics (CFD) technology, it has been widely applied in aircraft layout design and performance evaluation. Through this technology combined with wind tunnel testing, it has been found that the length-to-depth ratio of the delivery capsule and the aircraft's Mach number categorize the flow characteristics of the delivery capsule into three types: open, transitional, and closed. Open flow characteristics are more conducive to payload separation, while closed flow characteristics pose potential risks to payload separation.
[0004] However, in the actual design process of aircraft, as the flight altitude and speed of aircraft continue to increase, the overall structure of the aircraft places more constraints on the size and installation position of the delivery capsule. Relying solely on analyzing the flow characteristics of the delivery capsule is no longer sufficient to comprehensively and accurately assess the separation safety of the delivered payload, as it lacks consideration of the actual separation motion state of the delivered payload. On the other hand, traditional methods for assessing the separation safety of the delivered payload often employ unsteady numerical simulations using computational fluid dynamics (CFD) or wind tunnel tests to obtain the delivery payload separation trajectory. These methods require significant computational resources and time costs, and the acquisition cycle for a single separation trajectory is long, making it difficult to meet the actual needs of multi-scheme comparison and rapid evaluation in the preliminary design stage of the delivery capsule. Therefore, there is an urgent need for an efficient, comprehensive, and adaptable method for assessing the separation compatibility of the delivery payload within the aircraft's embedded delivery capsule in the preliminary design stage. Summary of the Invention
[0005] To address the aforementioned issues, this invention proposes a method, system, equipment, and medium for evaluating the compatibility of payload separation in aircraft deployments. Utilizing CFD simulation, the aerodynamic characteristics of the deployed payload near the hatch are obtained through numerical simulation. Combined with information on the payload's mass and inertia, the separation process and the positional relationship with the deployment compartment are analyzed, thereby assessing the safety of payload separation and supporting compatible payload separation design.
[0006] The technical solution adopted in this invention is as follows: A method for evaluating the compatibility of payload separation during aircraft delivery includes: The structural dimensions of the delivery module embedded inside the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload are determined in order to determine the launch location and launch conditions. The payload is placed at the launch position, and the aerodynamic forces and torques acting on the payload are simulated using a CFD steady-state calculation method based on the launch conditions. Based on the aforementioned aerodynamic forces and aerodynamic torques, and combined with the mass and inertia information of the deployed load, a relationship function is established between the descent distance and pitch attitude angle and time during the separation process of the deployed load. By combining the aforementioned relationship function and safety assessment parameters, a separation compatibility judgment criterion is constructed to determine whether the separation of the deployed payload and the embedded deployment compartment is compatible.
[0007] Furthermore, the method for determining the structural dimensions of the delivery compartment embedded in the aircraft includes: ignoring the internal details of the delivery compartment during the preliminary design stage, and simplifying the structural dimensions of the delivery compartment to length L, width W, and depth D, wherein the length-to-depth ratio L / D is used as a key parameter affecting the separation characteristics.
[0008] Furthermore, the method for determining the key flight parameters for the launch of the payload includes: Considering the main aerodynamic parameters affecting the launch of payloads embedded within the aircraft, including the incoming flow velocity Flow pressure Angle of attack and flight sideslip angle And there are:
[0009]
[0010] in, c The speed of sound at height H. Let H be the air density at altitude H; therefore, the key flight parameter for payload launch is determined as: Mach number. Ma Altitude H, Angle of Attack and flight sideslip angle .
[0011] Furthermore, the method for determining the safety assessment parameters for the separation of the deployed payload includes: Treat the lower surface of the aircraft as a plane Determine the position parallel to the plane in the side view. The baseline OX; Determine the payload's nose apex A, bottom control surface endpoint B, and center of mass C, where points A and B have the best chance of impacting the plane. A collision occurs, forming an angle. or ; During the payload separation process, the pitch angle of the deployed payload. It should be between the included angles and Between, that is:
[0012]
[0013]
[0014] in, It is the distance from the head of the deployed payload to the center of mass. It refers to the length of the load being deployed.
[0015] Further, the step of placing the payload at the launch position and, based on the launch conditions, simulating the aerodynamic forces and moments acting on the payload using a CFD steady-state calculation method includes: The payload is placed at the launch position of the launch compartment. Based on the typical combination of launch parameters for internally embedded payloads, the aerodynamic forces and aerodynamic moments of the payload under different launch conditions are obtained using the CFD steady-state calculation method. If the coordinate system is defined with the x-axis pointing from the nose to the tail of the aircraft, the y-axis pointing from the nose to the right, and the z-axis pointing upwards in the opposite direction of gravity, then the normal force is... The pitching moment is .
[0016] Furthermore, based on the aforementioned aerodynamic forces and aerodynamic moments, and combined with the mass and inertia information of the deployed load, a relationship function is established between the descent distance and pitch attitude angle during the load separation process and time, including: Obtain the mass and inertia information of the deployed payload, where the mass of the deployed payload is... m The moment of inertia of the deployed load is ; Using the force conditions of the load at the initial moment, the descent distance and pitch attitude angle are established longitudinally over time. t Approximate expression for the change:
[0017]
[0018] in, h For the descent distance, The pitch angle for payload delivery. The initial falling speed, ω is the angular velocity.
[0019] Furthermore, a separation compatibility determination criterion is constructed by combining the aforementioned relationship function and security assessment parameters, including: Considering safety margin The separation compatibility criterion is constructed as a function of descent distance and time:
[0020]
[0021] in, and These are undetermined coefficients; if the inequality is not satisfied, then the separation is determined to be incompatible.
[0022] A system for evaluating the compatibility of payload separation during aircraft delivery includes: The parameter determination module is configured to determine the structural dimensional parameters of the delivery capsule embedded in the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload, thereby determining the launch location and launch conditions. The aerodynamic characteristic calculation module is configured to place the released load at the launch position and, based on the launch conditions, use a CFD steady-state calculation method to simulate the aerodynamic force and aerodynamic torque acting on the released load. The relational function calculation module is configured to establish a relational function of the descent distance and pitch attitude angle as a function of time during the separation of the deployed load, based on the aerodynamic force and aerodynamic torque, combined with the mass and inertia information of the deployed load; The compatibility assessment module is configured to combine the relationship function and safety assessment parameters to construct a separation compatibility judgment criterion, thereby determining whether the separation of the delivery payload and the embedded delivery capsule is compatible.
[0023] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the aircraft payload separation compatibility assessment method.
[0024] A computer-readable storage medium storing a computer program that, when executed by a processor, implements the method for evaluating the compatibility of payload separation during aircraft deployment.
[0025] The beneficial effects of this invention are as follows: 1. This invention significantly improves the efficiency of separation compatibility assessment, meeting the rapid assessment needs of the preliminary design stage. This invention abandons traditional CFD unsteady numerical simulation and wind tunnel testing methods, employing steady CFD calculation methods throughout to simulate the aerodynamic stress state of the deployed payload. This greatly reduces the computation time and resource consumption of numerical simulation, solving the time-consuming and labor-intensive problems of traditional methods. It can quickly complete separation compatibility assessments under single or multiple launch conditions, meeting the practical engineering needs of multi-scheme comparison and rapid selection in the preliminary design stage of the deployment module.
[0026] 2. This invention establishes a systematic and standardized evaluation process, enhancing the comprehensiveness and logical consistency of the evaluation. It establishes a complete evaluation process from parameter determination to force simulation, then to the construction of motion relationship functions, and finally to compatibility determination. It sequentially determines three core parameters: the structural dimensions of the delivery capsule, flight, and separation safety, and clarifies the launch location and conditions. Subsequent analysis is then conducted in conjunction with the mass and inertia information of the delivery payload itself. Each step is interconnected and mutually reinforcing, breaking away from the traditional single evaluation model that relies solely on the flow characteristics analysis of the delivery capsule. This enables a multi-dimensional consideration of the delivery payload separation process, making the evaluation process more systematic and standardized.
[0027] 3. This invention enables the scientific simplification and quantitative definition of evaluation parameters, reducing analytical complexity while ensuring evaluation effectiveness. During the preliminary design phase of the delivery capsule, internal details are ignored, simplifying structural dimensional parameters and focusing on the key parameter of length-to-depth ratio. Simultaneously, flight aerodynamic parameters are converted into more general parameters suitable for aerodynamic analysis. Furthermore, a clear quantitative range for pitch attitude angles is defined for separation safety assessment, making the acquisition and analysis of various parameters more targeted. This reduces the complexity of parameter analysis while ensuring the effectiveness of core parameters in separation compatibility assessment, thus meeting the parameter analysis needs of the preliminary design phase.
[0028] 4. This invention establishes a quantitative motion relationship model and judgment criteria, improving the accuracy and operability of the evaluation results. Based on the aerodynamic forces and torques obtained from CFD steady-state calculations, combined with the mass and inertia information of the deployed load, a quantitative relationship function is established in the longitudinal direction for the changes in the descent distance and pitch attitude angle of the deployed load over time, transforming the separation motion state of the deployed load into a calculable mathematical model. Simultaneously, a safety margin is introduced and an inequality-form separation compatibility judgment criterion is constructed, transforming the abstract separation compatibility judgment into concrete numerical verification. The judgment criteria are clear, the operation process is simple, and the introduction of the safety margin takes into account the safety requirements in engineering applications, significantly improving the accuracy and reliability of the evaluation results.
[0029] 5. This invention provides a precise basis for payload separation and compatibility design, which can help optimize the overall layout of the aircraft. By accurately analyzing the motion state and compatibility results during the payload separation process, this invention can identify the key factors affecting separation compatibility in the design of the delivery bay and the setting of flight parameters. It provides specific and feasible design basis for optimizing the size and position of the delivery bay and setting the launch parameters of the delivery payload. From the delivery and separation stage, it provides support for optimizing the overall aerodynamic layout and structural design of the aircraft, and improves the rationality of the overall aircraft design. Attached Figure Description
[0030] Figure 1 This is a flowchart of a method for evaluating the compatibility of payload separation during aircraft deployment, according to an embodiment of the present invention.
[0031] Figure 2 This is a schematic diagram of the delivery compartment structure in Embodiment 2 of the present invention.
[0032] Figure 3 This is a schematic diagram of the pitch attitude angle during the load drop process in Embodiment 2 of the present invention.
[0033] Figure 4 This is a schematic diagram of the head collision of the deployed load in Embodiment 2 of the present invention.
[0034] Figure 5 This is a schematic diagram of the bottom collision of the deployed load in Embodiment 2 of the present invention.
[0035] Figure 6 This is a schematic diagram of the launch position of the payload in Embodiment 2 of the present invention. Detailed Implementation
[0036] To provide a clearer understanding of the technical features, objectives, and effects of the present invention, specific embodiments are now described. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention; that is, the described embodiments are only a part of the embodiments of the invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.
[0037] Example 1 like Figure 1 As shown, this embodiment provides a method for evaluating the compatibility of payload separation during aircraft deployment, including: The structural dimensions of the delivery module embedded inside the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload are determined in order to determine the launch location and launch conditions. The payload is placed at the launch position, and the aerodynamic forces and torques acting on the payload are simulated using a CFD steady-state calculation method based on the launch conditions. Based on the aforementioned aerodynamic forces and aerodynamic torques, and combined with the mass and inertia information of the deployed load, a relationship function is established between the descent distance and pitch attitude angle and time during the separation process of the deployed load. By combining the aforementioned relationship function and safety assessment parameters, a separation compatibility judgment criterion is constructed to determine whether the separation of the deployed payload and the embedded deployment compartment is compatible.
[0038] Preferably, in the preliminary design stage, the internal details of the launch compartment are ignored, and the structural dimensions of the launch compartment are simplified to length L, width W, and depth D, with the length-to-depth ratio L / D being the key parameter affecting separation characteristics. It should be noted that this step simplifies the structural dimensions of the launch compartment by ignoring non-critical internal details, reducing the difficulty of parameter acquisition and analysis in the preliminary design stage. Simultaneously, focusing on the key parameter of length-to-depth ratio makes subsequent separation characteristic analysis more targeted and effectively reduces unnecessary computation.
[0039] Preferably, the main aerodynamic parameters affecting the launch of payloads embedded within the aircraft are considered, such as the incoming flow velocity. Flow pressure Angle of attack and flight sideslip angle And there are:
[0040]
[0041] in, c The speed of sound at height H. Let H be the air density at altitude H; therefore, the key flight parameter for payload launch is determined as: Mach number. Ma Altitude H, Angle of Attack and flight sideslip angle .
[0042] It should be noted that this step standardizes and simplifies the launch flight parameters for the payload, avoids redundancy in the correlation between the original parameters, and makes the setting of subsequent launch conditions and numerical simulation calculations simpler and more efficient. At the same time, the converted parameters are more in line with the general application requirements of aerodynamic analysis, thus improving the versatility of the parameters.
[0043] Preferably, the lower surface of the aircraft is considered as a plane. Determine the position parallel to the plane in the side view. The baseline OX is used to determine the payload's nose apex A, bottom control surface endpoint B, and center of mass C, where points A and B have the best chance of aligning with the plane. A collision occurs, forming an angle. or During the load separation process, the pitch angle of the deployed load. It should be between the included angles and Between, that is:
[0044]
[0045]
[0046] in, It is the distance from the head of the deployed payload to the center of mass. It refers to the length of the load being deployed.
[0047] It should be noted that this step defines a clear quantitative evaluation standard for the safety of payload separation. By determining the feature points and the included angle range, the abstract separation safety requirements are transformed into specific attitude angle numerical ranges, providing a clear and practical basis for subsequent separation compatibility determination.
[0048] Preferably, the payload is placed at the launch position of the launch bay. Based on typical internally embedded payload launch parameter combinations, the aerodynamic forces and moments acting on the payload under different launch conditions are obtained using a CFD steady-state calculation method. If the coordinate system is defined as follows: x-axis points from the nose to the tail of the aircraft, y-axis points from the nose to the right, and z-axis points upwards and opposite to the direction of gravity, then the normal force is... The pitching moment is .
[0049] It should be noted that this step relies on steady CFD calculations to accurately obtain aerodynamic force data of the deployed payload under different launch conditions. Compared with unsteady numerical simulation, this significantly shortens the calculation time. At the same time, the unified coordinate system makes the definitions of normal force and pitch moment more standardized, ensuring the consistency and comparability of the force data.
[0050] Preferably, the mass and inertia information of the deployed load are obtained, wherein the mass of the deployed load is... m The moment of inertia of the deployed load is Using the force conditions of the load at the initial moment, the descent distance and pitch attitude angle are established longitudinally as a function of time. t Approximate expression for the change:
[0051]
[0052] in, h For the descent distance, The pitch angle for payload delivery. The initial falling speed, ω is the angular velocity.
[0053] It should be noted that this step transforms the separation motion state of the deployed load into a quantifiable mathematical relationship, establishing a motion model that closely matches the actual separation process. This provides core mathematical support for subsequent compatibility determination through numerical calculations. At the same time, the derivation method based on the initial force balances computational efficiency and model fit.
[0054] Preferably, a safety margin is considered. The separation compatibility criterion is constructed as a function of descent distance and time:
[0055]
[0056] in, and These are undetermined coefficients; if the inequality is not satisfied, then the separation is determined to be incompatible.
[0057] It should be noted that this step, by introducing a safety margin, makes the determination of separation compatibility more reliable, taking into account the safety requirements in engineering applications. At the same time, the inequality-form determination criterion makes the compatibility assessment more operational, and the determination can be completed through explicit numerical verification, avoiding the bias of subjective judgment.
[0058] Accordingly, this embodiment also provides an aircraft payload separation compatibility evaluation system, including: The parameter determination module is configured to determine the structural dimensional parameters of the delivery capsule embedded in the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload, thereby determining the launch location and launch conditions. The aerodynamic characteristic calculation module is configured to place the released load at the launch position and, based on the launch conditions, use a CFD steady-state calculation method to simulate the aerodynamic force and aerodynamic torque acting on the released load. The relational function calculation module is configured to establish a relational function of the descent distance and pitch attitude angle as a function of time during the separation of the deployed load, based on the aerodynamic force and aerodynamic torque, combined with the mass and inertia information of the deployed load; The compatibility assessment module is configured to combine the relationship function and safety assessment parameters to construct a separation compatibility judgment criterion, thereby determining whether the separation of the delivery payload and the embedded delivery capsule is compatible.
[0059] Specifically, the various functional modules of the evaluation system work together. First, the parameter determination module determines three types of parameters: the structural dimensions of the delivery capsule embedded in the aircraft, the launch flight of the delivery payload, and the separation safety, and outputs the corresponding launch position and launch conditions. Then, the aerodynamic characteristic calculation module retrieves the results, places the delivery payload in the corresponding launch position, and performs simulation calculations of aerodynamic forces and aerodynamic moments through CFD steady-state calculations based on the launch conditions. Subsequently, the relational function calculation module combines the mass and inertia information of the delivery payload and constructs a relational function of the descent distance and pitch attitude angle over time based on the aerodynamic characteristic calculation results. Finally, the compatibility evaluation module combines the relational function and safety evaluation parameters to construct separation compatibility judgment criteria and complete the final separation compatibility judgment.
[0060] It should be noted that by modularizing the entire process of separation compatibility assessment, the assessment process has been automated and standardized. Each module performs its own function and data can be shared, which greatly improves the efficiency and standardization of the assessment work. At the same time, the modular design facilitates system maintenance and functional expansion.
[0061] Example 2 This embodiment is based on embodiment 1: This embodiment provides a method for evaluating the compatibility of payload separation in an aircraft. Based on a certain aircraft, the design and evaluation of the length-to-depth ratio of the internal delivery module are carried out at three typical Mach numbers and altitudes, three typical flight angles of attack, and four typical delivery module length-to-depth ratios. The specific steps are as follows.
[0062] Based on a certain aircraft, typical payload launch and separation states are determined, as shown in Table 1, with a total of 36 states.
[0063] Table 1 - Launch and Separation Status of Payload from a High-Speed Aircraft
[0064] Based on the dimensions of the payload, the length L of the launch chamber is determined, and the design depth D of the launch chamber is 1000mm, 900mm, 800mm, and 700mm respectively. A typical structural diagram of the launch chamber is attached. Figure 2 As shown.
[0065] Determine the safety assessment parameters for the separation of the deployed payload from the embedded delivery capsule. Deployment payload length. The distance from the top of the head to the top is Appendix Figure 3 - Appendix Figure 5 Two scenarios are defined: the pitch attitude during the load drop process and the longitudinal collision.
[0066] Place the payload at the door of the delivery bay, as shown in the attached diagram. Figure 6As shown, CFD steady-state calculations were carried out based on the above launch conditions and four different depth delivery modules. The calculation results are shown in Table 2 (the coordinate system is defined as x pointing from the nose to the tail of the aircraft, y pointing from the nose to the right, and z pointing upwards in the opposite direction of gravity).
[0067] Table 2 - Aerodynamic forces of payload deployment under different aspect ratios and launch conditions
[0068] Set the mass of the dropped load m= 800kg, moment of inertia of the dropped load The initial falling speed is angular velocity The calculated pitch angle and descent distance of the load at three typical moments are shown in Table 3.
[0069] Table 3 - Typical Load Deployment Pitch Angle and Descent Distance
[0070] The coefficients of the safety margin function are defined as follows: Based on the data in Table 3, a typical time-based payload separation compatibility evaluation table is established, as shown in Table 4. Table 4 shows the separation time... t At 0.1s, states 9 and 18 are incompatible, separation time t At 0.2s, states 6, 9, 15, and 18 are incompatible; separation time t At 0.3s, states 6, 9, 15, and 18 are incompatible. According to the calculated states in Table 2, when the Mach number is large, the angle of attack is large, and the length-to-depth ratio of the delivery module is large, the delivery load separation is incompatible.
[0071] Table 4 - Compatibility Assessment of Load Deployment at Typical Moments
[0072] Example 3 This embodiment is based on embodiment 1: This embodiment provides a computer device, including a memory and a processor. The memory stores a computer program, and the processor executes the computer program to implement the aircraft payload separation compatibility evaluation method of Embodiment 1. The computer program can be in the form of source code, object code, executable file, or some intermediate form.
[0073] Specifically, a computer program for assessing the separation compatibility of the delivery payload and the embedded delivery module is stored in the memory of the computer device. The program contains all the execution steps of the assessment method in Example 1. When the processor calls and executes the computer program, it will automatically complete the separation compatibility assessment of the delivery payload and the embedded delivery module according to the steps of parameter determination, force simulation, function construction, and criterion judgment.
[0074] It should be noted that by digitizing the separation compatibility assessment method, the calculation, simulation and judgment of various parameters can be completed quickly by relying on the computing power of computer equipment, which greatly improves the efficiency of the assessment. At the same time, the assessment method can be standardized and implemented by computer, adapting to the batch assessment needs in engineering applications.
[0075] Example 4 This embodiment is based on embodiment 1: This embodiment provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the aircraft payload separation compatibility evaluation method of Embodiment 1. The computer program can be in the form of source code, object code, executable file, or some intermediate form. The storage medium includes any entity or device capable of carrying computer program code, a recording medium, a computer memory, a read-only memory (ROM), a random access memory (RAM), an electrical carrier signal, a telecommunication signal, and a software distribution medium, etc.
[0076] Specifically, a computer program is stored in a computer-readable storage medium. The program is developed according to the evaluation method of Embodiment 1 and contains all the execution logic and steps of the evaluation method. The storage medium can be read by various types of processors. When the processor retrieves and executes the program from the storage medium, it can complete the evaluation operation of the aircraft payload separation compatibility according to the established process.
[0077] It should be noted that this computer-readable storage medium enables the storage and portability of the separate compatibility evaluation program, allowing the evaluation method to be flexibly deployed and used on different computer devices, improving the application flexibility and scenario adaptability of the method. At the same time, the computer-readable storage medium also provides a reliable carrier for the preservation and dissemination of the program.
[0078] The above description is merely a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.
[0079] It should be noted that, for the sake of simplicity, the foregoing method embodiments are described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.
Claims
1. A method for evaluating the compatibility of payload separation during aircraft deployment, characterized in that, include: The structural dimensions of the delivery module embedded in the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload are determined in order to determine the launch location and launch conditions. The payload is placed at the launch position, and the aerodynamic forces and torques acting on the payload are simulated using a CFD steady-state calculation method based on the launch conditions. Based on the aforementioned aerodynamic forces and aerodynamic torques, and combined with the mass and inertia information of the deployed load, a relationship function is established between the descent distance and pitch attitude angle and time during the separation process of the deployed load. By combining the aforementioned relationship function and safety assessment parameters, a separation compatibility judgment criterion is constructed to determine whether the separation of the deployed payload and the embedded deployment compartment is compatible.
2. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 1, characterized in that, The method for determining the structural dimensions of the delivery compartment embedded in the aircraft includes: ignoring the internal details of the delivery compartment during the preliminary design stage, simplifying the structural dimensions of the delivery compartment to length L, width W, and depth D, where the length-to-depth ratio L / D is a key parameter affecting the separation characteristics.
3. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 1, characterized in that, The method for determining the key flight parameters for payload launch includes: Considering the main aerodynamic parameters affecting the launch of payloads embedded within the aircraft, including the incoming flow velocity Flow pressure Angle of attack and flight sideslip angle And there are: in, c The speed of sound at height H. Let H be the air density at altitude H; therefore, the key flight parameter for payload launch is determined as: Mach number. Ma Altitude H, Angle of Attack and flight sideslip angle .
4. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 1, characterized in that, The method for determining the safety assessment parameters for load separation includes: Treat the lower surface of the aircraft as a plane Determine the position parallel to the plane in the side view. The baseline OX; Determine the payload's nose apex A, bottom control surface endpoint B, and center of mass C, where points A and B have the best chance of impacting the plane. A collision occurs, forming an angle. or ; During the payload separation process, the pitch angle of the deployed payload. It should be between the included angles and Between, that is: in, It is the distance from the head of the deployed payload to the center of mass. It refers to the length of the load being deployed.
5. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 4, characterized in that, The step of placing the payload at the launch position and, based on the launch conditions, simulating the aerodynamic forces and moments acting on the payload using a CFD steady-state calculation method includes: The payload is placed at the launch position of the launch compartment. Based on the typical combination of launch parameters for internally embedded payloads, the aerodynamic forces and aerodynamic moments of the payload under different launch conditions are obtained using the CFD steady-state calculation method. If the coordinate system is defined with the x-axis pointing from the nose to the tail of the aircraft, the y-axis pointing from the nose to the right, and the z-axis pointing upwards in the opposite direction of gravity, then the normal force is... The pitching moment is .
6. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 5, characterized in that, Based on the aforementioned aerodynamic forces and aerodynamic moments, and combined with the mass and inertia information of the deployed load, a relationship function is established between the descent distance and pitch attitude angle during the load separation process and time, including: Obtain the mass and inertia information of the deployed payload, where the mass of the deployed payload is... m The moment of inertia of the deployed load is ; Using the force conditions of the load at the initial moment, the descent distance and pitch attitude angle are established longitudinally over time. t Approximate expression for the change: in, h For the descent distance, The pitch angle for payload delivery. The initial falling speed, ω is the angular velocity.
7. The method for evaluating the compatibility of payload separation during aircraft deployment according to claim 6, characterized in that, Combining the aforementioned relationship function and security assessment parameters, a separation compatibility determination criterion is constructed, including: Considering safety margin The separation compatibility criterion is constructed as a function of descent distance and time: in, and These are undetermined coefficients; if the inequality is not satisfied, then the separation is determined to be incompatible.
8. A system for evaluating the compatibility of payload separation during aircraft delivery, characterized in that, include: The parameter determination module is configured to determine the structural dimensional parameters of the delivery capsule embedded in the spacecraft, the key flight parameters for the launch of the delivery payload, and the safety assessment parameters for the separation of the delivery payload, thereby determining the launch location and launch conditions. The aerodynamic characteristic calculation module is configured to place the released load at the launch position and, based on the launch conditions, use a CFD steady-state calculation method to simulate the aerodynamic force and aerodynamic torque acting on the released load. The relational function calculation module is configured to establish a relational function of the descent distance and pitch attitude angle as a function of time during the separation of the deployed load, based on the aerodynamic force and aerodynamic torque, combined with the mass and inertia information of the deployed load; The compatibility assessment module is configured to combine the relationship function and safety assessment parameters to construct a separation compatibility judgment criterion, thereby determining whether the separation of the delivery payload and the embedded delivery capsule is compatible.
9. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the aircraft payload separation compatibility evaluation method according to any one of claims 1-7.
10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the aircraft payload separation compatibility evaluation method according to any one of claims 1-7.